Раздвоенный сопряженный винглет

ЗАКОНЦОВКА КРЫЛА

... 1. Законцовка крыла, предназначенная для крепления к наружному концу крыла, образующего плоскость крыла, и содержащая:верхний крылообразный элемент, выступающий вверх относительно плоскости крыла и имеющий заднюю кромку, инижний крылообразный элемент, неподвижно закрепленный относительно верхнего крылообразного элемента и имеющий корневую хорду и заднюю кромку, при этом корневая хорда нижнего крылообразного элемента пересекается с верхним крылообразным элементом, и нижний крылообразный элемент выступает вниз от места пересечения,при этом верхний крылообразный элемент имеет большие размеры, чем нижний крылообразный элемент, а задняя кромка нижнего крылообразного элемента примыкает к задней кромке верхнего крылообразного элемента в месте пересечения, ипри этом внутренний угол между верхним и нижним крылообразными элементами в месте пересечения меньше или равен 160°.2. Законцовка крыла по п.1, отличающаяся тем, что нижний крылообразный элемент имеет площадь в плане, которая составляет менее ...

Tragflügel

Die Erfindung betrifft einen Tragflügel, umfassend eine Flügelvorderkante (1), eine Flügelhinterkante (2) und am freien Ende einen zwischen Flügelvorderkante (1) und Flügelhinterkante (2) verlaufenden Flügelrand (3). Nach der Erfindung ist vorgesehen, dass am flügelhinterkantenseitigen Ende des Flügelrands (3) ein röhrenförmiges Element (4) zur Aufnahme und Durchleitung mindestens eines Teils eines vom Flügelrand (3) erzeugten Flügelrandwirbels angeordnet ist.

Winglet

Disclosed is a winglet 100 for attachment to a wing portion 200 of an aircraft, The winglet comprises a winglet root 102, defining a recess 106 for receiving a connector 230 of the wing portion and comprises protrusions 140, 150, for receipt into at least one corresponding hole (240, 250 figure 3) of the wing portion. A portion of the root 102 around the recess 106 has at least one hole 112, through it, for receiving a fastener 300 for fastening the winglet to the connector. Preferably the connector comprises a threaded screw surface which reacts to a screw-shaped fastener. Also disclosed is a wing portion for an aircraft which has a connector and a hole to receive a connector, and a wing portion having a convex surface portion.

Aircraft vapour trail control system

Primary structural element

An elongate structural element 200 (e.g. a spar (fig.2,200,300) or rib (fig.2,400)), suitable for a primary structure (fig.2,22) of an aircraft (fig.1,1) aerodynamic structure (e.g. a wing (fig.1,20), wingtip device (fig.1,30) or stabiliser (fig.1,40,50)), has a shear web 210 with a twist 211 about its longitudinal axis A-A so that a face of at least part of the web is non-planar when free from torque or torsional force applied about the longitudinal axis (i.e. a cross-sectional shape of the web at a first section 201&fig.4(i) is rotationally offset from one taken in the twisted section 202&fig.4(ii)). There may be multiple twists 211,212 about the longitudinal axis, which may be irregular such that the rate of rotational offset is non-uniform, or not consistent, along the axis. Preferably, the spar is made from a composite material formed with at least one fibre layup. Preferably, the spar has a flange 230 protruding from the web at an angle A of between 80 to 100 degrees. The flange is ...

Primary structural element

An elongate structural element 200 (e.g. a spar (fig.2,200,300) or rib (fig.2,400)), suitable for a primary structure (fig.2,22) of an aircraft (fig.1,1) aerodynamic structure (e.g. a wing (fig.1,20), wingtip device (fig.1,30) or stabiliser (fig.1,40,50)), has a shear web 210 with a twist 211 about its longitudinal axis A-A so that a face of at least part of the web is non-planar when free from torque or torsional force applied about the longitudinal axis (i.e. a cross-sectional shape of the web at a first section 201&fig.4(i) is rotationally offset from one taken in the twisted section 202&fig.4(ii)). There may be multiple twists 211,212 about the longitudinal axis, which may be irregular such that the rate of rotational offset is non-uniform, or not consistent, along the axis. Preferably, the spar is made from a composite material formed with at least one fibre layup. Preferably, the spar has a flange 230 protruding from the web at an angle A of between 80 to 100 degrees. The flange is ...

Actuator assembly for moving an aircraft wing tip device

SYSTEMS AND PROCEDURES FOR THE DESTABILIZATION OF A SHOVEL EDDY

Aerodynamic profile body for an aircraft

Aerodynamischer Profilkörper (1) für ein Flugzeug, insbesondere Winglet, mit einem eine Profilvorderkante (4a) aufweisenden vorderen Profilelement (2), mit einem eine Profilhinterkante (3a) aufweisenden hinteren Profilelement (3) und mit einer das vordere Profilelement (2) mit dem hinteren Profilelement (3) verbindenden Verstelleinheit (7), mit welcher das hintere Profilelement (3) gegenüber dem vorderen Profilelement (2) verstellbar ist, wobei die Verstelleinheit (7) eine mit dem vorderen Profilelement (2) verbundene vordere Lagereinrichtung (8), eine mit dem hinteren Profilelement (3) verbundene hintere Lagereinrichtung (9) und eine die vordere Lagereinrichtung (8) und die hintere Lagereinrichtung (9) miteinander verbindende Kraftübertragungseinrichtung (10) aufweist.

FLÜGELSPITZENVORRICHTUNG UND VERFAHREN

A wing tip device for fixing to the outboard end of a wing (301), the wing (301) defining a wing plane, the wing tip device comprising: an upper wing-like element (304) projecting upwardly and having a trailing edge; and a lower wing-like element (307) fixed with respect to the upper wing-like element (304) and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element (304), and the lower wing-like element (307) projecting downwardly from the intersection, wherein the upper wing-like element (304) is larger than the lower wing-like element (307) and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees, and wherein the lower wing-like element (307) has an element planform area less than approximately 25% of the ...

Wing tip device

A wing tip device for fixing to the outboard end of a wing (401), the wing defining a wing plane, the wing tip device comprising: an upper wing- like element (404) projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing- like element (407) fixed with respect to the upper wing- like element and having a root chord (412) and a trailing edge (417), the lower wing- like element root chord intersecting with the upper wing- like element, and the lower wing- like element projecting downwardly from the intersection, wherein the upper wing- like element is larger than the lower wing- like element and the trailing edge of the lower wing- like element is adjacent the trailing edge (416) of the upper wing- like element at the intersection, and wherein an included angle between the upper and lower wing- like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting ...

Fixed wing of an aircraft

A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box comprised of spars extending along the spanwise direction of the main wing, a plurality of ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box is comprised of a wing box base section (K10) and a wing box adapter section (20), that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device (W). In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib (R3) of the wing box base section (K10) up to the outermost rib (R5) of the wing box adapter section.

Application of conformal sub boundary layer vortex generators to a foil of aero / hydrodynamic surface

A method of improving aerodynamic performance of foils by the application of conformal, low drag vortex generators. A film of erosion protection material or other conformal material is placed on the foil to provide a medium for the incorporation of planform edge vortex generators. The form edge is shaped to achieve submerged vortex generating shapes of chevron or ogival planforms, extending primarily chordwise on the foil surface. The vortex generators promote improved boundary layer dynamics by mixing free stream flow into the boundary layer while minimising separation and fluid losses. At the trailing edge, the shape formed with the chevrons applied apex forward, acts as a vented gurney tab series and additionally as disruptors to the Von Karman Street wake, delaying sheet rollup into the tip vortice.

LIFT AUGMENTATION SYSTEM

This invention relates generally to a lift augmentation system for an airframe. More particularly, the invention concerns the combination of extendable/retractable wing tips with an airframe for lift augmentation as well as wings that can pivot into a deployed position. Flexible surface elements may be rolled for storage and unrolled for deployment with at least one being on the suction surface of the wing and at least one being on the pressure surface of the wing.

AIRCRAFT WITH ELLIPTICAL WINGLETS

An aircraft with swept back wings has winglets (202) at the outer ends of its wings (200). The winglets (202) curve upwardly as they extend outwardly from their intersection (204) with the wings (200). The curvature of the winglets (202) at least approximates a conical section curvature, e.g. an elliptical based on an ellipse having a major axis that extends vertically and coincides with the intersection (204) of the outer end of the wing (200) and the inner end of the winglet (202).

CONCEPT OF A VARIABLE WINGLET FOR LATERAL LOAD REDUCTION FOR COMBINED LATERAL AND VERTICAL LOAD REDUCTION, AND FOR IMPROVING THE PERFORMANCE OF MEANS OF LOCOMOTION

The present invention relates to a device for adapting aerodynamic characteristics of a wing element (1), wherein the device comprises a winglet (2), wherein the winglet (2) is movably attachable to the wing element (1), and wherein the winglet (2) or parts of the winglet is or are rotatable in relation to the wing element (1) such that an associated rotary axis (7) with a main direction of extension (6) of the wing element (1) encompasses an angle that differs from 90~.

CYLINDRICAL WING TIP WITH HELICAL SLOT

La présente invention concerne un dispositif ayant la forme d'une cavité cylindrique en spirale et/ou à fente hélicoïdale (15) permettant de réduire la traînée induite, le tourbillon marginal dit vortex et d'augmenter la finesse. Fixé solidaire à l'extrémité de l'aile (10) ou articulé toujours solidaire de cette extrémité d'aile, il peut s'adapter à tous profils, en particulier aux ailes des avions, des planeurs, aux pales d'hélicoptères et aux extrémités d'hélices tractantes, propulsantes ou propulsées comme les pales d'éoliennes ou encore pour appareils tels que bateaux ou sous-marins utilisant la portance ou la direction dans leur déplacement trois axes, vertical, horizontal et en lacets. Aux performances initiales, cette invention permet d'utiliser de plus faibles motorisations, de faire des trajets plus longs et plus vite tout en consommant moins d'énergie ou en produisant plus pour les éoliennes par exemple, d'utiliser des charges plus importantes, d'augmenter et d'aborder le trafic ...

ADHESIVE PANELS OF MICROVANE ARRAYS FOR REDUCING EFFECTS OF WINGTIP VORTICES

ABSTRACT In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing. CA 2913710 2019-03-20 ...

QUIET SLAT PROPELLER

An aircraft having a fuselage and a pair of fixed wings, and a propeller comprising at least one mounting member secured to at least one of the wings, a first and second blades rotatably connected to each mounting member and each having an airfoil shape. The first blade is configurable in a locked condition extending parallel to a leading edge of the wing during take-off and landing of the aircraft, and an unlocked, rotating condition, during flight for propelling the aircraft. The first blade is configured to be in the same plane in both the locked and unlocked conditions. The second blade is configured to rotate with the first blade within the plane in an unlocked, rotating condition and is pivotable about a hinge so as to extend transverse to the plane in a stowed condition. The first propeller blade can act as a Handley-Page slat during take-off and landing.

WINGTIP CONTROL SYSTEM

A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip.

WING TIP DEVICE FOR AN AIRCRAFT WING

A wing tip device for use with an aircraft wing having a wing tip. The wing tip device includes an upper winglet configured to extend upwardly from the aircraft wing when the wing tip device is positioned at the wing tip and a lower element configured to extend downwardly from the upper winglet and form a closed loop with a lower surface of the wing when the wing tip device is positioned at the wing tip, the closed loop having a hollow interior. The lower element is configured and positioned to redirect air as the aircraft moves through air, with the wing tip device positioned at the wing tip.

Wing-tip arrangement used for wing of aircraft, aircraft, and use

Propeller

Dispositif pour piloter un avion autour de son axe longitudinal.

Pilotage d'un avion autour de son axe longitudinal de roulis en braquant, selon un axe parallèle ou sensiblement parallèle à l'axe longitudinal de cet avion: - vers le haut (ou vers le bas) une seule à la fois de ses extrémités de voilure, dénommées "tiprons" lorsque la voilure présente sur toute son envergure un dièdre faible ou nul, - de la position verticale vers l'extérieur, une seule de ses extrémités de voilure dénommées "winglets mobiles" lorsque ces extrémités sont constituées de surfaces verticales. Outre le pilotage en roulis, une variante de ce dispositif permet pour un avion ou un engin aérospatial équipé de "winglets mobiles" inclinées, le pilotage en tangage. La figure 2 représente une réalisation selon l'invention dans laquelle un avion est équipé de "winglets mobiles" verticales (7) et (8). Chaque "winglet" est articulée autour d'un axe (6) parallèle à l'axe longitudinal de l'avion. Le braquage de la "winglet" (7) dans le sens indiqué par la flèche (9) induit le mouvement ...

SURGE CYLINDRICAL IN SPIRAL

PROCESS AND TESTING DEVICE OF PRODUCED SWIRL HAVE an END Of a VEHICLE

PLANE HAS ACTIVE CONTROL OF THE TWIST OF ITS WINGS

Surface aérodynamique orientable pour un aéronef

L'invention concerne une surface aérodynamique orientable d'un aéronef, telle qu'un aileron, articulée autour d'un axe 15 à chaque aile dudit aéronef et à l'arrière de laquelle est associé un compensateur aérodynamique 12, ladite surface 5 étant disposée en bout d'aile en étant directement actionnable par le pilote par des moyens de commande volontaire Selon l'invention, elle comprend au moins une ailette 18 fixée au voisinage de l'extrémité extérieure 19 de la face supérieure 20 de ladite surface aérodynamique 5 et sensiblement dans le prolongement de l'extrémité 21 de l'aile, ladite ailette 18 étant disposée dans un plan incliné tourné vers l'extérieur par rapport à ladite surface aérodynamique, en ayant sa direction générale sensiblement orthogonale à l'axe d'articulation 15 de ladite surface.

PLANE HAS YAW CONTROL BY DIFFERENTIAL TRAIL

METHOD FOR MONITORING THE DIRECTION OF AIRCRAFT, AS WELL AS AIRCRAFT ADAPTED FOR WORK SAID METHOD

Wing tip or propeller blade tip attachment comprises hollow cylinder with chamfered end and spiral slit to reduce drag

La présente invention concerne un dispositif ayant la forme d'une cavité cylindrique en spirale et/ ou à fente hélicoïdale permettant de réduire la traînée induite, le tourbillon marginal dit vortex et d'augmenter la finesse. Fixé solidaire à l'extrémité de l'aile ou articulé toujours solidaire de cette extrémité d'aile, il peut s'adapter à tous profils, en particulier aux ailes des avions, des planeurs, aux pales d'hélicoptères et aux extrémités d'hélices tractantes, propulsantes ou propulsées comme les pales d'éoliennes ou encore pour appareils tels que bateaux ou sous-marins utilisant la portance ou la direction dans leur déplacement trois axes, vertical, horizontal et en lacets. Aux performances initiales, cette invention permet d'utiliser de plus faibles motorisations, de faire des trajets plus longs et plus vite tout en consommant moins d'énergie ou en produisant plus pour les éoliennes par exemple, d'utiliser des charges plus importantes, d'augmenter et d'aborder le trafic transition ...

Body presenting a hydrodynamic profile, in particular stabilizing aileron for ships

L'invention concerne un corps présentant un profil hydrodynamique, notamment un aileron stabilisateur pour navires. Dans ce corps (1) présentant un profil hydrodynamique, par exemple dans un stabilisateur à ailerons ou un safran de gouvernail de navires ou un aileron formant quille de voiliers à quille qui est fixé sur un corps de support, de préférence un corps de navire de façon à faire saillie librement, sont fixées à l'extrémité libre du corps (1a) plusieurs nervures (R1 -R6 ) de façon à faire saillie, librement qui sont disposées les unes à côtés des autres à une certaine distance et parallèlement au plan de symétrie du corps, et dont la longueur présente à peu près 1/10 à 1/20 de la longueur du corps, par quoi des tourbillons se produisant à l'extrémité du corps peuvent être supprimés ou diminués. L'invention se rapporte à la construction des navires.

폴리케톤 섬유를 포함하는 폴리케톤 항공기 윙팁장치

... 본 발명은 일산화탄소, 에틸렌 및 프로필렌 공중합체로부터 폴리케톤 용액을 제조하고, 상기 폴리케톤 용액으로부터 강도와 신도가 우수한 폴리케톤 섬유 및 이를 포함하는 폴리케톤 항공기 윙팁장치에 관한 것이다.

브레이드 복합 날개보

... 브레이드 복합 날개보 또는 브레이드 복합 날개보용 예비 성형체로서, 복수의 튜브형 브레이드 섬유 플라이를 포함한다. 각 플라이들은 인접하는 회전쌍 사이에서 소정의 피치를 갖는 제1 회전 세트로 시계 방향으로 권취되는 제1 섬유 세트와, 인접하는 회전쌍 사이에서 소정의 피치를 갖는 제2 회전 세트로 반시계 방향으로 권취되는 제2 섬유 세트를 포함한다. 각 플라이들의 상기 제1 섬유 세트 및 상기 제2 섬유 세트는 브레이드 구조체를 형성하도록 서로 얽혀있다. 상기 날개보 또는 예비 성형체는 뿌리부에서 말단부로 길이 방향으로 연장하며, 상기 말단부를 향해 내측으로 가늘어지는 경사부를 갖는다. 각 플라이들은 상기 경사부에서 각 플라이들이 내측으로 가늘어질 때 감소되는 외주를 갖는다. 하나 이상의 플라이에 있어서, 상기 제1 섬유 세트와 상기 제2 섬유 세트의 피치는 상기 경사부에서 각 플라이들이 내측으로 가늘어질 때 증가한다. 날개보 또는 예비 성형체는 윙렛용 튜브형 주 날개보를 제공하는데 사용될 수 있다. 윙렛은 상부 캡과 하부 캡으로 연결되는 전방 웨브와 후방 웨브를 포함하는 전방 날개보를 포함한다. 또한, 상기 윙렛의 상부 스킨은 브레이드 날개보와 상부 전방 날개보 캡에 연결된다. 윙렛의 하부 스킨은 브리에드 날개보와 하부 전방 날개보 캡에 연결된다.

noise attenuating element, edge module of flape, panels of noise attenuation and acoustic attenuation, and, method of making a noise attenuation.

THERMALLY CONFIGURABLE STRUCTURAL ELEMENTS ESPECIALLY USEFUL FOR AIRCRAFT COMPONENTS

BRAIDED COMPOSITE SPAR

A braided composite spar (10) or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar (10) or preform extends lengthwise from a root(10a) to a tip (10b), and the spar or preform has a tapered portion (25) in which each ply has a height which reduces and a width which increases as it extends toward the tip. The spar (10) or preform can be used to provide a tubular main spar for a winglet (5). The winglet (5) also has a front spar (11) with a front spar web (16), an upper front spar cap (17), and a lower front spar cap (18). An upper skin (19) of the winglet (5) is joined to the braided spar (10) and the upper front spar cap (17). A lower skin (20) of the winglet (5) is joined to the braided spar (10) and the lower front spar cap (18).

BLUNT-LEADING-EDGE RAKED WINGTIPS

An airplane having a fuselage (11), opposed main wings (12), and blunt-leading-edge raked wingtips (8) is provided. Each main wing includes an outboard end (9) and a leading edge (14) having an outboard end leading-edge nose and nose radius. One blunt raked wingtip (8) is located at each main wing outboard end (9) and includes a leading edge (20) swept back from the main wing leading edge (14). Each blunt raked wingtip (8) further includes a plurality of local airfoils each having a leading-edge nose radius and a chord. The nose radius is greater than about 2 % of the local chord for the majority of the airfoils. The relative bluntness of the raked wingtips minimizes boundary-layer separation, drag associated with boundary-layer separation, and premature buffeting of the aircraft during low speed flight.

Wingtip device of a wing, and also a wing with such a wingtip device

A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided.

Adhesive panels of microvane arrays for reducing effects of wingtip vortices

A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

Aircraft lighting device

A wing tip device (108) has a lighting device (138) arranged to project from a spanwise portion (112) onto a substantially vertical portion (114) of the wing tip device 108.

SYSTEM AND METHOD FOR IMPROVED ROTOR TIP PERFORMANCE

Раздвоенный сопряженный винглет

FIELD: aviation. SUBSTANCE: versions of the winglets are made with possibility of attachment to aircraft wing. Winglet smoothly passes from wing end above plane of wing chords and can have underwing stabilizer protruding below plane of chords from lower surface of upper winglet. Upper winglet can have transition section bent upward from wing end to transition into substantially flat section. Upper and lower surfaces of top winglet can be limited by front and rear edges, which are deflected in direction of air flow, parallel to plane of chords, and are bent in direction of air flow, terminating at point far from wing end. Upper and lower surfaces of underwing stabilizer can be limited by front and rear edges, which are bent in direction of air flow and terminate at point, far from wing end. Versions of the winglet modification method characterize the manufacturing process using the curved blade. EFFECT: group of inventions is aimed at reduction of inductive resistance. 38 cl, 16 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 698 502 C2 (51) МПК B64C 23/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B64C 23/065 (2019.02); Y02T 50/164 (2019.02) (21)(22) Заявка: 2017105216, 05.08.2015 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): АВИЭЙШН ПАРТНЕРС, ИНК. (US) Дата регистрации: 28.08.2019 Приоритет(ы): (30) Конвенционный приоритет: 05.08.2014 US 14/452,424 (43) Дата публикации заявки: 07.09.2018 Бюл. № 25 (45) Опубликовано: 28.08.2019 Бюл. № 25 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 06.03.2017 2 6 9 8 5 0 2 (56) Список документов, цитированных в отчете о поиске: US 2012312928 A1, 13.12.2012. US 2004169110 А1, 02.09.2004. RU 2233769 C1, 10.08.2004. R U 05.08.2015 (72) Автор(ы): ГРАТЦЕР Луи Б. (US) US 2015/043819 (05.08.2015) C 2 C 2 (86) Заявка PCT: (87) Публикация заявки PCT: R U 2 6 9 8 5 0 2 WO 2016/022692 (11.02.2016) Адрес для переписки: 191036, Санкт- ...

СИСТЕМА КОНЦЕВЫХ КРЫЛЫШЕК, ЛЕТАТЕЛЬНЫЙ АППАРАТ И СПОСОБ РАБОТЫ ЛЕТАТЕЛЬНОГО АППАРАТА

Система концевых крылышек для крыла летательного аппарата содержит верхнее концевое крылышко и нижнее концевое крылышко, установленные на законцовке крыла. Нижнее концевое крылышко имеет статическое положение, когда крыло подвержено действию статической нагрузке при стоянке на земле. Нижнее концевое крылышко выполнено таким образом, чтобы отклонение крыла вверх при полетной нагрузке, приблизительно равной 1g, вызывает перемещение нижнего концевого крылышка из статического положения в полетное положение, образуя в результате относительное увеличение размаха крыла. Летательный аппарат содержит систему концевых крылышек, которые расположены на пересечении границы пролета ворот и линии просвета при тангаже и крене. Способ работы летательного аппарата характеризуется перемещением крылышек. Группа изобретений направлена на снижение индуктивного сопротивления крыла. 3 н. и 17 з.п. ф-лы, 15 ил.

ЗАКОНЦОВКА

Законцовка аэродинамической поверхности содержит верхнюю и нижнюю стороны, сопрягаемые между собой с образованием передней и задней кромок, а также рабочей изогнутой кромки, состоящей из входящего и исходящего участков, примыкающих к передней и задней кромкам и сопрягающихся в точке, соответствующей максимальному размаху аэродинамической поверхности таким образом, что проекция рабочей кромки на плоскость хорд имеет вид обращенной наружу дуги постоянного или переменного радиуса. Законцовка дополнительно содержит два стока пограничного слоя, расположенных в ряд на исходящем участке рабочей кромки с возможностью дробления сердцевины концевого вихря на вихревые жгуты сонаправленного вращения. Каждый из стоков выполнен в виде конструктивного элемента треугольной формы, образованного верхней и нижней поверхностями, являющимися продолжением верхней и нижней поверхностей и сопрягаемыми между собой с образованием внешней и тыльной кромок, являющихся составной частью рабочей кромки. Внешняя кромка ...

АЭРОГИДРОДИНАМИЧЕСКАЯ ПОВЕРХНОСТЬ, ГРУППА ВИХРЕГЕНЕРАТОРОВ И СПОСОБ УСТАНОВКИ ГРУППЫ ВИХРЕГЕНЕРАТОРОВ

Группа изобретений относится к области аэрогидродинамики. Аэрогидродинамическая поверхность включает группу вихрегенераторов и основную часть, содержащую две стороны, сопряженные между собой с образованием задней части с задней кромкой и передней части с передней кромкой. Группа вихрегенераторов включает возвышения с рабочими кромками, имеющими серповидную форму и расположенными вблизи передней кромки. Фронтальные проекции рабочих кромок расположены под углом от 60 до 80 градусов к фронтальной проекции передней кромки с возможностью генерации присоединенных вихревых структур встречного вращения. Отношение расстояния между серединами фронтальных проекций к высоте фронтальных проекций равно от 0,5 до 1,5. Касательные к серединам фронтальных проекций расположены под углом от 20 до 60 градусов друг к другу. Возвышения выполнены в виде гребней, огибающих переднюю кромку и имеющих серповидную форму. Рабочие кромки образованы внешними краями гребней. Группа вихрегенераторов выполнена в виде набора ...

КОНСОЛЬ КРЫЛА ЛЕТАТЕЛЬНОГО АППАРАТА С УСТРОЙСТВОМ ДЛЯ УПРАВЛЕНИЯ ПО КУРСУ

Изобретение относится к устройствам для управления летательным аппаратом (ЛА) с помощью подвижных аэродинамических поверхностей. Консоль крыла (1) ЛА содержит устройство для управления по курсу, установленное на концевой части консоли. Устройство содержит корневой (2) и концевой (3) элементы. Элементы выполнены в виде аэродинамических поверхностей. Первый торец (4) корневого (2) элемента сопряжен с концевым сечением (5) консоли. Концевое сечение выполнено в плоскости, параллельной плоскости симметрии (6) летательного аппарата. Второй (7) торец корневого элемента сопряжен с внутренним торцом (8) концевого (3) элемента. В устройстве обеспечена возможность одновременного независимого поворота корневого (2) элемента относительно консоли крыла (2), а концевого (3) элемента относительно корневого (2) элемента. Изобретение направлено на управление по курсу с помощью устройства, размещенного на консоли крыла без возникновения дополнительных аэродинамических моментов крена и тангажа. 5 з.п. ф-лы ...

Steuervorrichtung fuer Luftfahrzeuge

Aerofoil tip vortex reducing structure

For reducing wind turbine tip vortices, each blade tip comprises two or more vanes 3,6 or winglets separated by a gap 7 through which flow that would have formed a vortex core is passed from the upwind to the downwind blade sides. The trailing vane trailing edge is close to the main blade trailing edge. The pressure of fluid passing through the gap falls to the downwind side pressure so flow is ejected in a direction opposite that of blade motion to suppress rapidly revolving vortex core formation. A shroud 10 may cover two vane tips to prevent the formation of secondary vortices. The vane stagger at their roots is greater than that of the main foil and reduces along the length of the vane. The leading vane may be tilted towards the suction surface and the same length or shorter than the trailing vane which may tilt towards the pressure surface.

An aircraft wing

An aircraft wing 5 having a connection interface 9 at the tip of the wing where the wing is configurable between a first configuration in which a first wing tip device 7 is connected to the connection interface, and a second configuration in which a second wing tip device 11 is connected to the connection interface to replace the first wing tip device. The design of the wing (5) is such that it is designed for performance in both the first and the second configurations. Also claimed is an aircraft wing that is configurable between a first and second configuration for use during a first and second mission profile, where the performance of the wing is improved during the second mission profile when it is in the second configuration rather than if it had remained in the first configuration.

Wing-tip device

Aircraft wing with a moveable wing tip for load alleviation

A method of designing a winglet and a winglet designed thereby

A method of designing a winglet 3 for an aircraft 7 comprises the steps of: defining the location of the winglet root; defining a maximum height for the winglet tip; defining a maximum span for the winglet; creating the winglet shape by locating the winglet root 13', locating the winglet tip 15' at the location of maximum height and maximum span, and connecting the winglet root 13' to the winglet tip 15' using a winglet shape. The winglet shape comprises a curved transition region 17' extending away from the root, and a wing-like region extending from the distal end of the transition region 17' to the winglet tip 15'. The step of creating the winglet shape comprises iteratively changing the curvature and/or the location of the centre of the curvature of the transition region, whilst maintaining the locations of the winglet root and winglet tip. The total length of the winglet 3 from root 13 to tip 17 is increased whilst keeping the winglet 3 within the maximum height H and span S constraints ...

Apparatus, aircraft and method for moving a wing tip device away from a load-alleviating configuration

An aircraft (Fig 1a, 1) comprises a fixed wing (7) and a wing tip device 9 moveably mounted thereon. The wing tip device is movable from a load-alleviating configuration to a flight configuration. The wing tip device comprises an airflow channel 88 extending between respective apertures 83, 84 on the upper surface and lower surface of the wing tip device. The channel is configurable between an open state in which air can flow through the channel and a closed state in which the airflow through the channel is blocked. The channel is configured such that when the wing tip device is in the load-alleviating configuration and the channel is in the open state, the aerodynamic loading on the wing tip device in flight urges the wing tip device towards the flight configuration. An actuator may be incorporated into the device to assist the movement between the two positions.

Improvements relating to aircraft wings

... 818,188. Aircraft. KONINKLIJKE LUCHTVAART MAATSCHAPPIJ N. V. Sept. 21, 1956 [Sept. 24,1955; Sept. 11, 1956], No. 28955/56. Class 4. An aircraft wing comprises a tip tank extending above and below the adjacent surfaces of the wing and a projection extending outwardly from the tank to a tip of substantially smaller height than that between an imaginary extension of the wing surfaces adjacent the tank at the region of maximum thickness of the wing. Fig. 5 shows a plan, where in the tank 8 is fitted with an extension 9. Fig. 7 shows a front elevation of one form of the extension, and Fig. 8 is a front elevation of another form, wherein two extensions 4 are normally inclined upwardly and outwardly as at a, but can be rotated about fore-and-aft axes in opposite senses as at a, to control the aircraft in roll. In another form, Fig. 9 (not shown), the extensions comprise plates of constant thickness which are extendable or retractable spanwise from the tank, and are operated conjointly with spoilers ...

Apparatus, aircraft and method for moving a wing tip device away from a load-alleviating configuration

DEVICE AND PROCEDURE FOR THE CONTROL OF WAKE SUCTION CURRENTS

CYLINDRICAL WINGTIP WITH SCREW-SHAPED SLOT

LOAD-BEARING STRUCTURE WITH REDUCED TIP VORTEX

La structure portante telle qu'une aile est munie de plaquettes dentelées (16) à ses bords libres pour briser la tourbillon marginal produit à ces endroits par la distribution de pression du fluide. La dissipation du tourbillon est accélérée, la rémanence du tourbillon est considérablement réduite. Dans le cas d'un déflecteur d'une ligne d'hydrophones (30) touée par un navire (31) pour réaliser des essais sismiques en mer, le bruit perturbant les hydrophones (30) est réduit. Dans le cas d'applications marines, les risques de cavitation sont réduits considérablement, notamment en ce qui concerne des stabilisateurs ou des hélices. Dans le cas d'applications en aéronautique, la rémanence des tourbillons au décollage et à l'atterrissage d'avions est réduite.

ACTIVE SYSTEMS AND METHODS FOR CONTROLLING AN AIRFOIL VORTEX

Active systems and methods for controlling aircraft vortices are disclosed. An apparatus in accordance with one embodiment is directed to an aircraft system that includes an airfoil having first and second oppositely facing flow surfaces and a tip. The system can further include a vortex dissipation device carried by the airfoil, with the vortex dissipation device including an orifice positioned to direct a flow of fluid outwardly from the tip, an actuator operatively coupled to the fluid flow orifice and positioned to change a manner in which flow is directed outwardly from the tip, and a controller operatively coupled to the actuator to direct the operation of the actuator. The vortex dissipation device can be activated to accelerate the rate at which vortices (e.g., wing tip vortices) dissipate after they are generated, for example, by alternately pulsing flow inwardly and outwardly through the fluid flow orifice.

A WINGLET

A winglet (12) for an aircraft wing is provided. The winglet (12) has an airflow control arrangement, for example in the form of a trailing edge flap (20) by means of which lift generated by the winglet can be varied. The control arrangement desirably forms part of a manoeuvre load alleviation system (22) for the aircraft.

WING TIP DEVICE

An aircraft 1 comprises a wing (5) having a positive dihedral, the wing comprising a tip and a wing tip device (7 ) mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region (7d) inclined at a cant of more than (180) degrees. The region (7d) is arranged to generate lift during flight. The region (7d) inclined at a cant of more than (180) degrees may be located at the distal end (11) of the wing tip device (7). The wing tip may be swept and may aeroelastically deform during flight.

Fixed wing of an aircraft

A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box comprised of spars extending along the spanwise direction of the main wing, a plurality of ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box is comprised of a wing box base section (K10) and a wing box adapter section (20), that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device (W). In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib (R3) of the wing box base section (K10) up to the outermost rib (R5) of the wing box adapter section.

DEVICE Of TIP Of WING, BLADE Of WIND MILL OR HYDROLIENNE ALLOWING TO EVEN DECREASE TO CANCEL the MARGINAL SWIRLS SAID VORTEX

MONTAGE DE PLANS ADDITIONNELS EN BOUTS D'AILES

AUX BOUTS DES AILES 2 SONT MONTES AU MOINS UN 3, DE PREFERENCE DEUX PLANS ADDITIONNELS 3, 4 JUXTAPOSES QUI S'ETENDENT DANS LE SENS DE L'ENVERGURE ET DONT L'EFFICACITE PEUT ETRE MODIFIEE PAR UNE ROTATION COMMANDEE DE TOUS LES PLANS OU D'UNE PARTIE DE CEUX-CI. LES PLANS ADDITIONNELS PEUVENT TOURNER AUTOUR D'UN AXE 6 QUI EST SITUE A PEU PRES DANS LE PLAN DE LA CORDE DU PROFIL DE L'AILE 2. DANS LE CAS D'UN PLAN ADDITIONNEL AVANT PLACE SENSIBLEMENT EN AVANT DE LA LIGNE ELASTIQUE DE L'AILE, UN VOLET PEUT ETRE PLACE SUR SON ARETE ARRIERE POUR AUGMENTER SON EFFICACITE.

BEARING STRUCTURE HAS REDUCED MARGINAL SWIRL

La structure portante telle qu'une aile est munie de plaquettes dentelées (16) à ses bords libres pour briser le tourbillon marginal produit à ces endroits par la distribution de pression du fluide. La dissipation du tourbillon est accélérée, la rémanence du tourbillon est considérablement réduite. Dans le cas d'un déflecteur d'une ligne d'hydrophones (30) touée par un navire (31) pour réaliser des essais sismiques en mer, le bruit perturbant les hydrophones (30) est réduit. Dans le cas d'applications marines, les risques de cavitation sont réduits considérablement, notamment en ce qui concerne des stabilisateurs ou des hélices. Dans le cas d'applications en aéronautique, la rémanence des tourbillons au décollage et à l'atterrissage d'avions est réduite.

Turbulence reducing device for tip of wing or blade of e.g. wind turbine, has salmon having depth from leading edge towards trailing edge of blade, where salmon is adapted according to fluids in which it moves at normal speeds

Dispositif d'extrémité d'aile ou de pale d'éolienne ou d'hydrolienne permettant pour une éolienne une nette diminution des fluctuations de puissance à moins de 1% et de réduire sensiblement le flux turbulent, tourbillons marginaux dits vortex des ailes comme celles des avions.

윙팁 장치

... 윙 본체를 구비하는 상기 윙의 바깥쪽 단부에 장착되는 윙팁 장치로서, 상기 윙팁 장치는; 후연을 포함하고, 상기 윙 본체에 대하여 상부로 도출하는 상부 윙 형태 부재와; 뿌리부 익현 및 후연을 포함하고 상기 상부 윙 형태 부재에 고정되는 하부 윙 형태 부재를 포함하고; 상기 윙 형태 부재의 뿌리부 익현은 상기 상부 윙 형태 부재와 교차하고, 상기 교차하는 지점으로부터 하부로 돌출하며, 또한, 상기 상부 윙 형태 부재는 상기 하부 윙 형태 부재보다 크고, 상기 하부 윙 형태 부재의 후연은 상기 교차하는 지점에서 상기 상부 윙 형태 부재의 후연과 인접하며, 상기 교차하는 지점에서의 상기 상부 윙 형태 부재와 상기 하부 윙 형태 부재 사이의 각도는 160°이하이다. 또한, 상기 윙팁 장치가 장착된 윙; 상기 윙이 장착된 항공기; 상기 윙팁 장치를 윙에 장착 또는 새로 장착하는 방법; 기존의 장치를 조절하는 방법; 및 상기 윙팁 장치가 장착된 윙을 작동하는 방법에 관한 것이다.

Toy airplane for education

WINGLETS WITH RECESSED SURFACES, AND ASSOCIATED SYSTEMS AND METHODS

Winglets (130) with recessed surfaces (150), and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing (110) having an inboard portion (111) and an outboard portion (112), and further includes a winglet (130) coupled to the wing at the outboard portion. The winglet can have a first surface (131) facing at least partially inboard and a second surface (132) facing at least partially outboard, with the first surface including a recessed region (150).

AIRCRAFT DRAG MANAGEMENT STRUCTURE

Drag management structure. The structure includes a tube having an entrance and exit along a longitudinal axis. At least one row of stationary swirl generating vanes is provided at the entrance, the swirl vanes disposed at an angle with respect to the longitudinal axis selected to produce a steady streamwise vortex in a fluid at the tube exit. A fan rotor may be disposed upstream of the stationary vanes.

FIXED WING MICRO AERIAL VEHICLE

Fixed wing micro aerial vehicle characterized in that it comprises an allowing platform (1) composed by two low aspect ratio semi-wings (2) with substantially trapezoidal planform, equipped with elevons (4) along their trailing edge and with outboard vertical fins (3) for lateral-directional stability.

LIFT AUGMENTATION SYSTEM

This invention relates generally to a lift augmentation system for an airframe. More particularly, the invention concerns the combination of extendable/retractable wing tips with an airframe for lift augmentation as well as wings that can pivot into a deployed position. Flexible surface elements may be rolled for storage and unrolled for deployment with at least one being on the suction surface of the wing and at least one being on the pressure surface of the wing.

FLUID FLOW CONTROL DEVICE FOR A WING TIP

A fluid flow control device (10) for an aerofoil (11) comprises an aerofoil -tip body (17) of aerofoil shape, coupling apparatus (36) adapted to couple one end of the body (17) to an aerofoil (11), and a passive tip blowing assembly (16). The passive tip blowing assembly (16) is provided at the other end of the aerofoil -tip and comprises a housing (18) defining a fluid chamber (23) and a vane (22) of aerofoil shape. The fluid chamber extends along part of the chord- length of the body and has a fluid inlet (27) and a fluid outlet (28). The vane is arranged along the chord of the aerofoil- tip, with its leading edge (22a) at the inlet and its trailing edge (22b) at the outlet. The aerofoil section of the aerofoil -tip (17) has a higher camber than that of the aerofoil (1), which turns fluid flow across the low pressure side (32) of the aerofoil towards the aerofoil -tip (17), so that the fluid flow mirrors the fluid flow across the high pressure side (33) of the aerofoil.

Energy conserving supersonic aircraft

This invention is an extension of my system to recover into useful work the energy normally wasted by a supersonic aircraft in its shock wave mechanism. This system utilizes the excess propulsive jet velocity in a sheet below the wing to form a planar vortex flap which acts as a pressure shield. The present improvement extends the pressure generating forward concave wing undersurface of this system into an upward reflexed aft surface so as to benefit from the increased pressure provided by the downstream upwash vortex field. This allows the aft portion of the wing to serve as the energy recovery section by achieving the pressure required for lift on the undersurface of this aft wing portion at a lesser angle with reduced drag. This stream-wise series of functions specifies the wing undersurface as concave, convex, and concave sequentially in the flow direction, thus corresponding to the upper element of a planar supersonic nozzle. The jet manifold and its continuing vortex flap below comprise ...

AN AIRCRAFT

An aircraft () comprising a fuselage (), an anhedral rearwardly-swept leading wing () for generating lift connected to an upper portion of the fuselage, and a dihedral forwardly-swept trailing wing () for generating lift attached to a lower portion of the fuselage. The trailing wing () is arranged to be vertically lower than the leading wing () in flight. The leading wing () and trailing wing () are blended together at their wingtips, forming a common wingtip (), such that the underside surface () of the leading wing () forms a generally continuous and smoothly transitioning surface with the upper surface () of the trailing wing () so as to form a vortex guide surface () such that vortex air flow from the leading wing () is guided by the vortex guide surface () onto, or into the path of, the trailing wing (). 1. An aircraft comprising a fuselage , an anhedral rearwardly-swept leading wing for generating lift connected to an upper portion of the fuselage , and a dihedral forwardly-swept trailing wing for generating lift attached to a lower portion of the fuselage , the trailing wing being arranged to be vertically lower than the leading wing in flight , wherein the leading wing and trailing wing are blended together at their wingtips , forming a common wingtip , such that the underside surface of the leading wing forms a generally continuous and smoothly transitioning surface with the upper surface of the trailing wing so as to form a vortex guide surface such that vortex air flow from the leading wing is guided by the vortex guide surface onto , or into the path of , the trailing wing.2. The aircraft of claim 1 , wherein the vortex guide surface comprises a blended surface of the underside surface of the leading wing and the upper surface of the trailing wing.3. The aircraft of or claim 1 , wherein the upper surface of the leading wing forms a generally continuous surface and smoothly transitioning with the underside surface of the trailing wing.4. The aircraft of ...

Apparatus and method for the control of trailing wake flows

A system and method for dissipating vortices that form at the wingtips on aircraft and from other airfoils. A jet air stream is discharged in a location at or proximate to the outer end portion of the airfoil into the vortex flow, and the jet air stream is moved cyclically back and forth. The cyclic movement can be at lower or higher frequencies to alleviate at least in part intensity of the vortex or accelerate instability of the vortex which leads to vortex dissipation.

MORPHING CONTROL SURFACE

The invention relates to an aerodynamic profiled body for an aircraft, in particular a winglet, comprising a front profiled element having a profile front edge, a rear profiled element having a profile rear edge, and an adjusting unit, which connects the front profiled element to the rear profiled element and by means of which the rear profiled element can be moved in relation to the front profiled element, wherein the adjusting unit has a front mounting device connected to the front profiled element, a rear mounting device connected to the rear profiled element, and a force-transmitting device, which connects the front mounting device and the rear mounting device to each other.

Active winglet

An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

WING CONTROL DEVICES

TIP VORTEX GENERATION TECHNOLOGY FOR CREATING A LIFT ENHANCING AND DRAG REDUCING UPWASH EFFECT

Wing tip thrust augmentation system

A system for augmenting the thrust of aircraft involving the presence of fixed wing tip aerodynamic surfaces (14, 15) which extend both above and below the wing reference plane and are canted inward. The surfaces develop thrust components from the energy otherwise lost in wing tip vortices while producing essentially no net additional outer wing lift, thereby minimizing any increase in wing design bending moments due to their presence. The surfaces may be swept aft or forward and are secured to the wings in the tip regions forward of the wing trailing edge.

КОНСОЛЬ КРЫЛА САМОЛЕТА

УСТРОЙСТВО ДЛЯ ОБРАЗОВАНИЯ АЭРОДИНАМИЧЕСКИХ ВИХРЕЙ, А ТАКЖЕ РЕГУЛИРУЕМЫЙ ЗАКРЫЛОК И КРЫЛО С УСТРОЙСТВОМ ДЛЯ ОБРАЗОВАНИЯ АЭРОДИНАМИЧЕСКИХ ВИХРЕЙ

... 1. Устройство (10) для образования аэродинамических вихрей для размещения на расположенном по размаху боковом краю (12, 32) крыла (3) или расположенном на нем с возможностью перестановки регулируемом закрылке (4, 5), при этом устройство (10) для образования вихрей образовано по меньшей мере из одной детали крыла, отличающееся тем, что ! - по меньшей мере одна деталь крыла выполнена в виде перемещаемой относительно крыла или регулируемого закрылка (4, 5) в направлении их размаха детали, ! - на соответствующем расположенном по размаху краю крыла или регулируемого закрылка (4, 5) выполнена выемка для приема детали (11, 12, 13) крыла, и устройство (10) для образования вихрей имеет исполнительное устройство для убирания и выпускания детали крыла в выемку, а также приводное устройство для приведения в действие исполнительного устройства. ! 2. Устройство (10) для образования вихрей по п.1, отличающееся тем, что устройство (10) для образования вихрей образовано из нескольких деталей (11, 12, 13 ...

ЗАКОНЦОВКА КРЫЛА

... 1. Узел крыло-законцовка крыла, содержащий крыло, имеющее наружный конец и базовую плоскость, и законцовку крыла, имеющую корневой участок, присоединенный к наружному концу крыла, изогнутую под углом вверх секцию, вершину над базовой плоскостью крыла и переходный участок между изогнутой под углом вверх секцией и вершиной, на котором внешний угол наклона законцовки крыла уменьшается относительно базовой плоскости крыла. ! 2. Узел по п.1, отличающийся тем, что по меньшей мере часть законцовки крыла имеет плавный изгиб и содержит точку перегиба, в которой кривизна по размаху законцовки крыла меняет знак. ! 3. Узел по п.2, отличающийся тем, что внешний угол наклона законцовки крыла плавно уменьшается по длине переходного участка. ! 4. Узел по п.1, отличающийся тем, что законцовка крыла имеет дальнюю секцию между переходным участком и вершиной, причем дальняя секция образует с изогнутой под углом вверх секцией законцовки крыла угол в диапазоне 75-105° при взгляде в направлении, перпендикулярном ...

Retrofit flight control surface

A method of retrofitting a wing of a fixed wing aircraft. An existing aircraft wing with a main fixed wing portion 20; with a tip end and an existing movable flight control surface 30 connected adjacent the tip end is provided. The existing movable flight control surface is removed from the main fixed wing portion, and a wing tip device 40a and movable flight control surface 30a are selected as a pair to replace the existing movable flight control surface. The selected movable flight control surface has an aerodynamic surface of different shape to the one removed from the wing. The selected wing tip device and movable flight control surface are then fitted to the main fixed wing portion. Also disclosed is a wing where a ratio of the local cord length of the moveable flight control surface to the local cord length of the wind varies in the spanwise direction. Also disclosed is a wing where a camber of an aerofoil section of the wing including the inboard edge of the moveable flight control ...

An aircraft wing with a wing tip device and a strut

Stall trigger system

Wingtip device for an aircraft

An aircraft wing (102 fig 1) includes a closed surface wing tip device (104 fig 1) which includes an element or actuator 330 within the wing tip for deforming/morphing the shape of the wing tip between geometrical configurations having different aerodynamic properties, for example including one with better overall fuel efficiency for a shorter journey and one with overall fuel efficiency better suited for a longer journey. The device 400 includes a lower winglet 406 with an essentially planar portion 410 spaced apart from the main body of the wing by a blended transition region which is shaped such that the curvature of the local dihedral increases in the outboard direction. The device 400 includes an upper aerofoil structure 414 which with the winglet 406 essentially forms the closed surface.

An aircraft wing and wing tip device

BASIC STRUCTURE WITH REDUCED MARGINAL VORTEX

ACTIVE SYSTEMS AND PROCEDURES FOR THE CONTROLLING OF A BEARING AREA EDDY

FLÜGELSPITZENVORRICHTUNG AND METHOD

Tragflügelendvorrichtung zum Befestigen an einem Außenbordende eines Tragflügels (401), wobei der Tragflügel eine Flugebene definiert, mit einem oberen flügelartigen Element (404), das in Bezug auf die Flügelebene nach oben ragt und eine Hinterkante aufweist, und einem unteren flügelartigen Element (407), das in Bezug auf das obere flügelartige Element (404) fixiert ist und eine Wurzel-Profilsehne (412) und eine Hinterkante aufweist, wobei sich die Wurzel-Profilsehne (412) des unteren flügelartigen Elements mit dem oberen flügelartigen Element (404) schneidet und das untere flügelartige Element (407) von der Schnittstelle nach unten ragt, wobei das obere flügelartige Element (404) größer ist als das untere flügelartige Element (407) und die Hinterkante des unteren flügelartigen Elements (407) an der Schnittstelle an der Hinterkante des oberen flügelartigen Elements (404) angrenzt, und wobei ein eingeschlossener Winkel zwischen dem oberen (404) und dem unteren (407) flügelartigen Element ...

FLÜGELSPITZENVORRICHTUNG AND METHOD

Tragflügelendvorrichtung zum Befestigen an einem Außenbordende eines Tragflügels (401), wobei der Tragflügel eine Flugebene definiert, mit einem oberen flügelartigen Element (404), das in Bezug auf die Flügelebene nach oben ragt und eine Hinterkante aufweist, und einem unteren flügelartigen Element (407), das in Bezug auf das obere flügelartige Element (404) fixiert ist und eine Wurzel-Profilsehne (412) und eine Hinterkante aufweist, wobei sich die Wurzel-Profilsehne (412) des unteren flügelartigen Elements mit dem oberen flügelartigen Element (404) schneidet und das untere flügelartige Element (407) von der Schnittstelle nach unten ragt, wobei das obere flügelartige Element (404) größer ist als das untere flügelartige Element (407) und die Hinterkante des unteren flügelartigen Elements (407) an der Schnittstelle an der Hinterkante des oberen flügelartigen Elements (404) angrenzt, und wobei ein eingeschlossener Winkel zwischen dem oberen (404) und dem unteren (407) flügelartigen Element ...

FLÜGELSPITZENVORRICHTUNG UND VERFAHREN

A wing tip device for fixing to the outboard end of a wing (301), the wing (301) defining a wing plane, the wing tip device comprising: an upper wing-like element (304) projecting upwardly and having a trailing edge; and a lower wing-like element (307) fixed with respect to the upper wing-like element (304) and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element (304), and the lower wing-like element (307) projecting downwardly from the intersection, wherein the upper wing-like element (304) is larger than the lower wing-like element (307) and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees, and wherein the lower wing-like element (307) has an element planform area less than approximately 25% of the ...

Wingtip device of a wing, and also a wing with such a wingtip device

A wingtip device (W; W1, W2, W4, W5, W6, W7, W8) for a wing (T; 10a, 10b), which has an inner end (E1) and an outer end (E2), and in which the local dihedral of the wingtip device (W; W1, W2, W4, W5, W6, W7, W8) increases or reduces from the inner end (E1) to the outer end (E2), with a pressure-side flow surface (U-W) and a suction-side flow surface (P-W), wherein at least two ancillary wing sections (100; 101, 102, 103) are arranged on the wingtip device (W; W1, W2, W4, W5, W6, W7, W8), projecting in each case from the flow surface of the wingtip device (W; W1, W2, W3, W4, W5, W6, W7, W8), and wherein the ancillary wing sections (100; 101, 102, 103) in each case form an interface (q0) with the surface of the wingtip device (W; W1, W2, W4, W5, W6, W7, W8); which interfaces are located spaced apart from one another, and a wing (T) with such a wingtip device (W; W1, W2, W4, W5, W6, W7, W8).

FLOW-MECHANICALLY EFFECTIVE SURFACE FOR MINIMIZING INDUCED RESISTANCE

A flow-mechanically effective surface of a device moving in a fluid, in particular a flying machine, more particularly a support surface for a flying machine is disclosed, whereby said surface (1) comprises an elastic axis (EA) running in the span direction (6) of the surface (1) and an adjustable control surface (3). According to the invention, the surface (1) may be elastically deformed in the bending direction and/or in the direction of the elastic axis (EA), depending on the setting of the control surface (3) by means of a change in the induced flow-mechanical resistance and a control and/or regulation device is provided for setting the control surface (3) with regard to a minimisation of the induced flow-mechanical resistance of the surface (1).

WING-TIP ARRANGEMENT HAVING VORTILONS ATTACHED TO A LOWER SURFACE, AN AIRCRAFT HAVING SUCH A WING-TIP ARRANGEMENT AND THE USE OF VORTILONS ON A WING-TIP ARRANGEMENT

A wing-tip arrangement (2) couplable with a wing (38) of an aircraft comprises a connection region (4) for coupling or integration with the wing end region (10), at least one tip, at least one upper surface (14) and at least one lower surface (16), which extend between a leading edge (6) and a trailing edge (8) of the wing-tip arrangement (2) from the connection region (4) to the at least one tip, and at least one vortilon (18). The local dihedral of the wing-tip arrangement (2) changes between the at least one tip and the connection region (4), such that at least a part of the wing-tip arrangement projects at an angle relative to the wing, when coupled with the wing end region (10). The at least one vortilon (18) comprises a vortilon base (22) and a vortilon tip (24), wherein the vortilon base (22) is attached to at least one of the at least one lower surface (16) of the wing-tip arrangement (2) and wherein the vortilon tip (24) faces in an upstream direction.

Aircraft winglet design having a compound curve profile

An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets ( 302 ) are located at the outer end of each wing ( 300 ) and curve upwardly as they extend outwardly from their intersection ( 304 ) with the wings ( 300 ). The curvature profile ( 303 ) of the winglets ( 302 ) when viewed from the rear (or front) of the aircraft at least approximates a specified curve profile made up of more than one curved section, e.g. the winglet trailing edge profile ( 305 ) having a perpendicular projection onto a plane normal to the winglet inner or root chord ( 342 ), said projection creating a winglet profile curve approximating a compound curve composed of two arc segment ( 306, 307 ). The two arc segments are tangent to each other at there point of connection ( 306 b, 307 a ) wherein the arc segment ( 306 ) at the lower portion of the winglet connects to the outer end of the wing ( 300 ) and is tangent with the wing's reference plane ( 331 ). This lower arc segment ( 306 ) of the winglet profile connects to and is tangent with a second and arc segment ( 307 ) forming the profile of the upper portion of the winglet ( 302 ). A unique design specification for the plan form or developed shape of the winglet that is suitable for wings having nominal (less than 15 degrees) aft sweep, or have neutral, or forward sweep is also provided.

WING TIP DEVICE

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, includes: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection. The upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection. An included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. 1. A wing tip device for fixing to the outboard end of a wing , the wing defining a wing plane , the wing tip device comprising:an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; anda lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection,wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, andwherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.2. A wing tip device according to claim 1 , wherein the lower wing-like element has an element planform area less than approximately 25% of the upper wing-like element planform area.3. A wing tip device according to claim 1 , wherein an included angle between the wing plane and the lower wing-like ...

Performance-enhancing winglet system and method

A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to a ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move from the static position to an in-flight position and resulting in a relative span increase of the wing.

FIXED WING OF AN AIRCRAFT

A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K) up to the outermost rib of the wing box adapter section. 220. The wing according to claim 1 , characterized in that the wing adapter section () is an integral part of the main wing (M).320. The wing according to claim 1 , characterized in that the wing adapter section () is a separate part of the main wing (M) attached thereto.5. The fixed wing according to claim 1 , characterized in that the local sweep of the leading edge of the fixed wing in its nominal state of construction increases by between 10 and 45 degrees in the area of the wing box adapter section.620. The fixed wing according to claim 1 , characterized in that the outer end of the wing box adapter section (K) has a connection device for securing a wing tip device.710. The fixed wing according to claim 1 , characterized in that the wing box adapter section that forms the outer end area of the wing box is designed for the attachment of a wing tip device claim 1 , wherein the wing tip device with an inner rib is joined to an outer rib of the wing box base section (K).8. The fixed wing according to claim 6 , characterized in that the connection device is designed as a positive-locking part on the outer end as viewed from the wing root claim 6 , so as to positively attach a wing tip device to be coupled with the wing box ...

WING FOR AN AIRCRAFT, AIRCRAFT AND METHOD FOR REDUCING AERODYNAMIC DRAG AND IMPROVING MAXIMUM LIFT

A wing for an aircraft includes a leading edge and a wing tip extension extending from an end of a main wing region to a wing tip. The wing tip extension includes an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, which openings are connected to an air conveying device for conveying air through the openings. Thereby in flight states with a low flight velocity the flow around a wing tip extension can be harmonized such that the drag is decreased and the lift of the wing is increased. 1. A wing for an aircraft , comprising:a leading edge; anda wing tip extension extending from an end of a main wing region to a wing tip,wherein the wing tip extension comprises an arrangement of openings at least from the end of a main wing region to the wing tip along the leading edge, said openings connected to an air conveying device for conveying air through the openings.2. The wing of claim 1 , further comprising a leading edge high lift device arrangement with an outboard leading edge high lift device having an outer edge claim 1 ,wherein the arrangement of openings extends for up to 20% of the wingspan from the outer edge of the outboard leading edge high lift device to an inboard direction.3. The wing of claim 1 , wherein the arrangement of openings is positioned in the proximity of the region with the highest flow instability in terms of separation tendency on the wing with extended high lift devices.4. The wing of claim 1 , wherein the openings are selected from a group of openings claim 1 , the group consisting ofat least one bore hole,at least one slit introduced into the surface of the wing in a direction parallel to the leading edge,at least one slit introduced into the surface of the wing in a direction normal to the leading edge,at least one slit introduced into the surface of the surface element in a direction at an angle to the leading edge.5. The wing of claim 1 ,wherein the arrangement of openings comprises ...

WING TIP DEVICE

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting With the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection. 1. A wing tip device for fixing to the outboard end of a wing , the wing defining a wing plane , the wing tip device comprising:an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; anda lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection,wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, andwherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees.2. A wing tip device according to claim 1 , wherein the upper wing-like element includes a substantially planar portion and a non-planar curved wing tip extension adapted to smoothly blend the outboard end of the wing into the substantially planar portion of the upper wing-like element.3. A wing tip device according to claim 2 , wherein the non-planar curved wing tip extension has increasing curvature of local dihedral in the outboard direction.4. A wing tip device according to claim 1 , wherein the non-planar curved wing tip extension has continuously increasing sweepback of both the leading and trailing ...

Wing Tip With Winglet And Ventral Fin

A method of improving performance of an aircraft, including attaching a wing tip to a wing of the aircraft. The wing tip includes a winglet and a ventral fin. The winglet includes a winglet leading edge, a winglet trailing edge, an adapter section, a transition section attached to the adapter section, a blade section attached to the transition section, and a first tip section attached to the blade section. The ventral fin is coupled to the winglet at an attachment location adjacent the transition section. The ventral fin includes a second tip section. The wing has a wing leading edge and a wing trailing edge in a wing chord plane. Attaching the wing tip to the wing includes connecting the adapter section to the wing such that the winglet leading edge continuously transitions from the wing leading edge, and the winglet trailing edge continuously transitions from the wing trailing edge. 1. A method of improving performance of an aircraft , comprising: [ a winglet leading edge;', 'a winglet trailing edge;', 'an adapter section;', 'a transition section attached to the adapter section;', 'a blade section attached to the transition section; and', 'a first tip section attached to the blade section; and, 'a winglet, comprising, 'a ventral fin coupled to the winglet at an attachment location adjacent the transition section, the ventral fin comprising a second tip section; and, 'obtaining a wing tip, the wing tip comprising the winglet leading edge continuously transitions from the wing leading edge,', 'the winglet trailing edge continuously transitions from the wing trailing edge,', 'the blade section extends above the wing chord plane,', 'the ventral fin extends below the wing chord plane,', 'the first tip section has a leading edge curved toward a freestream air direction, and', 'the second tip section has a leading edge curved toward the freestream air direction., 'connecting the adapter section of the winglet to the wing, wherein, 'attaching the wing tip to a wing of the ...

Aircraft winglet design having a compound curve profile

An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets (302) are located at the outer end of each wing (300) and curve upwardly as they extend outwardly from their intersection (304) with the wings (300). The curvature profile (303) of the winglets (302) when viewed from the rear (or front) of the aircraft at least approximates a specified curve profile made up of more than one curved section, e.g. the winglet trailing edge profile (305) having a perpendicular projection onto a plane normal to the winglet inner or root chord (342), said projection creating a winglet profile curve approximating a compound curve composed of two arc segment (306, 307). The two arc segments are tangent to each other at there point of connection (306b, 307a) wherein the arc segment (306) at the lower portion of the winglet connects to the outer end of the wing (300) and is tangent with the wing's reference plane (331). This lower arc segment (306) of the winglet profile connects to and is tangent with a second arc segment (307) forming the profile of the upper portion of the winglet (302). A unique design specification for the plan form or developed shape of the winglet that is suitable for wings having nominal (less than 15 degrees) aft sweep, or have neutral, or forward sweep is also provided.

Active Winglet

An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency. 120-. (canceled)21. A wing of an aircraft comprising:an angled portion coupled to the wing outboard of an aileron; anda controllable airflow modification device coupled to the wing inboard of the angled portion, the controllable airflow modification device controllable independently of the aileron, and the controllable airflow modification device configured to reduce a load on the wing.22. The wing of claim 21 , the load comprising stress in the wing caused at least in part by an aerodynamic load exerted on the angled portion.23. The wing of claim 21 , the controllable airflow modification device configured to reduce the load on the wing below a design load.24. The wing of claim 21 , the controllable airflow modification device configured to reduce a spanwise section load to a level at or below a design value for an analogous wing without an angled portion.25. The wing of claim 21 , the controllable airflow modification device being configured to adjust a control surface of the winglet at least one of electronically claim 21 , mechanically claim 21 , hydraulically claim 21 , pneumatically claim 21 , or a combination thereof.26. The wing of claim 21 , the controllable airflow modification device coupled to a control system for controlling a control surface of the controllable airflow modification device.27. The wing of claim 26 , the control system comprising a control device with control logic claim 26 , the control device being communicatively coupled ...

AIRCRAFT WING WITH WING TIP DEVICE

An aircraft wing assembly including: a wing having a wing box structure with an upper wing cover and a lower wing cover, and a wing tip device attached to the outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm, a seal assembly aerodynamically seals the gap, wherein the seal assembly includes a bridging component on an interior side of the gap, and a seal which fills the gap and is supported by the bridging component. 1. An aircraft wing assembly comprising:a wing having a wing box structure including an upper wing cover and a lower wing cover;a wing tip device attached to an outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm; anda seal assembly configured to aerodynamically seal the gap, wherein the seal assembly includes a bridging portion extending across an interior side of the gap to bridge the gap, and a seal portion which projects from the bridging portion to fill the gap.2. The aircraft wing assembly according to wherein the bridging portion extends inboard of the edge of the lower wing cover and outboard of the edge of the wing tip device lower cover to retain the seal portion within the gap.3. The aircraft wing assembly according to claim 1 , wherein the seal assembly includes a retaining portion fixed to the seal portion and extending across an exterior side of the gap to retain the seal portion within the gap.4. The aircraft wing assembly according to wherein the seal assembly is self-retaining.5. The aircraft wing assembly according to claim 1 , wherein the bridging portion comprises an inboard flange which abuts an interior surface of the lower wing cover claim 1 , and an outboard flange which abuts an interior surface of the wing tip device lower cover ...

ADJUSTABLE LIFT MODIFICATION WINGTIP

An adjustable lift modification wingtip may be attached to a baseline wing of an aircraft. The adjustable lift modification wingtip may comprise a horizontal portion including a control surface and a vertical portion coupled to the horizontal portion. The vertical portion may move about an axis that may be substantially perpendicular to the horizontal portion. The control surface and the vertical portion may be adjusted in conjunction to increase wing efficiency at a flight condition. 1. A winglet fixedly attachable to a baseline wing of an aircraft comprising:a horizontal portion comprising a control surface; anda vertical portion coupled to the horizontal portion, the vertical portion being configured to move about an axis that is substantially perpendicular to the horizontal portion, the control surface and the vertical portion which, when attached to the baseline wing of the aircraft increase wing efficiency at a flight condition.2. The winglet of claim 1 , further comprising a control system for controlling motion of the control surface and the vertical portion based at least in part on in-flight flight condition data.3. The winglet of claim 2 , the control system being communicatively coupled to a sensor located on the aircraft and configured to receive a signal from the sensor located on the aircraft.4. The winglet of claim 2 , the control system configured to:deflect the control surface down and rotate a leading edge of the vertical portion in to increase lift at a first flight condition; anddeflect the control surface up and rotate the leading edge of the vertical portion out to decrease lift at a second flight condition.5. The winglet of claim 4 , the control surface configured to deflect between 15 degrees up and 15 degrees down; and the vertical portion configured to deflect between 4 degrees in and 4 degrees out.6. The winglet of claim 2 , the control system being configured to control the control surface and vertical portion independently of at least ...

One-Piece Composite Bifurcated Winglet

A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft.

WINGLET SYSTEM AND METHOD

A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet may have a length of approximately 50-80 percent of a length of the upper winglet. 1. A winglet system , comprising:an upper winglet and a lower winglet mounted to a wing;the lower winglet has a length of approximately 50-80 percent of a length of the upper winglet;the lower winglet having a static position when the wing is subject to an on-ground static loading; andthe lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.2. The winglet system of wherein:the lower winglet is oriented at an anhedral angle of no less than approximately 15 degrees during the upward deflection of the wing under the approximate 1-g flight loading.3. The winglet system of wherein:the upper winglet is oriented at a dihedral angle of at least approximately 60 degrees during upward deflection of the wing under the approximate 1-g flight loading.4. The winglet system of claim 1 , wherein:an upper winglet tip and a lower winglet tip terminate at approximately the same lateral location when the wing is under the on-ground static loading.5. The winglet system of wherein:the ...

ELLIPTICAL WING TIP AND METHOD OF FABRICATING SAME

A wingtip of a lifting surface of an aeronautical vehicle, the lifting surface having a span, a leading edge, a trailing edge, an upper surface and a lower surface, the wingtip being in a range of five percent to fifteen percent of an end portion of the span of the lifting surface, the wingtip including: an elliptical shape between the leading and trailing edges, the elliptical shape tapering in a direction towards an outer edge of the wing tip, wherein the tapering occurs in a plurality of geometric parameters of the lifting surface including spanwise chord distribution between the leading and trailing edges, spanwise mean camber distribution between the leading including and trailing edges, spanwise maximum thickness between the upper and lower surfaces, and spanwise twist of a mean average of the spanwise chord distribution of the wingtip. 1. A wingtip of an airfoil of an aircraft , the airfoil having a span , a leading edge , a trailing edge , an upper surface and a lower surface , the wingtip being in a range of five percent to fifteen percent of an end portion of the span of the airfoil , the wingtip comprising: an elliptical shape between the leading and trailing edges , the elliptical shape tapering in a direction towards an outer edge of the wing tip , wherein the tapering of the wingtip occurs in four geometric parameters including spanwise chord distribution between the leading and trailing edges , spanwise mean camber distribution between the leading and trailing edges , spanwise maximum thickness between the upper and lower surfaces , and spanwise twist of a mean average of the spanwise chord distribution of the wingtip; andwherein the chord length is tapered in a range of 0.45 to 0.50 of the initial chord at 100% span, the mean camber distribution tapers to zero at 100% span, a thickness to chord ratio tapers to less than one percent at 100% span, and twist of a mean chord distribution of the span of the wingtip is in a range of negative one degree and ...

SPLIT WINGLET SYSTEM

A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing. 1. A winglet system , comprising:an upper winglet and a lower winglet mounted to a wing;the lower winglet having a static position when the wing is subject to an on-ground static loading;the lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading; andthe lower winglet being configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.2. The winglet system of claim 1 , wherein:the wing has a wing tip including a wing tip chord;the upper winglet and the lower winglet each having a root chord; andthe upper winglet root chord and the lower winglet root chord each have a length of at least approximately 50 percent of the wing tip chord.3. The winglet system of claim 2 , wherein: ...

Structural health monitoring sensory system integrated to a self-adapting morphing system

A system and method for damage detection and for evaluating the real operation conditions for structural platforms using structural health monitoring is integrated to a system and method that permits for the platform to provide a flexible geometric control considering a self-adapting morphing which is capable of providing better operating structural platform performance.

WINGTIP FOR A GENERAL AVIATION AIRCRAFT

A wingtip for extending a wing of an aircraft having a NACA 23012 airfoil. The wingtip has an airfoil design for directing and associated wingtip vortex outward and upward to thereby increase the effective wingspan of the aircraft and to reduce induced drag. The wingtip is preferably molded and comprises a fuel tank bay, internal antenna, landing light and navigation light. 1. A wingtip for extending a wing of an aircraft having a NACA 23012 airfoil, the wing tip has an airfoil design which directs an associated wingtip vortex outward and upward to thereby increase the effective wingspan of the aircraft to reduce induced drag The present invention relates to wing tips for general aviation aircraft. More particularly, the present invention relates to a wing tip particularly designed for a Beechcraft Bonanza type aircraft.General aviation aircraft are a class of airplanes comprising business and personal aircraft which are not military or airline transport aircraft. One of the most popular types of general aviation aircraft is a Beechcraft Bonanza type aircraft, in particular a Bonanza or Baron model aircraft. The production of these aircraft started in 1947 and many are still flying today. Although several different models have been made over the years reflecting new and improved technology, the models still use the same airfoil: NACA 23012.Although the airfoil of the models does not represent recently developed technology, bonanzas are well known for their aerodynamic efficiency and good performance. However, there remains room for improvement, particularly with respect to wingtip design.In accordance with the present invention, an add-on or replacement wingtip is provided which is particularly well-suited for installation on Beechcraft bonanza or Baron aircraft, hereinafter collectively referred to as Bonanza aircraft. Installation of a wingtip of the present invention on a Bonanza aircraft provides additional lift while lowering the induced drag of the Bonanza ...

AIRCRAFT WING WITH A WING TIP DEVICE AND A STRUT

An aircraft wing () has a wing tip device () joined thereto. The root () of the wing tip device () is joined to the tip of the wing () at a first connection (). An external strut () extends between the wing () and the wing tip device (), the strut () being joined to the wing () at a second connection (). The second connection () is inboard of the first connection, such that loadings on the wing tip device () generated during use, are transferred, via the strut (), to a location on the wing () that is inboard of where the root () of the wing tip device () is joined to the tip of the wing. 1. An aircraft wing having a wing tip device joined thereto ,wherein the root of the wing tip device is joined to the tip of the wing at a first connection,and wherein an external strut extends between the wing and the wing tip device,the strut being joined to the wing at a second connection, the second connection being inboard of the first connection, such that loadings on the wing tip device generated during use, are transferred, via the strut, to a location on the wing that is inboard of where the root of the wing tip device is joined to the tip of the wing.2. The aircraft wing according to claim 1 , wherein the wing was originally designed not to have the wing tip device claim 1 , the wing tip device having been retro-fitted or forward-fitted to the wing.3. The aircraft wing according to claim 1 , wherein the first connection is unsuitable for transferring the loadings on the wing tip device to the wing claim 1 , in the absence of the strut.4. The aircraft wing according to claim 3 , wherein the first connection is substantially unable to support a bending moment across the first connection claim 3 , wherein the bending moment is applied by the wing tip device in absence of the external strut.5. The aircraft wing according to claim 1 , wherein an assembly comprising the wing claim 1 , the strut and the wing tip device is statically determinate.6. The aircraft wing according to ...

LAMINAR FLOW WINGLET

An aircraft wing tip device may include a unitized, monolithic leading edge torque box that may be formed of polymer matrix fiber-reinforced material. The leading edge torque box may include a skin that may define a continuous, uninterrupted outer mold line surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length. The leading edge torque box may further include at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith. 1. A wing tip device for an aircraft , comprising: a skin defining a continuous, uninterrupted outer mold line (OML) surface extending aftwardly from a winglet leading edge by a distance of at least approximately 60 percent of a local chord length; and', 'at least one internal component extending between opposing inner surfaces of the skin and being integrally formed therewith., 'a unitized, monolithic leading edge torque box formed of polymer matrix fiber-reinforced material and including2. The wing tip device of claim 1 , wherein:the leading edge torque box is formed as a co-cured assembly of composite layups of the skin and the internal component.3. The wing tip device of claim 2 , wherein:the composite layups comprise at least one of thermosetting composite material, thermoplastic composite material, pre-impregnated composite material, and resin-infused composite material.4. The wing tip device of claim 1 , wherein:the internal component comprises a spar extending at least partially along a spanwise direction of the wing tip device.5. The wing tip device of claim 4 , wherein:the leading edge torque box includes a front spar and a rear spar;the front spar being located aft of the winglet leading edge; andthe rear spar being located at a torque box aft end.6. The wing tip device of claim 1 , wherein:the wing tip device comprises one of a raked wing tip and a split winglet having upper and lower winglets.7. The ...

Active winglet

An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

Aircraft wing with wing tip device

An aircraft wing assembly comprising a wing ( 2 ) having a wing box structure including an upper wing cover ( 7 ) and a lower wing cover ( 8 ), and a wing tip device ( 1 ) attached to the outboard end of the wing, the wing tip device including an upper cover ( 9 ) and a lower cover ( 10 ), wherein a gap (g) between opposing edges of the wing tip device lower cover ( 10 ) and the lower wing cover ( 8 ) is at least 5 mm, and further comprising a seal assembly ( 20 ) for aerodynamically sealing the gap (g), wherein the seal assembly ( 20 ) includes a bridging component ( 21 ) on an interior side of the gap (g), and a seal ( 22 ) which fills the gap (g) and is supported by the bridging component ( 21 ). Also, an aircraft having the wing assembly, and a method of attaching a wing tip device ( 1 ) to the outboard end of a wing ( 2 ).

WINGTIP DEVICE OF A WING, AND ALSO A WING WITH SUCH A WINGTIP DEVICE

A wingtip device for a wing is provided. The wingtip device has an inner end and an outer end, and in which the local dihedral of the wingtip device increases or reduces from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface. At least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the flow surface of the wingtip device. The ancillary wing sections in each case form an interface with the surface of the wingtip device; which interfaces are located spaced apart from one another. A wing with such a wingtip device is also provided. 1. A wingtip device for a wing , comprising:an inner end; and at least two ancillary wing sections are arranged on the wingtip device, projecting in each case from the pressure-side flow surface of the wingtip device, and', 'the ancillary wing sections in each case form an interface with the pressure-side flow surface of the wingtip device; which interfaces are located spaced apart from one another., 'an outer end, in which a local dihedral of the wingtip device increases from the inner end to the outer end, with a pressure-side flow surface and a suction-side flow surface, wherein2. The wingtip device according to claim 1 , wherein the separation distance between each pair of interfaces is at least 1.5 times the length of the shorter of the two ancillary wing sections.3. The wingtip device in accordance with claim 1 , wherein with reference to a section through the wingtip device in a YZ-plane claim 1 , at least one ancillary wing section is arranged on a side of the wingtip device claim 1 , which generally has a convex curvature.4. The wingtip device claim 1 , in accordance with claim 1 , wherein a local central plane of the ancillary wing section is inclined at an angle of less than 30 degrees relative to a local thickness direction of a local wingtip device coordinates system claim 1 , at least within a region of up to 85% of the length of the ...

INTEGRAL ANTENNA WINGLET

Disclosed is a winglet radome assembly, which can include at least one antenna assembly that can send and receive signals, such as radio waves. Some implementations of the winglet radome assembly can be secured to a wing of an aircraft, such as a fixed-wing aircraft. In addition, the winglet radome assembly can be configured to secure to a distal end of the wing and can be securely adapted to a variety of aircraft. 1. A winglet radome apparatus , comprising:an aerodynamic body configured to securely mate to a distal end of a wing of an aircraft, wherein the body is made out of a material that allows uninterrupted transmission of a wireless signal through the material;an antenna assembly enclosed within the body and configured to at least one of send the wireless signal to or receive the wireless signal from at least one location outside the body, the antenna assembly including a grounding element that enables the antenna assembly to ground to at least the wing of the aircraft.2. The winglet radome apparatus of claim 1 , wherein the grounding element is made out of one or more of a copper material claim 1 , copper coated material claim 1 , tin-plated copper claim 1 , or a highly conductive metal that is plated for corrosion resistance.3. The winglet radome apparatus of claim 1 , wherein the grounding element includes a ground strap configured to directly mate with the wing and provide conductivity between the antenna assembly and the wing.4. The winglet radome apparatus of claim 1 , wherein at least the body forms an extension to the wing of the aircraft when the body is securely mounted to the distal end of the wing.5. The winglet radome apparatus of claim 4 , wherein the body extends along at least a part of a longitudinal axis of the wing.6. The winglet radome apparatus of claim 5 , wherein the distal end of the body deflects away from the longitudinal axis of the wing forming an upturned wingtip.7. The winglet radome apparatus of claim 6 , wherein at least a part ...

TRAILING EDGE COMPONENTS, AIRCRAFT STRUCTURES INCLUDING TRAILING EDGE COMPONENTS AND METHODS FOR MANUFACTURING TRAILING EDGE COMPONENTS

Trailing edge components of aircraft structures, aircraft structures comprising such trialing edge components, and methods of manufacturing such trailing edge components are provided. In an exemplary embodiment, a trailing edge component includes a first skin comprising a first plurality of plies of carbon fiber reinforced polymer material and having a first mating region. The first plurality of plies includes a first ply with a first drop-off edge in the first mating region. A second skin includes a second plurality of plies of carbon fiber reinforced polymer material and having a second mating region affixed to the first mating region. 1. A trailing edge component comprising:a first skin comprising a first plurality of plies of carbon fiber reinforced polymer material and having a first mating region, the first plurality of plies comprising a first ply with a first drop-off edge in the first mating region; anda second skin comprising a second plurality of plies of carbon fiber reinforced polymer material and having a second mating region affixed to the first mating region.2. The trailing edge component of claim 1 , wherein the first mating region has a tapered cross-section.3. The trailing edge component of claim 1 , wherein the second plurality of plies comprises a second ply with a second drop-off edge in the second mating region.4. The trailing edge component of claim 1 , wherein the second mating region has a tapered cross-section.5. The trailing edge component of claim 1 , wherein the first plurality of plies of the first skin comprises the same carbon fiber reinforced polymer material.6. The trailing edge component of claim 1 , wherein the first drop-off edge in the first mating region extends from a first side of the first skin to a second side of the first skin.7. The trailing edge component of claim 1 , wherein the carbon fiber reinforced polymer material comprises a braided fabric claim 1 , a woven fabric claim 1 , a unidirectional tape claim 1 , a sheet ...

An aircraft with a foldable wing tip device

An aircraft including a wing ( 1 ) and a wing tip device ( 6 ). The wing tip device ( 6 ) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded inwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device ( 6 ) is connected to the wing along a hinge axis ( 14 ) by spar beams ( 10 and 12 ) of the wing tip device, one of the beams being mounted for pivoting about a fixed axis and the other beam being mounted on a spherical bearing ( 15 ) to provide greater freedom of movement. Various actuator arrangements may be provided to pivot the wing tip device.

ONE-PIECE COMPOSITE BIFURCATED WINGLET

A method and apparatus for forming a composite winglet for an aircraft is presented. The composite winglet comprises a first blade, a second blade, and a root region. The first blade includes a first leading edge and a first trailing edge. The second blade includes a second leading edge and a second trailing edge. The second blade is positioned at an angle to the first blade. The root region is co-cured with the first blade and the second blade to form the composite winglet. The root region is configured to receive an attachment system for attaching the composite winglet to a wing of the aircraft. 1. A manufacture that comprises a winglet that comprises a unitary bifurcated structure that comprises three ply-sets co-cured to comprise a root region integral to the unitary bifurcated structure and configured for attachment onto a tip of a wing.2. The manufacture of claim 1 , further comprising the winglet being devoid of fasteners.3. The manufacture of claim 1 , further comprising the winglet being devoid of any attached fairing component.4. The manufacture of claim 1 , further comprising the winglet being devoid of any attached splicing component.5. The manufacture of claim 1 , further comprising the winglet being devoid of any metallic components.6. The manufacture of claim 1 , further comprising an outboard portion of: the root region claim 1 , an upper blade of the winglet claim 1 , and a lower blade of the winglet claim 1 , that each comprise a first ply-set of the three ply-sets.7. The manufacture of claim 1 , further comprising an inboard portion of an upper blade of the winglet and an upper skin of the root region that each comprise a second ply-set of the three ply-sets.8. The manufacture of claim 1 , further comprising an inboard portion of a lower upper blade of the winglet and a lower skin of the root region that each comprise a third ply-set of the three ply-sets.9. The manufacture of claim 6 , further comprising a first ply-set of the three ply-sets ...

Wing tip device

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device.

Wing Tip With Winglet And Ventral Fin

An airplane including a wing and a wing tip attached to an end of the wing. The wing has a wing leading edge and a wing trailing edge in a wing chord plane. The wing tip includes a winglet and a ventral fin. The winglet has a winglet leading edge continuously transitioning from the wing leading edge, and a winglet trailing edge continuously transitioning from the wing trailing edge. The winglet leading edge may be swept rearward. The winglet includes an adapter section attached to the end of the wing, a transition section attached to the adapter section, a blade section attached to the transition section, the blade section extending above the wing chord plane, and a first tip section attached to the blade section. The ventral fin may be coupled to the winglet at an attachment location adjacent the transition section, and extends below the wing chord plane.

Wing Tip With Optimum Loading

A wing tip designed for attachment to a winglet of an aircraft, the winglet coupled to a wing of the aircraft and having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle. 1. A wing tip designed for attachment to a winglet of an aircraft , the winglet coupled to a wing of the aircraft and having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing , the wing tip comprising:a curved leading edge from the winglet leading edge to a leading end point;a curved trailing edge from a winglet trailing edge to a trailing end point; andan end segment connecting the leading end point and the trailing end point, the end segment swept back from the trailing end point to the leading end point at an end segment angle.2. The wing tip according to claim 1 , wherein the end segment angle is approximate to a sweep angle of the wing trailing edge.3. The wing tip according to claim 1 , wherein the curved leading edge defines a first parabolic line claim 1 , the first parabolic line approaching a freestream direction at the leading end point.5. The wing tip according to claim 3 , wherein the curved trailing edge defines a second parabolic line claim 3 , the second parabolic line approaching the freestream direction at the trailing end point.7. The wing tip according to claim 1 , wherein the curved leading edge defines a first elliptic line claim 1 , the first elliptic line approaching a freestream direction at the leading end point.9. The wing tip according to claim 7 , wherein the curved trailing edge ...

Aircraft with C-Shaped Carrier Surfaces and Movable Top Surfaces

An aircraft with C-shaped carrier surfaces wherein an axis of rotation of top surfaces is arranged in the respective aerodynamic center of the top surfaces, furthermore that each top surface can be adjusted by an adjustment device that can be controlled by a control device, wherein an angle of attack of the top surfaces can be adjusted that is optimal for a minimal induced resistance based on flight state parameters. This arrangement minimizes the adjusting moment during the adjusting of the top surfaces and is independent of the angle of attack of the top surface. 1. An aircraft with C-shaped carriers comprising a lower main carrier surface , a winglet surface extending upward on its end , and on the end of which winglet surface an inwardly extending top surface is fastened , wherein an axis of rotation of the top surfaces is arranged in the respective aerodynamic center of the top surfaces , furthermore , that each top surface is adjustable by an adjustment device , wherein the two adjustment devices are controllable in the same manner by a control device , and wherein an angle of attack of the top surfaces is adjustable which is optimal for a minimal induced resistance.2. The aircraft according to claim 1 , wherein the adjustment device is constructed as a redundantly operating claim 1 , double spindle drive.3. The aircraft according to claim 1 , wherein the adjustment device is hydraulically constructed.4. The aircraft according to claim 1 , wherein each adjustment device is constructed from a combination of a spindle drive for slow adjusting movements and of a hydraulic cylinder for rapid adjusting movements.5. The aircraft according to claim 4 , wherein the control device is constructed to individually control the two adjustment devices claim 4 , and additional adjusting signals for the two top surfaces for the controlling of the aircraft are enabled to be inputted.6. The aircraft according to claim 5 , wherein the control device is constructed in such a ...

WINGLET SYSTEM

A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The upper winglet root chord and the lower winglet root chord may each have a length of no greater than 100 percent of the wing tip chord. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. 1. A winglet system , comprising:an upper winglet and a lower winglet each having a root chord and being mounted to a wing tip of a wing, the wing tip having a wing tip chord;the upper winglet root chord and the lower winglet root chord each having a length of no greater than 100 percent of the wing tip chord;the lower winglet having a static position when the wing is subject to an on-ground static loading; andthe lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.2. The winglet system of claim 1 , wherein:the upper winglet root chord and the lower winglet root chord each have a length of at least approximately 50 percent of the wing tip chord.3. The winglet system of claim 1 , wherein:the upper winglet root chord and the lower winglet root chord each have a length of from approximately 60 to 100 percent of a length of the wing tip chord.4. The winglet system of claim 1 , wherein:at least one of the upper winglet and lower ...

WING TIP DEVICE ATTACHMENT APPARATUS AND METHOD

A wing tip device for attachment to a wing tip of a powered aircraft including: a first mounting formation, a second mounting formation spaced apart in a spanwise direction relative to the first mounting formation, a third mounting formation spaced apart in a chordwise direction relative to the first and second mounting formations, wherein each of the first, second and third mounting formations are configured for attachment to at least one of a wing spar and a wing rib, and, at least one of the mounting formations is configured to permit movement of a portion of the wing tip device in the spanwise direction relative to a portion of the wing tip. 1. A wing tip device for attachment to a wing tip of a powered aircraft , the wing tip device comprising:a first mounting formation,a second mounting formation spaced apart in a spanwise direction relative to the first mounting formation,a third mounting formation spaced apart in a chordwise direction relative to the first and second mounting formations,wherein each of the first, second and third mounting formations are configured for attachment to at least one of a wing spar and a wing rib, and,at least one of the mounting formations is configured to permit movement of a portion of the wing tip device in the spanwise direction relative to a portion of the wing tip.2. The wing tip device according to wherein the wing tip device comprises a first load-bearing structure that extends from the wing tip device into the wing tip and the first load-bearing structure comprises the first mounting formation.3. The wing tip device according to wherein the first load-bearing structure comprises the second mounting formation.4. The wing tip device according to wherein the first load-bearing structure comprises a beam.5. The wing tip device according to wherein the wing tip device comprises a second load-bearing structure that comprises the third mounting formation.6. The wing tip device according to wherein the second load-bearing ...

BRAIDED COMPOSITE SPAR

A braided composite spar or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar or preform has a centre line which extends lengthwise from a root to a tip, and at least part of the centre line follows a curved path which does not lie in a single plane. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. 1. A braided composite spar or preform for a braided composite spar , comprising a plurality of tubular plies of braided fibres , wherein the spar or preform has a centre line which extends lengthwise from a root to a tip , and at least part of the centre line follows a curved path which does not lie in a single plane.2. The spar or preform of wherein the curved path lies within a tapered portion of the spar or preform in which each ply has a height which reduces and a width which increases as it extends toward the tip.3. The spar or preform of claim 1 , wherein the spar or preform has a tapered portion in which each ply has a height which reduces and a width which increases as it extends toward the tip.4. The spar or preform of wherein each ply in the tapered portion has a circumference which reduces as it extends toward the tip.5. The spar or preform of claim 1 , wherein the spar or preform is a composite spar claim 1 , and the tubular plies of braided fibres are impregnated with a matrix.6. A winglet comprising a composite spar according to claim 1 , wherein the composite spar comprises forward and aft webs joined by upper and lower caps claim 1 , and the winglet comprises an upper skin joined to the upper cap of the composite spar and a lower skin joined to the lower cap of the composite spar.7. ...

BRAIDED COMPOSITE SPAR

A braided composite spar or preform for a braided composite spar, comprising a plurality of tubular plies of braided fibres, wherein the spar or preform extends lengthwise from a root to a tip, and the spar or preform has a tapered portion in which each ply has a height which reduces and a width which increases as it extends toward the tip. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. 1. A braided composite spar or preform for a braided composite spar , comprising a plurality of tubular plies of braided fibres , wherein the spar or preform extends lengthwise from a root to a tip , and the spar or preform has a tapered portion in which each ply has a height which reduces and a width which increases as it extends toward the tip.2. The spar or preform of wherein each ply in the tapered portion has a circumference which reduces as it extends toward the tip.3. The spar of preform of claim 2 , wherein each ply in the tapered portion has a circumference which reduces continuously as it extends toward the tip.4. The spar of preform of claim 1 , wherein each ply in the tapered portion comprises forward and aft webs joined by upper and lower caps claim 1 , and wherein for each ply in the tapered portion a height of the webs reduces and a width of the caps increases as the ply extends toward the tip.5. The spar of preform of claim 1 , wherein each ply in the tapered portion has a height which reduces continuously as it extends toward the tip.6. The spar of preform of claim 1 , wherein each ply in the tapered portion has a width which increases continuously as it extends toward the tip.7. A winglet comprising a composite spar according to claim 1 , wherein the ...

BRAIDED COMPOSITE SPAR

A braided composite spar or preform for a braided composite spar with a plurality of tubular plies of braided fibres. Each ply has a first set of fibres which wind in a clockwise direction in a first series of turns with a pitch between each adjacent pair of turns, and a second set of fibres which wind in an anti-clockwise direction in a second series of turns with a pitch between each adjacent pair of turns. The first and second sets of fibres in each ply are intertwined to form a braided structure. The spar or preform extends lengthwise from a root to a tip and has a tapered portion which tapers inwardly towards the tip. Each ply has a circumference in the tapered portion which reduces as it tapers inwardly. For at least one of the plies the pitches of the first and second sets of fibres increase continuously as the ply tapers inwardly in the tapered portion. The spar or preform can be used to provide a tubular main spar for a winglet. The winglet also has a front spar with a front spar web, an upper front spar cap, and a lower front spar cap. An upper skin of the winglet is joined to the braided spar and the upper front spar cap. A lower skin of the winglet is joined to the braided spar and the lower front spar cap. 1. A braided composite spar or preform for a braided composite spar , comprising a plurality of tubular plies of braided fibres , each ply comprises a first set of fibres which wind in a clockwise direction in a first series of turns with a pitch between each adjacent pair of turns , and a second set of fibres which wind in an anti-clockwise direction in a second series of turns with a pitch between each adjacent pair of turns , the first and second sets of fibres in each ply being intertwined to form a braided structure; wherein the spar or preform extends lengthwise from a root to a tip , the spar or preform has a tapered portion which tapers inwardly towards the tip , each ply has a circumference in the tapered portion which reduces as it tapers ...

WINGLET

A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web, an upper front spar cap, and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap. The winglet is manufactured by co-curing the upper skin to the upper main spar cap and the upper front spar cap; and co-curing the lower skin to the lower main spar cap and the lower front spar cap. 1. A winglet comprising a tubular main spar with forward and aft main spar webs joined by upper and lower main spar caps; a front spar with a front spar web , an upper front spar cap , and a lower front spar cap; an upper skin joined to the upper main spar cap and the upper front spar cap; and a lower skin joined to the lower main spar cap and the lower front spar cap.2. The winglet of wherein the upper front spar cap extends forwards away from the main spar claim 1 , and the lower front spar cap extends forwards away from the main spar.3. The winglet of wherein the main spar has a tapered portion in which a height of the main spar reduces and a fore-and-aft width of the main spar increases as it extends toward a tip of the spar4. The winglet of wherein the main spar has a centre line which extends lengthwise from a root of the winglet to a tip of the winglet claim 1 , and at least part of the centre line follows a curved path.5. The winglet of wherein the curved path does not lie in a single plane so that a cant angle and a sweep angle of the main spar both change continuously along the curved path.6. The winglet of wherein the main spar comprises a plurality of tubular plies of braided fibres impregnated with a matrix.7. The winglet of wherein the front spar is tubular with forward and aft front spar webs joined by the upper and lower front spar caps.8. The winglet of wherein the upper skin is bonded to the ...

RETROFIT FLIGHT CONTROL SURFACE

A method of retrofitting a wing of a fixed wing aircraft is disclosed including the steps of providing an existing aircraft wing with a main fixed wing portion, and the main fixed wing portion having a tip end and an existing movable flight control surface connected adjacent the tip end. The existing movable flight control surface is then removed from the main fixed wing portion, and a wing tip device and movable flight control surface are selected as a pair to replace the existing movable flight control surface, with the selected movable flight control surface having an aerodynamic surface of different shape to the shape of the flight control surface removed from the wing. The selected wing tip device and movable flight control surface are then fitted to the main fixed wing portion. 1. An aircraft wing having a root end , a tip end , a span extending between the root end and the tip end , a leading edge , a trailing edge and a chord extending between the leading edge and the trailing edge , and comprising:a main fixed wing portion having an inboard portion adjacent the root end, and an outboard portion adjacent the tip end;a wing tip device attached to the tip end of the wing; anda movable flight control surface connected at the outboard portion of the main fixed wing portion and having a leading edge, a trailing edge and a chord extending between the leading edge and the trailing edge,wherein a ratio of the local chord length of the movable flight control surface to the local chord length of the wing varies in the spanwise direction.2. An aircraft wing according to claim 1 , wherein the ratio of the local chord length of the movable flight control surface to the local chord length of the wing increases or decreases in the spanwise direction.3. An aircraft wing according to claim 1 , wherein the wing tip device is blended into the tip end of the main wing portion.4. An aircraft wing according to claim 1 , wherein the control surface is an aileron claim 1 , flaperon ...

Variable Geometry Wingtip

A variable geometry wingtip is comprised of two deformable yet relatively stiff airfoils ( 6, 7 ) that work in compression and tension against each other to change shape. There is only one moving part in the assembly ( 5 ) with no internal mechanisms to facilitate morphing. The wingtip ( 5 ) consists of a lower airfoil ( 7 ) and an upper airfoil. ( 6 ) The base of the lower airfoil ( 8 ) is mounted horizontally to an under surface ( 4 ) of an outboard end ( 2 ) of a wing. ( 1 ) The upper airfoil ( 6 ) has a portion ( 9 ) which is allowed to retract and extend from an upper surface ( 3 ) of the outboard end ( 2 ) of the wing. ( 1 ) A single projecting wingtip ( 11 ) is formed at an intersection ( 10 ) of the lower and upper airfoils. ( 6, 7 )

AIRCRAFT WING HAVING CONTINUOUSLY ROTATING WING TIPS

The present invention relates to a wing for an aircraft. The wing includes a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft. The wing also includes a wing tip having a proximal end and a distal end, the wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational centre with respect to the main wing section. 1. A wing for an aircraft comprising:a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft; andat least one wing tip having a proximal end and a distal end, the at least one wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational centre with respect to the main wing section.2. The wing according to claim 1 , wherein a total surface area of the wing tip is between 2% to 20% of a total surface area of the aircraft wing.3. The wing according to claim 1 , wherein a thickness of the wing tip is between 6% to 20% of a median chord length of the wing tip.4. The wing according claim 1 , wherein the wing tip rotational centre is arranged proximal to a mean lift line of the main wing section.5. The wing according to claim 4 , wherein the wing tip rotational centre and the mean lift line of the main wing section are coaxially aligned.6. The wing according to claim 1 , wherein the main wing section comprises a static wing or fixed wing.7. The wing according to claim 1 , further comprising a locking mechanism operable to fix the wing tip to the main wing section in a locked position preventing rotation of the wing tip claim 1 , and operable to release the wing tip from the locked position where the wing tip is free to rotate about the wing tip ...

Wingtip Control System

A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip. 1. A wingtip control system comprising:a switch system for a flight deck of an aircraft, wherein the switch system is configured to be placed into an armed state and generate an armed signal; anda controller in communication with the switch system, wherein the controller is configured to receive the armed signal from the switch system; visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft; and generate a movement command to move the wingtip.2. The wingtip control system of claim 1 , wherein the switch system is configured to be placed into the armed state prior to at least one of takeoff or landing of the aircraft.3. The wingtip control system of claim 1 , wherein the switch system comprises a first switch and a second switch claim 1 , wherein the first switch is configured to be placed into the armed state and the second switch is configured to visually indicate the desired position for the wingtip of the aircraft in response to the event.4. The wingtip control system of further comprising:a first visual indication associated with the first switch and configured to indicate the armed state of the first switch; anda second visual indication associated with the second switch and configured to indicate the desired position of the wingtip of the aircraft to be sent to the ...

ULTRA-QUIET PROPELLER SYSTEM

A propeller system combines innovative strategies to create a new methodology to reduce propeller or rotor noise. The propeller is specifically aimed for ultra-quiet electrically powered aircraft for use in high proximity aviation, but its low-noise advantages will extend to other purposes. The propeller blade includes geometries, along with size and operational limitations that minimize rotational and vortex noise, vibration and span-wise air flow on the blade. To further reduce noise, the propeller provides greater relative thrust on the inboard portions of the blade than do conventional propellers and provides less than conventional relative thrust including negative thrust at the outermost portions of the blade. The propeller blade includes stepped changes in local blade stiffness at calculated intervals that can reduce resonant blade vibrations and their resultant noise. This ultra-quiet propeller design can also be used for quieting hovercraft, drones, surveillance aircraft, indoor fans, wind tunnels and other applications. 1. An aerodynamic propeller system comprised of:a hub; a) a leading and trailing edge; and', 'b) a chord-line having a chord length, wherein the chord-line is the shortest straight-line distance from the leading edge to the training edge; and', 'c) a tip; and', 'd) a root at the opposite end of the propeller blade from the tip and wherein the root is coupled to a central hub; and', 'e) a neck that is a portion of said blade adjacent the central hub; and', "f) a thrust axis that is at the center of the propeller hub and is perpendicular to the propeller disc's plane of rotation; and", 'g) a total blade radius that is the distance from the tip to the center of the hub, wherein said center is configured on the thrust axis of the propeller; and', 'h) a blade axis that is the imaginary straight line perpendicular to the thrust axis and drawn radially outward from the axial center of the blade root; and', 'i) a blade sweep angle that is no more ...

Aircraft with a wing tip comprising a fuel pod

An aircraft is disclosed having a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations.

AIRCRAFT WING FOR RECEIVING A PLURALITY OF DIFFERENT WING TIP DEVICES

An aircraft wing, the wing having a connection interface at the tip of the wing, and the wing being configurable between a first configuration in which a first wing tip device is connected to the connection interface, and a second configuration in which a second wing tip device is connected to the connection interface to replace the first wing tip device. The design of the wing is such that it is designed for performance in both the first and the second configurations. 1. A method of designing a wing for an aircraft , the wing having a connection interface at its tip for receiving a plurality of different wing tip devices , and the wing being configurable between a first configuration in which a first wing tip device is connected to the connection interface , and a second configuration in which the first wing tip device is replaced by a second wing tip device connected to the connection interface , 'designing the wing for performance in both the first configuration and the second configuration.', 'wherein the method comprises the step of'}2. A method according to claim 1 , wherein the step of designing the wing comprises designing for the aircraft flying a first mission profile in the first configuration claim 1 , and for the aircraft flying a second mission profile in the second configuration.3. An aircraft wing claim 1 , the wing having a connection interface at the tip of the wing claim 1 , and the wing being configurable between a first configuration in which a first wing tip device is connected to the connection interface claim 1 , and a second configuration in which a second wing tip device is connected to the connection interface to replace the first wing tip device claim 1 ,wherein the wing has been designed for performance in both the first and the second configurations.4. An aircraft wing according to claim 3 , wherein the wing is designed for use in the first configuration on an aircraft flying a first mission profile claim 3 , and for use in the second ...

AIRCRAFT WITH A WING TIP COMPRISING A FUEL POD

An aircraft comprising a wing, the wing having a connection interface at the tip of the wing, and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface, and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip. The second wing tip comprises a fuel pod for carrying additional fuel, and a wing tip device for improving aerodynamic efficiency. The wing may be designed for performance in both configurations. 1. An aircraft comprising an aircraft wing , the wing having a connection interface at the tip of the wing , and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface , and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip ,wherein the second wing tip comprises a fuel pod andwherein the wing has been designed for performance in both the first and the second configurations.2. An aircraft according to claim 1 , wherein the second wing tip also comprises a wing tip device for improving aerodynamic efficiency of the aircraft.3. An aircraft comprising a wing claim 1 , the wing having a connection interface at the tip of the wing claim 1 , and the wing being interchangeable between a first configuration in which a first wing tip is connected to the connection interface claim 1 , and a second configuration in which a second wing tip is connected to the connection interface to replace the first wing tip claim 1 , wherein the second wing tip comprises a fuel pod for carrying fuel and a wing tip device for improving aerodynamic efficiency.4. An aircraft according to wherein the centre of mass of the fuel pod is positioned along the axis of twist of the wing claim 2 , such that when the wing changes from the first to the second configuration claim 2 , the twist of the wing is not altered claim 2 ...

WING TIP DEVICE FOR AN AIRCRAFT WING

A wing tip device for an aircraft wing may include an upper winglet and a lower element. The upper winglet may extend upwardly from an aircraft wing. The lower element may extend downwardly from the upper winglet and may form a closed loop below the wing. The closed loop may have a hollow interior. 1. A wing tip device for an aircraft wing , comprising:an upper winglet configured to extend upwardly from an aircraft wing; anda lower element extending downwardly from the upper winglet and configured to form a closed loop below the wing, the closed loop having a hollow interior.2. The wing tip device of claim 1 , wherein:the lower element comprises a lower arc forming the closed loop with a wing lower surface.3. The wing tip device of claim 1 , wherein:the lower element comprises a lower loop mounted to a wing lower surface.4. The wing tip device of claim 1 , wherein:the upper winglet and the lower element are formed as a unitary structure.5. The wing tip device of claim 1 , wherein:the lower element has an outboard portion that is tangent to the upper winglet.6. The wing tip device of claim 1 , wherein:the upper winglet and the lower element are removably attachable to the wing at a wing tip joint.7. The wing tip device of claim 6 , wherein:the lower element has an outboard end and an inboard end, the outboard end extending downwardly from the upper winglet; andthe wing tip joint comprising an outboard end attachment of the upper winglet to the wing tip, and an inboard end attachment of the inboard end of the lower element to the wing at a location inboard of the wing tip.8. The wing tip device of claim 6 , further including:a tip extension extending between the upper winglet and an inboard end of the lower element; andthe wing tip joint being located inboard of the inboard end.9. The wing tip device of claim 1 , wherein:the closed loop has a triangular shape, a rounded shape, a parabolic shape, a semi-circular shape, or a trapezoidal shape.10. The wing tip device of ...

Solar powered airplane

A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

Airflow Interrupting Devices

A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered. 1. A boundary layer interrupting device comprising:a first edge fixedly coupleable to a leading edge of a wingtip device; anda second edge comprising a flow disruptor configured to alleviate a load on the wingtip device.2. The device of claim 1 , wherein the flow disruptor comprises a sharp edge extending into a stagnation region of the wingtip device at a first angle of attack of the wingtip device and protrudes from the stagnation region at a second angle of attack of the wingtip device.3. The device of claim 1 , wherein the flow disruptor comprises an edge extending from a stagnation region of the wingtip device at a threshold angle of attack.4. The device of claim 3 , wherein the edge comprises an edge with a small effective radius in comparison to at least one of a length of the device claim 3 , a width of the device claim 3 , or a height of the device.5. The device of claim 1 , wherein the wingtip device is a winglet claim 1 , a spiroid claim 1 , a split winglet claim 1 , a fence claim 1 , an endplate claim 1 , or a combination thereof.6. The device of claim 1 , wherein the wingtip device has a substantially vertical portion comprising the leading edge.7. The device of claim 6 , wherein the first edge is positionable to a portion of the leading edge substantially closer to an end of the wingtip device distal to a region of the wingtip device that ...

Latch Pin Assembly

A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit retraction of the latch pin to the unlatched position. 1. A latch pin assembly for use with a hydraulic fluid source , the latch pin assembly comprising:a latch pin defining an extend chamber and a retract chamber, the latch pin including a latch surface;a latching hydraulic line fluidly communicating between the extend chamber and the hydraulic fluid source;an unlatching hydraulic line fluidly communicating between the retract chamber and the hydraulic fluid source;a mechanical lock engaging the latch surface of the latch pin when in a lock position to mechanically lock the latch pin in a latched position; anda hydraulic lock disposed in the latching hydraulic line and having an initial state, in which fluid flow is blocked from exiting the extend chamber through the latching hydraulic line, and an open state, in which fluid flow is permitted from the extend chamber through the latching hydraulic line.2. The latch pin assembly of claim 1 , in which the mechanical lock comprises:a lock cam movable between a lock position, in which the lock cam engages the latch surface of the latch pin, and an unlock position, in which the lock cam is disengaged from the latch surface of ...

Wingtip Device

A wingtip device may be attached to a baseline wing of an aircraft. The wingtip device may comprise a vertical portion coupled to the baseline wing. The vertical portion may comprise a leading edge and trailing edge. The leading edge and trailing edge may be nonlinear shapes. For example, compound curves, smooth continuous higher order polynomials, or combinations thereof. The leading edge and trailing edge may be shaped as to locate the wingtip device further aft than a conventional winglet design. 1. A winglet fixedly attachable to a baseline wing of an aircraft comprising:a vertical portion having a leading edge and a trailing edge, the leading edge having a first nonlinear shape and the trailing edge having a second nonlinear shape.2. The winglet of claim 1 , the first nonlinear shape defined by a first compound curve.3. The winglet of claim 1 , the second nonlinear shape defined by a second compound curve.4. The winglet of claim 1 , the first nonlinear shape defined by a first smooth continuous higher order function.5. The winglet of claim 1 , the second nonlinear shape defined by a second smooth continuous higher order function.6. The winglet of claim 1 , the first nonlinear shape defined by one or more of a smooth continuous 4th order function claim 1 , a smooth continuous 5th order function claim 1 , a smooth continuous 6th order function claim 1 , a smooth continuous 7th order function.7. The winglet of claim 1 , the second nonlinear shape defined by one or more of a smooth continuous 4th order function claim 1 , a smooth continuous 5th order function claim 1 , a smooth continuous 6th order function claim 1 , a smooth continuous 7th order function.8. The winglet of claim 1 , a portion of the leading edge of the winglet extending past a portion of a trailing edge of the baseline wing.9. The winglet of claim 8 , the portion of the leading edge comprising greater than one third of the winglet length in a direction perpendicular to a free stream direction of ...

AIRCRAFT BODY AND METHOD OF MAKING THE SAME

An aircraft body and a method of making an aircraft body are provided. In one embodiment, an aircraft body may be molded from a single layer of carbon fiber stock, producing curved sections of single layer molded carbon fiber by molding pliable carbon fiber stock, and heat curing the carbon fiber stock to form a rigid, molded wing section. 1. An aircraft body for flight comprising:a planar fuselage section comprising: a left side, a right side, a nose end, and a tail end;a left-wing section; anda right-wing section;wherein each wing section comprises: a connection edge configured to attach to the fuselage section, a nose end, a tail end, an upper surface, a lower surface, a tip, a leading edge, and a trailing edge, the wing sections configured to create an aerodynamic force in response to an airflow acting on the surfaces of the wing sections during flight; andwherein the left-wing section connection edge is configured to attach to the left side of the fuselage section, and the right-wing section connection edge is configured to attach to the right side of the fuselage section.2. The aircraft body of claim 1 , wherein all of the fuselage section is configured to be positioned below the top surface of the wing sections when the wings sections are connected to the fuselage section.3. The aircraft body of claim 1 , wherein the fuselage section has an upper rear portion configured to project upward from the wing sections and define a tail section of the aircraft body when the wing sections are connected to the fuselage section.4. The aircraft body of claim 1 , wherein the wing sections are adhesively attached to the fuselage section.5. The aircraft body of claim 1 , wherein each of the fuselage section and the wing sections is comprised of a single layer of carbon fiber panel claim 1 , the carbon fiber panel comprising a single layer of a carbon fiber cloth impregnated with a polymer.6. The aircraft body of claim 5 , wherein the polymer is a thermosetting polymer ...

CONTROLLABLE AIRFLOW MODIFICATION DEVICE PERIODIC LOAD CONTROL

An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency. 2. The aircraft of claim 1 , the CAMD comprising:a control surface disposed at a trailing edge of the baseline wing, such that the control surface is substantially parallel to the baseline wing; anda control system for controlling motion of the control surface based at least in part on in-flight load data.3. The aircraft of claim 2 , the control surface being configured for the aircraft based at least in part on historical flight data.4. The aircraft of claim 2 , the control system being communicatively coupled to one or more sensors located on the aircraft and configured to receive a signal from the sensor located on the aircraft.5. The aircraft of claim 4 , wherein the one or more sensors comprise a first sensor fore of a torsional axis of the wing extension and a second sensor aft of the torsional axis of the wing.6. The aircraft of claim 4 , wherein the one or more sensors comprise a rotational sensor.7. A wing extension fixedly attachable to a baseline wing of an aircraft claim 4 , the wing extension comprising:a horizontal portion that, when attached to the aircraft, is substantially parallel to the baseline wing of the aircraft, the horizontal portion being configured to fixedly attach to an outboard portion of the baseline wing of the aircraft; anda controllable airflow modification device (CAMD) coupled to the horizontal ...

Split Spiroid

The spiroid wing tip according to embodiments of the invention including a continuous segmental assembly having a closed loop frontal profile comprising a lower near vertical segment, a horizontal segment, a vertical segment, a second horizontal upper segment, and a near vertical segment. Accordingly to some embodiments of the invention, the spiroid profile is lowered with respect to the wing chord plane, such that a portion of the spiroid wing tip extends below the wing chord plane. 1. A spiroid wing tip designed for attachment to an aircraft wing having an aircraft wing leading edge and an aircraft wing trailing edge , the spiroid wing tip comprising: a beginning section including a leading edge generally continuous with the aircraft wing leading edge;', 'an ending section having a trailing edge swept rearward with respect to the aircraft wing trailing edge; and', 'an middle section between the beginning section and the ending section, the middle section including a portion extending above a chord plane of the aircraft wing., 'an enclosed loop, comprising2. The spiroid wing tip according to claim 1 , wherein the ending section trailing edge is generally continuous with the aircraft wing trailing edge.3. The spiroid wing tip according to claim 1 , wherein the intermediate section is swept rearward with respect to the aircraft wing trailing edge.4. The spiroid wing tip according to claim 1 , wherein the intermediate section includes a portion extending below the chord plane of the aircraft wing.5. The spiroid wing tip according to claim 1 , wherein the beginning section extends from the aircraft wing in the chord plane thereof.6. The spiroid wing tip according to claim 1 , wherein the beginning section tapers from a first chord length at an aircraft wing attachment section to a second chord length smaller than the first chord length remote from the aircraft wing attachment section.7. The spiroid wing tip according to claim 6 , wherein the intermediate section tapers ...

Lifting surfaces and associated method

An arrangement of lifting surfaces including a primary lifting surface having a flexural axis extending in the spanwise direction of the lifting surface, a root, and a tip. A first tip device is attached to the tip and has a first lifting surface. A second tip device is attached to the tip and has a second lifting surface. A control system is coupled to the first and second tip devices for moving the first and second lifting surfaces relative to the tip or for actively controlling circulation of the first and second lifting surfaces. The control system is operable to change a value of torque effective at the primary lifting surface about the flexural axis.

AIRCRAFT WINGLET DESIGN HAVING A COMPOUND CURVE PROFILE

An improved winglet design is presented for aircraft wherein the winglet configuration is well suited for aircraft wings having moderate to no aft swept, or wings having forward swept. The winglets () are located at the outer end of each wing () and curve upwardly as they extend outwardly from their intersection () with the wings (). The curvature profile () of the winglets () when viewed from the rear (or front) of the aircraft at least approximates a specified curve profile made up of more than one curved section, e.g. the winglet trailing edge profile () having a perpendicular projection onto a plane normal to the winglet inner or root chord (), said projection creating a winglet profile curve approximating a compound curve composed of two arc segment (). The two arc segments are tangent to each other at there point of connection () wherein the arc segment () at the lower portion of the winglet connects to the outer end of the wing () and is tangent with the wing's reference plane (). This lower arc segment () of the winglet profile connects to and is tangent with a second arc segment () forming the profile of the upper portion of the winglet (). A unique design specification for the plan form or developed shape of the winglet that is suitable for wings having nominal (less than 15 degrees) aft sweep, or have neutral, or forward sweep is also provided. 119-. (canceled)20. A wing for an aircraft , the wing comprising:an inner end, an outer end, an upper surface, a lower surface, a leading edge, and a trailing edge; anda winglet having an inner end, an outer end tip, an upper surface, a lower surface, a leading edge and a trailing edge;wherein the inner end of said winglet is connected to the outer end of said wing, and the upper and lower surfaces of the winglet and the leading and trailing edges of the winglet are continuations of the upper and lower surfaces of the wing and leading and trailing edges of the wing, respectively;wherein a curve defining the winglet ...

Aircraft with active support

An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.

VERTICAL TAKE-OFF AND LANDING (VTOL) AIRCRAFT WITH EXHAUST DEFLECTOR

A vertical take-off and landing (VTOL) aircraft is provided and includes a fuselage with first and second wings extending outwardly from opposite sides of the fuselage, nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight and exhaust deflectors disposed proximate to trailing ends of the nacelles. The exhaust deflectors are disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions. 1. A vertical take-off and landing (VTOL) aircraft , comprising:a fuselage with first and second wings extending outwardly from opposite sides of the fuselage;nacelles with proprotors respectively disposed on the first and second wings, the proprotors being rotatable to generate lift in vertical flight and thrust in horizontal flight; andexhaust deflectors disposed proximate to trailing ends of the nacelles, the exhaust deflectors being disposed to assume at least first, second and third configurations respectively associated with first, second and third flight conditions.2. The VTOL aircraft according to claim 1 , further comprising alighting elements disposed to support the aircraft in a ground operational condition.3. The VTOL aircraft according to claim 1 , wherein the first and second wings respectively comprise:first and second wing portions extending outwardly from the opposite sides of the fuselage; andfirst and second swept winglets extending outwardly from and forming obtuse angles with the first and second wing portions.4. The VTOL aircraft according to claim 1 , wherein the nacelles each comprise primary exhaust ducts at the trailing ends thereof and the exhaust deflectors comprise:hinges disposed at trailing edges of each of the primary exhaust ducts; andfirst and second deflector flaps coupled to each of the primary exhaust ducts via the hinges such that the first and second ...

Wing Tip Device

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device. 1. A wing tip device for fixing to the outboard end of a wing , the wing defining a wing plane , the wing tip device comprising:an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; anda lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection,wherein the upper wing-like element includes a substantially planar portion and a transition portion adapted to smoothly blend the outboard end of the wing into the substantially planar portion,wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the ...

WINGLET ATTACH FITTING AND METHOD FOR ATTACHING A SPLIT WINGLET TO A WING

A winglet attach fitting may include a wing attachment portion, an upper winglet attachment portion, and a lower winglet attachment portion. The upper winglet attachment portion may be coupled to the wing attachment portion and may be configured to support an upper winglet. The lower winglet attachment portion may be coupled to the wing attachment portion and may be configured to support a lower winglet. The wing attachment portion may be removably attachable to a wing tip using fasteners. 1. A winglet attach fitting for attaching a split winglet to a wing , comprising:a wing attachment portion;an upper winglet attachment portion coupled to the wing attachment portion and configured to support an upper winglet;a lower winglet attachment portion coupled to the wing attachment portion and configured to support a lower winglet; andthe wing attachment portion being removably attachable to a wing tip using fasteners.2. The winglet attach fitting of claim 1 , wherein:the fasteners are installed from an inboard side of the wing tip.3. The winglet attach fitting of claim 1 , wherein:the fasteners comprise tension fasteners.4. The winglet attach fitting of claim 3 , wherein:the wing attachment portion includes barrel nuts bores configured to contain barrel nuts; andthe tension fasteners being threadably engageable to the barrel nuts.5. The winglet attach fitting of claim 1 , wherein:the upper winglet is attached to the upper winglet attachment portion using shear fasteners; andthe lower winglet is attached to the lower winglet attachment portion using shear fasteners.6. The winglet attach fitting of claim 1 , further comprising:the upper winglet attachment portion and the lower winglet attachment portion being joined together at the wing attachment portion to form a unitary structure; andat least one of the upper winglet attachment portion and the lower winglet attachment portion being insertable into a respective one of the upper winglet and the lower winglet and being ...

Wing Tip Device

A wing tip device for fixing to the outboard end of a wing, the wing defining a wing plane, the wing tip device comprising: an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; and a lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like clement projecting downwardly from the intersection, wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection, and wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees. Also, a wing with the wing tip device; an aircraft with the wing; a method of fitting, or retro-fitting, the wing tip device to a wing; a method of modifying an existing wing tip device; and a method of operating a wing with the wing tip device. 1. A wing tip device for fixing to the outboard end of a wing , the wing defining a wing plane , the wing tip device comprising:an upper wing-like element projecting upwardly with respect to the wing plane and having a trailing edge; anda lower wing-like element fixed with respect to the upper wing-like element and having a root chord and a trailing edge, the lower wing-like element root chord intersecting with the upper wing-like element, and the lower wing-like element projecting downwardly from the intersection,wherein the upper wing-like element is larger than the lower wing-like element and the trailing edge of the lower wing-like element is adjacent the trailing edge of the upper wing-like element at the intersection,wherein an included angle between the upper and lower wing-like elements at the intersection is less than, or equal to, 160 degrees, andwherein the ...

WING LOAD ALLEVIATION METHODS AND APPARATUS

Wing load alleviation methods and apparatus are disclosed. An example winglet system for an aircraft includes a first winglet including a body portion having a leading edge and a trailing edge, a base portion to be coupled to an outboard end of a wing such that the body portion projects at an upward angle from the wing during all modes of airplane operation, a control surface coupled to the body portion proximate to the trailing edge, and at least one of a spoiler and an aileron coupled to the outboard end of the wing; and a processor to, in response to at least one input signal indicative of one of a subset of flight conditions, command actuated deflections of both the control surface of the first winglet and the at least one of the spoiler and the aileron to create an incremental pressure field in an airflow region inboard of the first winglet. 1. A winglet system for an aircraft , comprising: a body portion having a leading edge and a trailing edge;', 'a base portion to be coupled to an outboard end of a wing such that the body portion projects at an upward angle from the wing during all modes of airplane operation;, 'a first winglet, comprising 'a control surface coupled to the body portion proximate to the trailing edge;', 'and'}at least one of a spoiler and an aileron coupled to the outboard end of the wing; anda processor to, in response to at least one input signal indicative of one of a subset of flight conditions, command actuated deflections of both the control surface of the first winglet and the at least one of the spoiler and the aileron to create an incremental pressure field in an airflow region inboard of the first winglet.2. The winglet system of claim 1 , wherein the control surface is to be coupled to the body portion of the first winglet via at least one hinge and fitted with at least one actuator configured to deflect the control surface relative to the body portion.3. The winglet system of claim 2 , wherein the at least one actuator comprises ...

Latch Pin Assembly for Folding Wing Tip System

A folding wing tip system of an aircraft includes a latch pin actuator having a primary mechanical lock and a secondary hydraulic lock. The mechanical lock may include a lock cam movable between a lock position, in which the lock cam engages the latch pin, and an unlock position, in which the lock cam is disengaged from the latch pin, and a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position. The hydraulic lock may be disposed in an unlatching hydraulic line and has an initial state, in which fluid flow through the unlatching hydraulic line is blocked thereby to hold the latch pin in the latched position, and an open state, in which fluid flow through the unlatching hydraulic line is permitted thereby to permit refraction of the latch pin to the unlatched position. 1. A latch pin assembly provided on an aircraft having a hydraulic fluid source , the latch pin assembly comprising:a piston including a piston head;a latch pin enclosing the piston head and defining an inner chamber, the piston head separating the inner chamber into an extend chamber and a retract chamber, the latch pin including a latch surface;a latching hydraulic line fluidly communicating between the extend chamber and the hydraulic fluid source;an unlatching hydraulic line fluidly communicating between the retract chamber and the hydraulic fluid source;a lock cam movable between a lock position, in which the lock cam engages the latch surface of the latch pin, and an unlock position, in which the lock cam is disengaged from the latch surface of the latch pin;a first lock actuator mechanically coupled to the lock cam and configured to provide a bias force pushing the lock cam toward the lock position;a second lock including a hydraulic lock disposed in the unlatching hydraulic line and having an initial state, in which fluid flow through the unlatching hydraulic line is blocked, and an open state, in which fluid ...

SPLIT WINGLET

A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet is configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing. 1. A winglet system , comprising:an upper winglet and a lower winglet mounted to a wing;the lower winglet having a static position when the wing is subject to an on-ground static loading;the lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading; andthe lower winglet being configured to aeroelastically deflect upwardly under the approximate 1-g flight loading and further increase the effective span of the wing beyond the effective span increase that is caused by the upward deflection of the wing.2. The winglet system of claim 1 , wherein:the wing has a wing tip including a wing tip chord;the upper winglet and the lower winglet each having a root chord; andthe upper winglet root chord and the lower winglet root chord each have a length of at least approximately 50 percent of the wing tip chord.3. The winglet system of claim 2 , wherein: ...

Split Blended Winglet

A split winglet configured for attachment to a wing tip of a wing. The split winglet may include an upper winglet extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane. The upper winglet and the ventral fin may include tip configurations. At least one of the upper winglet tip configuration and the ventral fin tip configuration may be provided by a curved blade cap attached thereto. The curved blade cap may include a leading edge having a first curve with a first radius, and a trailing edge having a second curve with a second radius different from the first radius. The curved blade cap may also include a distal segment oblique to the first curve and the second curve. 1. A retrofitting for a winglet attached to a wing tip of a wing , comprising: a leading edge having a first curve with a first radius;', 'a trailing edge having a second curve with a second radius different from the first radius; and', 'a distal segment oblique to the first curve and the second curve, wherein the first curve terminates at a first end of the distal segment and the second curve terminates at a second end of the distal segment opposite the first end., 'a curved blade cap designed for attachment to the winglet, the curved blade cap comprising2. The retrofitting according to claim 1 , wherein the winglet comprises an upper winglet extending from the wing tip above a chord plane of the wing claim 1 , the upper winglet comprising an upper surface and a lower surface bounded by an upper winglet leading edge and an upper winglet trailing edge swept toward an airstream direction substantially parallel with a root chord.3. The retrofitting according to claim 2 , wherein the winglet further comprises a ventral fin projecting from the lower surface of the upper winglet below the chord plane claim 2 , the ventral fin comprising an upper surface and a lower surface bounded by a ventral fin leading edge and a ventral fin trailing edge swept ...

Split Blended Winglet

A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally upward projecting wing end to form a winglet assembly or may be separately attached onto an existing upwardly curved winglet. 1. A wing tip designed for attachment to an end of a wing of an aircraft , the wing having a leading edge and a trailing edge in a wing chord plane , the wing tip comprising: an adapter section designed for attachment to the wing end;', 'a blade section extending above the wing chord plane;', 'a transition section connecting the blade section to the adapter section; and', 'a tip section connected to the blade section opposite of the transition section, the tip section having a leading edge curved toward the freestream air direction; and, 'a winglet having a leading edge and a trailing edge designed to continuously transition from the leading edge and the trailing edge of the wing, the leading edge of the winglet swept rearward, the winglet comprisinga ventral fin coupled to the winglet at an attachment location adjacent the transition section, the ventral fin extending below the wing chord plane, the ventral fin comprising a tip section having a leading edge curved toward the freestream air direction.2. The wing tip according to claim 1 , wherein the ventral fin comprises a leading edge swept rearward claim 1 , the ventral fin leading edge including a curved portion and a linear portion claim 1 , the linear portion extending between the curved portion and the ventral fin tip section.3. The wing tip according to claim 1 , wherein the winglet adapter section and blade sections are generally planar claim 1 , and wherein the winglet transition section is generally curved.4. The wing tip according to claim 1 , wherein the ventral fin includes a trailing edge claim 1 , and wherein the ventral fin trailing edge is ...

CONTROLLABLE AIRFLOW MODIFICATION DEVICE PERIODIC LOAD CONTROL

An active wing extension includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes multiple controllable airflow modification devices coupled thereto. By virtue of having multiple controllable airflow modification devices, the wing extension is capable of adjusting control surfaces of the multiple controllable airflow modification devices in response to in-flight conditions, to reduce wing loads, improve wing fatigue characteristics, increase range, reduce torsional loads, alleviate flutter, and/or increase efficiency. 1. An aircraft comprising:a fuselage;a baseline wing, the baseline wing coupled to the fuselage at a first end of the baseline wing and having an aileron; and a horizontal portion coupled to a second end of the baseline wing, such that the horizontal portion is outboard of the baseline wing; and', 'a controllable airflow modification device (CAMD) directly coupled to the horizontal portion of the wing extension, the CAMD being configured to alleviate a torsional load on a wing and to be controllable independently of the aileron., 'a wing extension comprising2. The aircraft of claim 1 , the CAMD comprising:a control surface disposed at a trailing edge of the baseline wing, such that the control surface is substantially parallel to the baseline wing; anda control system for controlling motion of the control surface based at least in part on in-flight load data.3. The aircraft of claim 2 , the control surface being configured for the aircraft based at least in part on historical flight data.4. The aircraft of claim 2 , the control system being communicatively coupled to one or more sensors located on the aircraft and configured to receive a signal from the sensor located on the aircraft.5. The aircraft of claim 4 , wherein the one or more sensors comprise a first sensor fore of a torsional axis of the wing extension and a second sensor ...

WING TIP SHAPE FOR A WING, IN PARTICULAR OF AIRCRAFT

A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction. 1. A wing for an aircraft , wherein the wing comprises:a profile that extends in the direction of the span of the wing, and across said direction of the span of the wing from the wing leading edge to the wing trailing edge,wherein the profile is delimited by a first skin and a second skin, and a winglet, arranged on a wing end, wherein the winglet is substantially planar, and wherein a transition region is arranged between the wing and the winglet, andwherein the transition region extends from a connection on the wing to a connection on the winglet, wherein in the transition region the curvature of the local dihedral increases in the outboard direction.2. The wing of claim 1 , wherein in the transition region the curvature of the local dihedral increases over at least substantially 50% of a spanwise dimension of the transition region up to a maximum.3. The wing of claim 1 , wherein in the transition region the curvature of the local dihedral increases over at least substantially 75% of a spanwise dimension of the transition region up to a maximum.4. The wing of claim 1 , wherein in the transition region the curvature of the local dihedral increases over at least substantially 90% of a spanwise dimension of the transition region up to a maximum.5. The wing claim 2 , wherein in the transition ...

High Efficiency Aircraft Propulsion System

A fuel efficient aircraft propulsion system comprises a wingtip mounted ducted pusher fan with convergent backwash and a skewed conical engine nacelle. The system both mitigates wingtip vortex drag and converts a portion of vortex energy into propulsion force and lift force. The forward-tapering nacelle skews both downward and inward, so the lower nacelle surface is flush with the lower wing surface and the inboard nacelle surface does not alter flow over the upper wing surface. This firstly preserves lift at the outboard wing end. Secondly, air displacement by the nacelle accelerates flow only on the outboard and upper nacelle surfaces, and because the nacelle occupies the core of the nascent wingtip vortex, rotational air velocity is greatest on the upper nacelle surface. The resultant pressure drop on the upper nacelle surface contributes to aircraft lift. And because the nacelle surface tapers forward, this pressure drop does not exert backward-acting drag on the aircraft. Aft of the nacelle, the pusher fan hub surface conforms with the aft nacelle surface and tapers aft. Propulsion foils project from the forward portion of the pusher fan hub at an outward-aft angle, which directs convergent high pressure backwash flow along the aft tapering hub surface. This isolates aft-facing hub surfaces from drag-inducing vortex core pressure drop. Downstream fan backwash convergence then forms a central volume of high pressure flow where the low pressure trailing vortex core would otherwise develop. This is an efficient means to dissipate the cyclonic structure of the vortex, because vortex persistence requires low pressure core persistence. The direction of pusher fan rotation opposes the direction of wingtip vortex rotation as described in the prior art. This cross-flow interaction increases the effective power of the fan and also further counters vortex formation. An integral peripheral duct links the outer ends of the fan propulsion foils to provide thrust efficiency ...

WINGLET SYSTEM HAVING UPPER AND LOWER WINGLET

A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet may be substantially straight in the static position. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. 1. A winglet system , comprising:an upper winglet and a lower winglet mounted to a wing;the lower winglet having a static position when the wing is subject to an on-ground static loading, the lower winglet being substantially straight in the static position; andthe lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.2. The winglet system of claim 1 , wherein:the wing has a wing tip including a wing tip chord;the upper winglet and the lower winglet each having a root chord; andthe upper winglet root chord and the lower winglet root chord each have a length of at least approximately 50 percent of the wing tip chord.3. The winglet system of claim 2 , wherein:the upper winglet root chord and the lower winglet root chord each have a length of from approximately 60 to 100 percent of a length of the wing tip chord.4. The winglet system of claim 1 , wherein:at least one of the upper winglet and lower winglet has a leading edge root glove mounted at a juncture of the wing with the respective upper winglet and lower ...

CURVED WINGTIP FOR AIRCRAFT

Embodiments of the present disclosure include a curved planar wingtip for a straight wing and a curved planar wingtip for a swept wing of an aircraft. The curved planar wingtips include a member that extends from the end of the wing in a direction aft of the wing trailing edge while remaining substantially planar with the wing. The curved planar wingtips curve continuously from leading and trailing edges of the wing to form a tip located aft of the wing. Other embodiments of the curved planar wingtip are configured for a horizontal or vertical tail. Yet another embodiment includes a curved wingtip that extends aft of a trailing edge of the wing by a distance greater than the curved wingtip extends above a top surface of the wing. 1. A curved planar wingtip for a wing of an aircraft , comprising a continuously curving planar member that extends aft of a trailing edge of the wing and substantially in the same plane as the wing.2. The curved planar wingtip of claim 1 , wherein the continuously curving planar member forms a tip that extends aft of the trailing edge of the wing.3. The curved planar wingtip of claim 2 , wherein the tip is substantially pointed.4. The curved planar wingtip of claim 2 , wherein the tip extends aft of the trailing edge of the wing by a distance of at least ten percent of a tip chord of the wing.5. The curved planar wingtip of claim 1 , wherein a span of the wingtip is at least twice the distance that the tip extends aft of the trailing edge.6. The curved planar wingtip of claim 1 , further comprising an outboard edge and an inboard edge that each curve continuously with elliptical radii to provide in-plane sweep from an end of the wing.7. The curved planar wingtip of claim 6 , wherein the outboard edge follows a complex curve with a smaller radius of curvature near a leading edge and a gradually increasing radius of curvature as the leading edge curves aft towards the tip.8. The curved planar wingtip of claim 6 , wherein the inboard edge ...

ROTATABLE WING TIP JOINT AND METHOD OF MAKING SAME

A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base. 1. A joint for coupling a wing tip to a wing base , said joint comprising:a linking member that extends from a first end to a second end, said linking member first end is coupleable to the wing base, said linking member second end is coupleable to the wing tip, said linking member defines a first hinge line and a second hinge line, said first hinge line and said second hinge line are substantially parallel; andat least one actuator, a first end of each said at least one actuator is coupled to said linking member, a second end of each said at least one actuator is coupleable to one of the wing base and the wing tip, said at least one actuator is operable to rotate the wing tip about said first and second hinge lines between a first orientation and a second orientation relative to the wing base.2. The joint according to claim 1 , wherein said first and second hinge lines are offset from each other by a distance.3. The joint according to claim 1 , wherein said at least one actuator cooperates with said linking member such that the second orientation defines a rotation from the first orientation about said first and second hinge lines.4. The joint according to claim 1 , wherein:each said at least one actuator second end is linearly extendable ...

Split Blended Winglet

A split winglet configured for attachment to a wing tip of a wing. The split winglet may include an upper winglet extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane. The upper winglet and the ventral fin may include tip configurations. At least one of the upper winglet tip configuration and the ventral fin tip configuration may be provided by a curved blade cap attached thereto. The curved blade cap may include a leading edge having a first curve with a first radius, and a trailing edge having a second curve with a second radius different from the first radius. The curved blade cap may also include a distal segment oblique to the first curve and the second curve.

ARRANGEMENT FOR MOVING A WING TIP DEVICE BETWEEN A FLIGHT CONFIGURATION AND A GROUND CONFIGURATION

An aircraft comprises a wing, a wing tip device at the tip of the wing and an actuator. The actuator is arranged to effect movement of the wing tip device between a flight configuration for use during flight and a ground configuration in which the wing tip device is moved away from the flight configuration such that the span of the aircraft is reduced. The aircraft comprises a carriage guide, such as a rail, fixed relative to the wing, and a carriage arranged to move along the carriage guide as the wing tip device moves between the flight and ground configurations. The wing tip device is fixed relative to the carriage such that the path of the wing tip device, during movement of the wing tip device, between the flight and the ground configurations, is defined by the shape of the carriage guide. 1. An aircraft comprising a wing , a wing tip device at the tip of the wing and an actuator , the actuator being arranged to effect movement of the wing tip device between:(i) a flight configuration for use during flight and(ii) a ground configuration for use during ground-based operations, in which ground configuration the wing tip device is moved away from the flight configuration such that the span of the aircraft is reduced, a carriage guide, fixed relative to the wing,', 'a carriage arranged to move along the carriage guide as the wing tip device moves between the flight and ground configurations,', 'wherein the carriage carries the wing tip device and', 'the wing tip device is fixed relative to the carriage, such that the path of the wing tip device, during movement of the wing tip device, between the flight and the ground configurations, is defined by the shape of the carriage guide., 'characterised in that the aircraft comprises2. An aircraft according to claim 1 , wherein carriage guide is shaped such that the movement of the wing tip device between the flight and the ground configurations comprises both a rotational component of movement of the wing tip device claim ...

Split Winglet Lateral Control

A winglet includes a winglet body and a control body. The winglet body includes a first winglet surface arranged opposite a second winglet surface. The second winglet surface is joined to the first winglet surface to form front and trailing edges of the winglet body. The second winglet surface defines a control body seat. The control body is coupled to the winglet body to move between a stowed position seated in the control body seat and a deployed position rotated out of the control body seat. The control body includes a first control surface arranged to face toward the winglet body, a second control surface arranged opposite the first control surface to face away from the winglet body and joined to the first control surface to form a trailing edge of the control body and a control front connecting the first control surface and the second control surface. 1. A winglet comprising: a first winglet surface arranged to face away from an attached wing; and', 'a second winglet surface arranged opposite the first winglet surface to face toward the attached wing, the second winglet surface joined to the first winglet surface to form a front edge of the winglet body and a trailing edge of the winglet body, the second winglet surface defining a control body seat; and, 'a winglet body comprising a first control surface arranged to face toward the winglet body;', 'a second control surface arranged opposite the first control surface to face away from the winglet body and joined to the first control surface to form a trailing edge of the control body; and', 'a control front connecting the first control surface and the second control surface., 'a control body coupled to the winglet body to move between a stowed position seated in the control body seat and a deployed position rotated out of the control body seat, the control body comprising2. The winglet of claim 1 , further comprising a hinge mounted at a junction of the control front and the first control surface claim 1 , the ...

Split Blended Winglet

A split winglet configured for attachment to a wing of an airplane. The split winglet may include an upper winglet smoothly extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane from a lower surface of the upper winglet. The upper winglet may include a transition section which curves upward from the wing tip into a substantially planar section. Upper and lower surfaces of the upper winglet may be bounded by leading and trailing edges which are swept toward an airstream direction, parallel with the chord plane, and curve toward the airstream direction before terminating at a point distal of the wing tip. Similarly, upper and lower surfaces of the ventral fin may be bounded by leading and trailing edges which curve toward the airstream direction and terminate at a point distal of the wing tip. 1. A split winglet configured for attachment to a wing tip of an airplane , comprising:an upper winglet extending from the wing tip above a chord plane of the wing, the upper winglet comprising an upper surface and a lower surface bounded by a leading edge and a trailing edge, the leading edge and the trailing edge comprising substantially linear sections which are swept toward an airstream direction and then converging to an upper winglet tip configuration comprising a curving of the leading edge and the trailing edge toward the airstream direction to substantially a point distal of the wing tip, the airstream direction being substantially parallel with the chord plane; anda ventral fin projecting from the lower surface of the upper winglet, the ventral fin comprising an upper surface and a lower surface bounded by a leading edge and a trailing edge extending below the chord plane, the leading edge and the trailing edge comprising substantially linear sections which are swept toward the airstream direction and then converge to a ventral fin tip configuration comprising a curving of the leading edge and the trailing edge ...

ACTIVE FLOW CONTROL SYSTEMS AND METHODS FOR AIRCRAFT

Example active flow control systems and methods for aircraft are described herein. An example active flow control system includes a plurality of nozzles arranged in an array across a surface of an aircraft. The nozzles are oriented to eject air across the surface to reduce airflow separation. The active flow control system also includes an air source coupled to the nozzles and a controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface. 1. An active flow control system comprising:a plurality of nozzles arranged in an array across a surface of an aircraft, the nozzles oriented to eject air across the surface to reduce airflow separation;an air source coupled to the nozzles, anda controller to activate the nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a wave of air moving from outboard to inboard and then from inboard to outboard across the surface.2. The active flow control system of claim 1 , wherein the plurality of nozzles are a first plurality of nozzles and the wave of air is a first wave of air claim 1 , further including a second plurality of nozzles arranged in an array across the surface and disposed adjacent the first plurality of nozzles.3. The active flow control system of claim 2 , wherein the controller is to activate the second plurality of nozzles to eject air from the air source in sequence from outboard to inboard and then from inboard to outboard to create a second wave of air moving from outboard to inboard and then from inboard to outboard across the surface.4. The active flow control system of claim 3 , wherein the controller activates the first plurality of nozzles and the second plurality of nozzles such that the first and second waves of air move in a same direction inboard and ...

Adhesive Panels of Microvane Arrays for Reducing Effects of Wingtip Vortices

In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing. 1. A wing , comprising:a low pressure side and a high pressure side opposite the low pressure side, wherein the low pressure side and high pressure side are configured, when air flows over the wing, to generate a force on the high pressure side; and a first side coupled to the low pressure side of the wing;', 'a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in a plurality of arrays, the plurality of arrays operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing; and', 'one or more markings, each of the one or more markings indicating alignment of the drag reducing apparatus with respect to a feature of the wing., 'a drag reducing apparatus coupled to the low pressure side of the wing using an adhesive, the drag reducing apparatus comprising2. The wing of claim 1 , wherein the plurality of arrays are arranged such that centers of the generated vane vortices are different from centers of the wingtip vortex.3. A wing claim 1 , comprising:a low pressure side and a high pressure side opposite the low pressure side, wherein the low pressure side and high pressure side are configured, when air flows over the wing, to generate a force on the high pressure side; and a first side coupled to the low pressure side of the wing; ...

FLIGHT CONTROL METHODS FOR OPERATING CLOSE FORMATION FLIGHT

Embodiments of methods and apparatus for close formation flight are provided herein. In some embodiments, a method of operating aircraft for flight in close formation includes establishing a communication link between a first aircraft and a second aircraft, assigning to at least one of the first aircraft or the second aircraft, via the communication link, initial positions relative to one another in the close formation, providing flight control input for aligning the first and second aircraft in their respective initial positions, tracking, by at least one aircraft in the close formation, at least one vortex-generated by at least one other aircraft in the close formation, and based on the tracking, providing flight control input to adjust a relative position between the first aircraft and the second aircraft.

WINGTIP CONTROL SYSTEM

A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip. 120-. (canceled)21. An airfoil structure control system in communication with an airfoil structure movement system , the airfoil structure control system configured such that a combination , of a switch system and a visual indication on a flight deck interface , display a selected position for a airfoil structure and , based upon the display of the selected position , control and display an actual position of the airfoil structure.22. The airfoil structure control system of claim 21 , further comprising a switch configured for a manual override of an automated sequencing claim 21 , by the airfoil structure control system claim 21 , of the airfoil structure movement system.23. The airfoil structure control system of claim 21 , further comprising the manual override comprising an operation that disables an armed state of the airfoil structure control system.24. The airfoil structure control system of claim 21 , further configured to generate a movement command claim 21 , to move the airfoil structure claim 21 , to the airfoil structure movement system claim 21 , based upon reception by the airfoil structure control system of an activation via receipt of an armed signal followed by receipt of an indication of an occurrence of an event during operation of an aircraft that comprises the airfoil structure.25. The airfoil structure control system of claim 21 , further configured to ...

Adhesive Panels of Microvane Arrays for Reducing Effects of Wingtip Vortices

A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing. 120-. (canceled)21. A drag reducing apparatus configured to be coupled to an exterior surface of a vehicle , the drag reducing apparatus comprising a plurality of vortex generators arranged in an array configuration , the array configuration of vortex generators configured to generate a series of co-rotating vortices that serve to weaken a rotational strength of a vortex generated by the vehicle , wherein:a spacing of the array configuration of vortex generators is between 0.1 and 1 inch; andeach of the plurality of vortex generators is between 0.25 and 0.5 inches in height.22. The drag reducing apparatus of claim 21 , wherein the drag reducing apparatus is composed of aluminum claim 21 , titanium claim 21 , a polymer claim 21 , or a composite material.23. The drag reducing apparatus of claim 21 , wherein a shape of each of the plurality of vortex generators is selected from the group consisting of semi-spherical claim 21 , pyramid-shaped claim 21 , and cone shaped.24. The drag reducing apparatus of claim 21 , wherein the drag reducing apparatus is configured to be coupled to a flap of a wing of an aircraft.25. The drag reducing apparatus of claim 21 , wherein the drag reducing apparatus is configured to be coupled proximate a wingtip of the vehicle.26. The drag reducing apparatus of claim 21 , wherein the drag reducing apparatus is configured to be coupled to the exterior surface of the vehicle using an ...

Active winglet

An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

TAIL SITTER VEHICLE WITH AERIAL AND GROUND REFUELING SYSTEM

An aircraft is provided and includes a fuselage, first and second wings extending outwardly from opposite sides of the fuselage, proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations and a refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus. The refueling apparatus is coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations. 1. An aircraft , comprising:a fuselage;first and second wings extending outwardly from opposite sides of the fuselage;proprotors operably disposed on each of the first and second wings to drive vertical take-off and landing aircraft operations and horizontal flight aircraft operations; anda refueling system including at least one fuel tank disposed in at least one or more of the fuselage, the first wing or the second wing and a refueling apparatus, the refueling apparatus being coupled to the at least one fuel tank such that fuel is movable with respect to the at least one fuel tank during aircraft ground and aerial operations.2. The aircraft according to claim 1 , wherein each of the first and second wings comprises:a main wing;a winglet coupled to a distal end of the main wing; anda hinge by which the winglet is pivotable about the distal end of the main wing.3. The aircraft according to claim 1 , wherein the proprotors comprise foldable rotor blades.4. The aircraft according to claim 1 , further comprising alighting elements disposed at a trailing side of the first and second wings for aircraft support during the ground operations.5. The aircraft according to claim 1 , wherein the fuselage comprises:a wing section disposed along a plane of the first and second wings; anda bulged section disposed to extend away from the plane.6. The ...

NOISE ATTENUATION PANEL

A noise attenuation element can be arranged for connection to an air directing structure such as a wing flap. The element has a non-uniform lattice density across at least a portion of the body of the element. 135.-. (canceled)36. A noise attenuation element for connection to an air directing structure , the noise attenuation element comprising:a body which has a lattice structure, wherein the lattice structure has a non-uniform lattice density across at least a portion of the body.37. The noise attenuation element of claim 36 , wherein the body has at least two regions claim 36 , each region having a different lattice density and wherein the lattice density of a first region is greater than the lattice density of a second region.38. The noise attenuation element of claim 36 , wherein a transition region is provided between regions of the body with different lattice densities claim 36 , and wherein the lattice density of the body in the transition region increases from a first lattice density to a second lattice density.39. The noise attenuation element of claim 36 , wherein a first lattice density corresponds to the lattice density of a first region of the body and a second lattice density corresponds to the lattice density of a second region of the body claim 36 , and wherein the lattice density increases uniformly between the first and second lattice densities.40. The noise attenuation element of claim 39 , wherein the element further comprises couplings arranged to allow the element to be coupled to a structure and wherein the lattice density of the body adjacent to the coupling is greater than the lattice density remote from the coupling.41. The noise attenuation element of claim 36 , wherein the body of the element has a leading edge in a gas stream direction and a trailing edge in a gas stream direction and wherein the leading edge and trailing edges of the body are solid and the region of the body between the leading and trailing edge has a lattice structure ...

JOINT

A joint including first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing. 1. A joint comprising:first and second rib components,the first rib component having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; andthe second rib component having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface,wherein the abutment surfaces of the respective first and second rib components are abutting and joined with a tension joint, andwherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second rib components are interleaved and have one or more pins passing through the aligned lug holes.2. The joint according to claim 1 , wherein the lugs of the respective first or second rib components project beyond the abutment surfaces of the respective first or second rib components.3. The joint according to claim 1 , wherein the tension joint includes a plurality of tension bolts.4. The joint according to claim 3 , further comprising a nut associated with each tension bolt.5. The joint according to claim 1 , wherein the pinned lug joint comprises two or more groups of lugs on each side of the joint.6. The joint according to claim 5 , wherein the groups of lugs are spaced apart by a distance greater than a ...

Split Blended Winglet

A split winglet configured for attachment to a wing tip of a wing. The split winglet may include an upper winglet extending from the wing tip above a chord plane of the wing and a ventral fin projecting below the chord plane. The upper winglet and the ventral fin may include tip configurations. At least one of the upper winglet tip configuration and the ventral fin tip configuration may be provided by a curved blade cap attached thereto. The curved blade cap may include a leading edge having a first curve with a first radius, and a trailing edge having a second curve with a second radius different from the first radius. The curved blade cap may also include a distal segment oblique to the first curve and the second curve. 1. A method of retrofitting a winglet , the winglet including a winglet leading edge and a winglet trailing edge , the method comprising: a blade cap leading edge having a first curve with a first radius;', 'a blade cap trailing edge having a second curve with a second radius; and', 'a distal segment oblique to the first curve and the second curve, the first curve terminating at a first end of the distal segment and the second curve terminating at a second end of the distal segment opposite the first end; and, 'obtaining a curved blade cap, comprising aligning the blade cap leading edge with the winglet leading edge; and', 'aligning the blade cap trailing edge with the winglet trailing edge., 'fastening the curved blade cap to the winglet, comprising2. The method of retrofitting according to claim 1 , wherein the winglet extends from the wing tip above a chord plane of the wing claim 1 , the winglet comprising an upper surface and a lower surface bounded by the winglet leading edge and the winglet trailing edge swept toward an airstream direction substantially parallel with a root chord.3. The method of retrofitting according to claim 1 , wherein at least one of the first curve and the second curve is a compound curve comprising at least a first ...

A CURVED WINGLET

A winglet has an inner end and an outer The winglet has a varying radius of curvature (R) which: (i) decreases along the winglet over a first distance d (ii) remains constant over a second distance d and (iii) increases along the winglet over a third distance d. The sum of the first and third distances (dd) is greater than the second distance (d). The radius of curvature may vary according to the equation R=k/dn. The parameter n may be equal to 1, such that the curvature follows an Euler spiral. 1. An aircraft wing and a winglet on the tip thereof , the winglet comprising:an inner end and an outer end, andthe winglet having a varying radius of curvature (R) extending from the inner end to the outer end, and wherein the radius of curvature of the winglet:(i) decreases along the winglet over a first distance dl from the inner end to a first location along the winglet;{'b': '2', '(ii) remains constant over a second distance d from the first location to a second location along the winglet; and'}{'b': '3', '(iii) increases along the winglet over a third distance d from the second location to a third location along the winglet,'}{'b': 1', '3', '2, 'wherein the sum of the first and third distances (d+d) is greater than the second distance (d).'}2111. The aircraft wing and winglet according to claim 1 , wherein over the first distance d claim 1 , the radius of curvature varies according to an equation R=k/dn claim 1 , where k is a constant claim 1 , d is the distance along the winglet measured in an outward direction claim 1 , and n is greater than zero.3. The aircraft wing and winglet according to claim 2 , wherein the distance d is measured from an origin at the inner end of the winglet claim 2 , and the inner end of the winglet is substantially planar.4322. The aircraft wing and winglet according to claim 1 , wherein over the third distance d claim 1 , the radius of curvature varies according to an equation R=k/dn claim 1 , where k is a constant claim 1 , d is the ...

Winglet

A winglet for attachment to a wing portion of an aircraft including a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and includes at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. A portion of the winglet root that at least partially defines an upper or a lower side of the recess has at least one hole extending therethrough for receiving a fastener for fastening the winglet to the connector when the connector is located in the recess.

METHOD FOR ATTACHING A SPLIT WINGLET TO A WING

A method of securing a split winglet to a wing tip of an aircraft includes fastening an upper winglet to an upper winglet attachment portion of a wing attach fitting having a wing attachment portion. The method further includes fastening a lower winglet to a lower winglet attachment portion of the wing attach fitting. The method additionally includes fastening the wing attachment portion to the wing tip using tension fasteners installed from an inboard side of the wing tip to secure the split winglet to the wing. 1. A method of securing a split winglet to a wing tip , comprising the steps of:fastening an upper winglet to an upper winglet attachment portion of a winglet attach fitting having a wing attachment portion;fastening a lower winglet to a lower winglet attachment portion of the winglet attach fitting; andfastening the wing attachment portion to the wing tip using fasteners to secure the split winglet to the wing.2. The method of claim 1 , further comprising:installing the fasteners from an inboard side of the wing tip.3. The method of claim 1 , wherein the step of fastening the wing attachment portion to the wing tip using fasteners comprises:passing the fasteners into an interior of the wing;extending the fasteners through a wing tip rib; andthreadably engaging the fasteners into a fitting root end of the wing attachment portion.4. The method of claim 1 , further comprising:fastening the wing attachment portion to a wing tip rib of the wing tip with the upper winglet fastened to the upper winglet attachment portion and the lower winglet fastened to the lower winglet attachment portion.5. The method of claim 1 , further comprising:removing the fasteners securing the wing attachment portion to the wing tip; andremoving the wing attachment portion from the wing tip with at least one of the upper winglet and the lower winglet being attached to the wing attachment portion.6. The method of claim 1 , further comprising:removing a hinge pin attaching the upper ...

LOCK ACTUATION SYSTEM FOR AIRCRAFT

Described herein is a system that includes an actuator with a movable input, a first summing mechanism with an input, a first output, and a second output. The input of the first summing mechanism is movably driven by the movable input of the actuator and the first output of the first summing mechanism is movably coupled to a first actuatable element. The system also includes an end mechanism with an input and a first output. The input of the end mechanism is movably driven by the second output and the first output of the end mechanism is movably coupled to a second actuatable element. The system further includes a sensor that senses a position of the rotational input of the actuator. A status of the first and second actuatable elements is based on a sensed position of the movable input of the actuator. 1. A system , comprising:an actuator providing a movable input;a first summing mechanism with an input, a first output, and a second output, the input of the first summing mechanism being movably driven by the movable input of the actuator and the second output of the first summing mechanism being movably coupled to a first actuatable element;an end mechanism with an input and a first output, the input of the end mechanism being movably driven by the first output of the first summing mechanism and the first output of the end mechanism being movably coupled to a second actuatable element;a sensor that senses a position of the movable input of the actuator; anda controller that determines a status of the first and second actuatable elements based on a sensed position of the movable input of the actuator.2. The system of claim 1 , further comprising a second summing mechanism with an input movably driven by the first output of the first summing mechanism claim 1 , a second output coupled to a third actuatable element claim 1 , and a first output movably coupled to the input of the end mechanism claim 1 , the input of the end mechanism being movably driven by the first ...

BOUNDARY LAYER SUCTION DESIGN BY USING WINGTIP VORTEX FOR A LIFT-GENERATING BODY

A boundary layer suction design using wingtip vortex for a lift-generating body that has optimized aerodynamic performances. Holes or slots connected to the tip of the lift generating body via a plenum sucked a part of the boundary layer to delay flow transition or separation. Thus, with a more stable boundary layer, the lift is increased while the drag is reduced. Also, a valve is used to control the pressure in the plenum and optimized the suction mechanism. 1. An apparatus with a boundary layer suction design by using wingtip vortex for a lift-generating body , the apparatus comprising:A lift-generating body with a tip and one surface experiencing a higher pressure than another surface;A hole or slot placed on one of the surfaces of the lift-generating body;A plenum embedded in the lift-generating body and connecting the hole or slot to the tip of the lift generating body;An opening at the tip connecting a plenum the external fluid surrounding the lift-generating body.2. The boundary layer suction design by using wingtip vortex for a lift-generating body according to claim 1 , wherein multiple holes or slots are placed on the surface of the lift-generating body and are all connected to an opening at the tip of the lift-generating body via a plenum or different plenums.3. The boundary layer suction design by using wingtip vortex for a lift-generating body according to claim 1 , wherein a valve is placed at the tip of the lift-generating body and regulates the pressure inside a plenum embedded in the lift-generating body. A boundary layer surrounds any body in motion in a fluid. The viscous forces present at the surface of the body are at the origin of the boundary layer. The amount of form and skin friction drags are determined by the behavior of the boundary layer. The skin friction drag increases when there is a transition from a laminar to a turbulent boundary layer. The form drag augments when there is a flow separation with a reverse flow region in the ...

AIRCRAFT WING COMPRISING A CONTROLLABLE-ATTACK WING TIP

An aircraft wing, including a main part and a wing tip mounted mobile in attack relative to the main part. 1. An aircraft wing comprising:a main part,a wing tip mounted mobile in attack relative to the main part, anda junction device between the wing tip and the main part of the wing, the junction device being configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip, and to allow rotation of the wing tip relative to the main part about a second rotation axis enabling the wing tip to be folded to raise it.2. The aircraft wing as claimed in claim 1 , wherein the first rotation axis is substantially parallel to a spanwise direction of the wing or is oriented substantially along a transverse direction of the aircraft claim 1 , and wherein the second rotation axis is substantially parallel to a direction of flow of the airflow over the wing.3. The aircraft wing as claimed in claim 1 , wherein the wing tip is mounted mobile in attack relative to the main part in accordance with a limited amplitude.4. The aircraft wing as claimed in claim 1 , wherein said amplitude is limited to a range of angles between 15 and −15°.5. The aircraft wing as claimed in claim 1 , wherein said amplitude is limited to a range of angles between 15° and −90°.6. The aircraft wing as claimed in claim 1 , wherein the junction device includes a first actuator and a second actuator respectively enabling control in attack and control in folding.7. An aircraft comprising at least one wing claim 1 , the aircraft wing comprising:a main part,a wing tip mounted mobile in attack relative to the main part, anda junction device between the wing tip and the main part of the wing, the junction device being configured to allow rotation of the wing tip relative to the main part about a first rotation axis enabling control in attack of the wing tip, and to allow rotation of the wing tip relative to the main part about a second ...

Split Spiroid

An airplane, including a wing and a spiroid wing tip coupled to an end of the wing. The wing includes a wing leading edge and a wing trailing edge. The spiroid wing-tip includes an enclosed loop, which includes a beginning section, an ending section, and a middle section. The beginning section includes a leading edge generally continuous with the wing leading edge. The ending section includes a trailing edge swept rearward with respect to the wing trailing edge. The middle section is between the beginning section and the ending section, and includes a portion extending above a chord plane of the wing.

ROTATABLE WING TIP JOINT AND METHOD OF MAKING SAME

A joint for coupling a wing tip to a wing base includes a linking member that extends from a first end to a second end. The linking member first end is coupleable to the wing base, and the linking member second end is coupleable to the wing tip. The linking member defines first second hinge lines that are substantially parallel. The joint also includes at least one actuator. A first end of each at least one actuator is coupled to the linking member, and a second end of each at least one actuator is coupleable to one of the wing base and the wing tip. The at least one actuator is operable to rotate the wing tip about the first and second hinge lines between a first orientation and a second orientation relative to the wing base. 1. A joint for coupling a wing tip to a wing base , said joint comprising:a linking member that extends from a first end to a second end, said linking member first end is coupleable to the wing base, said linking member second end is coupleable to the wing tip, said linking member defines a first hinge line and a second hinge line, said first hinge line and said second hinge line are substantially parallel; andat least one actuator, a first end of each said at least one actuator is coupled to said linking member, a second end of each said at least one actuator is coupleable to one of the wing base and the wing tip, said at least one actuator is operable to rotate the wing tip about said first and second hinge lines between a first orientation and a second orientation relative to the wing base, wherein:each said at least one actuator second end is rotatable relative to said at least one actuator first end about an actuator axis;each said at least one actuator second end is movable to a first position relative to said at least one actuator first end to position the wing tip in the first orientation; andeach said at least one actuator second end is movable to a second position relative to said at least one actuator first end to position the wing ...

UNMANNED AERIAL VEHICLE WITH A TRI-WING CONFIGURATION

This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a substantially polygonal perimeter frame and a central frame. The perimeter frame includes a front wing, a lower rear wing, and an upper rear wing. The wings provide lift to the UAV when the UAV is moving in a direction that includes a horizontal component. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more thrusting motors and corresponding thrusting propellers. When the UAV is moving horizontally, the thrusting motor(s) may be engaged and the thrusting propeller(s) will aid in the horizontal propulsion of the UAV. 1. An unmanned aerial vehicle (“UAV”) frame , comprising: a hub;', 'a first motor arm extending from the hub in a first direction;', 'a second motor arm extending from the hub in a second direction;', 'a third motor arm extending from the hub in a third direction; and', 'a fourth motor arm extending from the hub in a fourth direction;, 'a central frame, including a front wing having a first end and a second end;', 'a first side rail coupled to the first end of the front wing;', 'a second side rail coupled to the second end of the front wing;', 'a lower rear wing coupled to the first side rail and the second side rail; and', 'an upper rear wing coupled to the first side rail and the second side rail; and, 'a perimeter frame, includingwherein the first motor arm, the second motor arm, the third motor arm, and the fourth motor arm are coupled to the perimeter frame.2. The UAV frame of claim 1 , wherein the first end of the front wing and the first side rail are coupled using a corner junction.3. The UAV frame of claim 2 , wherein the corner junction includes an input/output mounting component configured to house at least one input/output component.4. The ...

VORTEX REDUCTION APPARATUS FOR USE WITH AIRFOILS

Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight. 1. A vortex reduction apparatus for use with an airfoil , the vortex reduction apparatus comprising:a housing to couple to a tip of an airfoil, the housing defining a volute fluid flow passageway between an inlet and an outlet, the volute fluid flow passageway structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.2. The vortex reduction apparatus as defined in claim 1 , wherein the volute fluid flow passageway includes a vane formed in a cavity of the housing.3. The vortex reduction apparatus as defined in claim 2 , wherein the vane extends from an inner surface of the housing defining the cavity toward a longitudinal axis of the volute fluid flow passageway.4. The vortex reduction apparatus as defined in claim 3 , wherein the vane is fixed to the housing.5. The vortex reduction apparatus as defined in claim 3 , wherein the vane does not rotate relative to the housing.6. The vortex reduction apparatus as defined in claim 2 , wherein the vane includes a plurality of vanes spaced along a longitudinal length of the volute fluid flow passageway between the inlet and the outlet.7. The vortex reduction apparatus of claim 2 , wherein the vane extends along at least a portion of a longitudinal length of the housing between the inlet and the outlet.8. The vortex reduction apparatus as defined in claim 1 , wherein the volute fluid flow passageway defines an axial fluid flow path having a longitudinal ...

MULTI-MODE AERIAL VEHICLE

A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing. 1. A multi-mode aerial vehicle , comprising:an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom;a right-fixed wing extending from the right side of the elongated fuselage;a right tilt wing attached at a first side to a free end of the right fixed wing, the right tilt wing being rotatable ninety degrees about its axis;a right duct attached to a second side of the right tilt wing;a right winglet attached to the right duct opposite to the right tilt wing;a left-fixed wing extending from the left side of the elongated fuselage;a left tilt wing attached at a first side to a free end of the left fixed wing, the left tilt wing being rotatable ninety degrees about its axis;a left duct attached to a second side of the left tilt wing;a left winglet attached to the left duct opposite to the left tilt wing;a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, the tilt tail being rotatable ninety degrees within the curved guide slot;a tilting mechanism coupling, via a gearbox, a right shaft integrated with the right tilt wing, a left shaft integrated with the ...

A wing for an aircraft, and an aircraft comprising such a wing

Braided composite spar

브레이드 복합 날개보용 브레이드 복합 날개보(10) 또는 예비 성형체로서, 복수의 튜브형 브레이드 섬유 플라이를 포함하고, 상기 날개보(10) 또는 예비 성형체는 뿌리부에서 말단부로 길이 방향으로 연장하는 중심선을 갖고, 상기 중심선의 일부 또는 전체는 단일 평면에 놓이지 않는 곡선 경로를 따른다. 상기 날개보(10) 또는 예비 성형체는 윙렛(5)용 튜브형 주 날개보를 제공하는데 사용될 수 있다. 또한, 상기 윙렛(5)은 전방 날개보 웨브(16), 상부 전방 날개보 캡(17), 및 하부 전방 날개보 캡(18)이 형성된 전방 날개보(11)를 갖는다. 상기 윙렛(5)의 상부 스킨(19)은 상기 브레이드 날개보(10)와 상부 전방 날개보 캡(17)에 연결된다. 상기 윙렛(5)의 하부 스킨(20)은 상기 브레이드 날개보(10)와 하부 전방 날개보 캡(18)에 연결된다.