Прямоугольный, многощелевой, однооболочковый, управляемый парашют

Полезная модель относится к парашютной технике, в частности к прямоугольному, многощелевму, однооболочковому, управляемому парашюту. Прямоугольный, многощелевой, однооболочковый, управляемый парашют состоит из купола, строп, подвесной системы. При этом купол выполнен из нескольких полотнищ, соединенных друг с другом с помощью силовых лент. Причем расстояние между полотнищами – щель, должно быть не менее ширины полотнищ, из которых составлен купол. Целью заявляемой конструкции парашюта являются уменьшение площади купола, уменьшение массы парашюта вследствие уменьшения площади купола, уменьшение нагрузки, действующей на парашютиста во время раскрытия купола, исключение изменения формы купола, исключение вращения или рыскания относительно вертикальной оси, исключение раскачивания парашютиста из стороны в сторону, исключение возможности гибели парашютиста в результате частичного разрушения купола. 1 ил.

ПАРАШЮТ

Изобретение относится к парашютной технике, в частности к крестообразным парашютам. Парашют содержит выполненный из ткани с низкой или нулевой воздухопроницаемостью купол крестообразной формы с короткими лопастями и стропы, присоединенные к лопастям и центральной части с образованием коробчатой конструкции. При этом длина лопастей увеличивается к их краям. Техническим результатом изобретения является обеспечение минимальной разнодлинности прикрепленных к лопастям строп, что позволяет уменьшить вероятность перехлестывания купола стропами и тем самым повысить надежность работы парашюта. 1 з.п. ф-лы, 5 ил.

ПЛАНИРУЮЩИЙ ПАРАШЮТ

Изобретение относится к авиационной промышленности, в частности к парашютной технике, и предназначено для использования в качестве парашюта для управляемых парашютных систем, в том числе для автоматизированных парашютных систем доставки грузов. В планирующем парашюте, содержащем купол типа «крыло», выполненный в виде верхней и нижней оболочек, соединенных между собой по задней кромке, нервюры, соединяющие оболочки между передней и задней кромками с образованием воздухозаборников, и соединенные с куполом стропы. При этом купол выполнен площадью от 45 м2до 70 м2, стропы расположены в несколько каскадов, причем профиль крыла выполнен с закругленной передней кромкой с размахом 12-15 м и с удлинением 2,5-3 единиц. Длины силовых нервюр выполнены с уменьшением от центра к краям профиля при соотношении боковой силовой нервюры к центральной 1:1,5, силовые нервюры усилены лентами в направлениях продолжения строп купола и имеют по отношению к горизонту угол наклона от 30° до 40°. Стропы смонтированы ...

NON-WOVEN FABRIC

... 1313037 Parachutes MONSANTO CO 16 Aug 1971 [17 Aug 1970] 38344/71 Heading B7G [Also in Division D1] A cruciform parachute for supporting magnesium flares is made from a non-woven web (see Divisions D1-D2) of autogenously bonded continuous nylon filaments randomly orientated within the plane of the web, the web having an air permeability of 300 to 550 cu. feet/sq. foot per minute at a pressure difference of 0À5 inch of water, and a density of 0À25 to 0À46 gm. per c.c. Preferably the thickness is 1À7 to 5À3 mils. and the weight is 0À6 to 1À0 oz./sq. yd. The cruciform structure prevents oscillation, so that, when used to support a flare, ascending magnesium oxide particles are trapped by the web thus reducing its permeability and thereby slowing the descent of the flare.

Domed air receiver for the operation of parachutes

... 695,569. Parachutes. SANDERSON. C. Sept. 19, 1950. No. 22934/50. Class 4. A parachute comprises a domed air receiver 23 made of light metal disposed within, and at the apex of a canopy 27, valve means 38 being provided for controlling the discharge of air from beneath the canopy. Air enters the receiver through a plurality of holes 22 and leaves via a vent 33.

Aerial delivery system

An aerial delivery box 30 for release from an aircraft comprises a hold 31 for a payload and an impact absorbing zone 32for protecting the payload of the hold. The hold and the impact absorbing zone are formed of biodegradable materials. The impact absorbing zone comprises at least one layer having a honeycomb structure 33 defining a cellular network extending in the plane of the layer. The aerial delivery box may be attached to a parachute 20 by a plurality of shroud lines 21 to form an aerial delivery assembly. A method of delivering goods by aerial delivery comprises releasing the aerial delivery assembly from an aircraft. The aerial delivery assembly may be released from a cargo pod of an aircraft 150 such as a cargo pod comprising a first casing 152 attached to the aircraft and a second casing 151 attached to the first casing rearwards of the first casing. The first and second casings define an opening to receive the assembly. The second casing is adapted to be releasable from the ...

Improvements in or relating to aerodynamic slots in flexible membranes

1,143,383. Parachutes, sails and other air sustained membranes. O. W. NEUMARK. 25 May, 1966 [31 May, 1965], No. 22980/65. Headings B7G, B7K, B7V and B7W. Flexible fabric used in parachutes, kites, sails and for the skirts of ground-effect machines is provided with an aerodynamic slot 6 having edges 4. 5 interconnected at a plurality of positions by webs 3 to thereby ensure that the width of the slot is uniform. The webs are integrally woven into main webs 1, 2 to which the edges 4, 5 of the slot are sewn. The webs may be in a single central or offset row, or in two mutually staggered rows. A parachute of generally wing-shaped configuration. Fig. 7, has a number of slots 6 formed in the above manner distributed over its upper surface. The surface has an air-filled bulbous leading edge 10 and is constrained to an aerofoil configuration in side elevation by downwardly extending fabric webs 11, the lower edges of which are provided with tension cords 12 which are extended to form fore-and-aft rigging lines 13. To close each slot the edges 4, 5 may be drawn together by cords (17), Fig. 9 (not shown), passing through eyelets in an adjacent web 11 and the resulting nick which occurs in the surface of the parachute may be smoothed out by tensioning a cord 20 which passes through a tunnel 21 provided on the web 11. A groundeffect machine, Fig. 10 (not shown), has a skirt comprising inner and outer skins (22, 23) separated by flexible webs (25) to define a passage through which air passes through slots (6) of the above described form and disposed in the lower part (22a) of the outer skin. The skins (22, 23) are held in an inwardly curved position by cables (23a, 26).

ESCAPE PARACHUTE FOR EMERGENCY

Ram air inflated wing

LOW COST PARACHUTE AND METHOD OF MAKING SAME

A parachute canopy comprising a plurality of gores (12) wherein at least one of the gores comprises an inflation pocket (25) and a method for making said parachute canopy comprising the steps of folding a plurality of rectangular gones in half, parallel to a pair of long sides (12A), each of said gones having two short sides (12B) and two long sides (12A); sealing a first short side of each of said plurality of gones to form an inflation pocket in each of said gones; connecting said plurality of gones together proximate to said inflation pockets; and connecting adjacent corners of a second short side of said plurality of gones.

REINFORCING MATERIAL FOR PARACHUTES AND METHODS FOR REINFORCING PARACHUTES

A parachute (10) is formed using a non-woven composite material. The non-woven composite material (100) is formed by fusing a plurality of mono-filament fibers between thin layers of plastic (126,128). The non-woven material may be used as reinforcing tapes or as parachute lines in connection with a parachute of typical construction.

Gewebe für Fallschirme.

Fallschirm.

Fallschirmhülle.

Fallschirm.

Verfahren zur Herstellung eines der Befestigung dienenden Endstückes am Ende eines flachen Bandes

Verfahren zur Herstellung eines Fallschirmes aus Bändern und nach dem Verfahren hergestellter Fallschirm

Aerial delivery system

Lifesaving parachute

The present invention relates to a lifesaving parachute, for moving people in danger to the ground safely in the case of accidents causing the loss of lives, such as fire of a high-storied building, earthquake and the like, which includes a main body having straps for a user to wear the parachute, stick elements formed of a unit length and fixed to the main body along a periphery thereof, elastic elements connected to connection elements of the stick elements for applying elastic force to the stick elements in a spreading direction of the stick elements, and an empty receiving case having an opened lower part for receiving the main body as folded.

Fabric forms some for aerofoils of parachutes and manufactoring process of such aerofoils

Rope improved for parachute

Parachute with cap made up of bands or ribbons

Fabric for the clothes industry of aerofoils of parachutes and other uses technical

Aerofoil of parachute forming parachute extractor

Improvements with the parachutes

Fabric for parachutes

HIGH-ALTITUDE PAYLOAD RETRIEVAL (HAPR) APPARATUS AND METHODS OF USE

The disclosure provides an HAPR apparatus comprising an inflatable frame configured to generate canopy extension based on surrounding atmospheric pressure. The inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa. The internal pressure of the inflatable frame is typically about 101 kPa. The HAPR apparatus allows ascension with the canopy hanging under its own weight to reduce ascension time, then generates canopy extension prior to release in essentially a zero velocity, zero dynamic pressure condition. 1. (canceled)2. (canceled)3. (canceled)4. (canceled)5. (canceled)6. (canceled)7. A High-Altitude Payload Retrieval (HAPR) apparatus for full planform deployment at high altitude comprising:a canopy comprising a flexible material having a weight;a line channel passing through the canopy;an inflatable frame coupled to the canopy, where the inflatable frame is configured on the canopy to establish a projected span of the canopy when inflated to a non-wrinkling condition, and where the inflatable frame has a first collapse load limit less than the weight of the canopy at a first pressurized state less than 75 kPa and the inflatable frame has a second collapse load limit greater than the weight of the canopy at a second pressurized state of greater than 95 kPa; a plurality of fastening devices coupled to a perimeter of the canopy and configured to fasten a plurality of lines to the canopy; andan upper skin having a leading edge, trailing edge, a first lateral edge, and a second lateral edge generally opposing the first lateral edge, where the inflatable frame is coupled to the upper skin;a lower skin;a plurality of rib panels each having an upper edge and a lower edge, with at least a portion of the upper edge affixed to the upper skin and at least a portion of the lower ...

Aerial delivery system

Improvements in or relating to parachutes

... 199,104. Democratis, S. J. March 13, 1922. Parachutes.-A parachute or part thereof is. formed with the warp and weft of the fabric arranged at an angle to the line of pull of the load. The parachute is formed in panels stitched together with zig-zag stitches as shown in Fig. 6 and hemmed at its lower edge. Where fabric cut on the bias is not wide enough to fill a panel the corner may be filled by an additional triangular piece as shown in Fig. 5.

FOOD CLOSE US TIGERS PARACHUTE AND MANUFACTURING PROCESS DAFUR

Verbindungsglied und dessen Verwendung

Die Erfindung betrifft ein Verbindungsglied (1) mit einem eine Öffnung aufweisenden Grundkörper (10) und einem in der Öffnung aufnehmbaren Verschlussteil (4), wobei das Verschlussteil ein erstes Ende (41) aufweist, welches am Grundkörper schwenkbar gelagert ist und ein zweites Ende (42) aufweist, welches mittels einer Verriegelungsvorrichtung (3) am Grundkörper festlegbar ist, wobei die Verriegelungsvorrichtung einen Schwenkhebel (33) enthält und das Verbindungsglied weiterhin eine Sicherungseinrichtung (2, 8, 9, 17) aufweist, welche dazu eingerichtet ist, ein unbeabsichtigtes Schwenken des Schwenkhebels zu verhindern, wobei die Sicherungseinrichtung einen Verriegelungsstift (8) und einen Betätigungsknopf (2) enthält, der Verriegelungsstift in eine zugeordnete Bohrung (17) am Grundkörper eingreift und im Betätigungsknopf aufgenommen ist, welcher axial verschiebbar am Schwenkhebel aufgenommen ist. Weiterhin betrifft die Erfindung die Verwendung eines solchen Verbindungsgliedes.

POLYMERIC FILM MATERIAL AND ITS PRODUCTION

PARACHUTE SLIDER WITH STIFFENING ELEMENTS

An improved slider for use with a parachute, particularly a ram-air type parachute, is provided. The slider includes a generally rectangular piece of material having grommets in the corners through which the suspension lines of the parachute run. At least one retaining structure is attached to or made in the slider material for securing one or more stiffening elements. The stiffening elements are flexible enough to allow for the packing of the parachute, but stiff enough to keep the material of the slider spread open in the fore/aft direction across the short axis of the slider and thereby prevent the slider from folding and flapping once the canopy has opened.

CRUCIFORM PARACHUTE WITH ARMS ATTACHED

An improved cruciform or cross parachute is formed by attaching the adjacent edges of the lateral arms (14, 16, 18, 20) to each other to form a three- dimensional canopy (10), when inflated, which is substantially square at the top and substantially round at the lower edge. The attachment of the adjacent edges of the arms are such as to provide generally vertical openings or vents (36) through which air can flow outwardly from underneath the canopy, which form "corner air flow jets", thus allowing use of zero or near zero porosity fabric for constructing the canopy. Attachment of the adjacent edges of the arms at their outer tips forms a continuous hem at the lower edge of the canopy which eases packing and improves reliability. Arm air flow jets of U.S. Patent No. 5,839,695 may also be included in addition to the corner air flow jets formed by attaching the adjacent arm side edges. Air flow from underneath the canopy through the air flow jets should be sufficient to achieve a degree of ...

Cruciform parachute with arms attached

Parachute

Aerofoil of parachute hypersustentée

Improvements with the parachutes

AERIAL DELIVERY DEVICES, SYSTEMS AND METHODS

According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.

PARACHUTE FOR LOW ALTITUDE DEPLOYMENT

A parachute is adapted for deployment at low altitudes and low air speeds, such as for use in emergency evacuations from buildings. A canopy of the parachute includes a conical portion with a top polar opening. The canopy also includes a porous section that create an airflow stream during descent, generating forward speed and enabling the parachute to be steered during descent. The materials used in the canopy lines and the harness help reduce shocks and help to sustain a substantially steady-state internal air pressure in the canopy. A method for folding the parachute helps to reduce the time to deployment.

PARACHUTE INLET CONTROL SYSTEM AND METHOD

A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of lacing loops and/or reefing rings. The lacing loops may be passed through the reefing rings and/or may be routed around one or more of the main parachute suspension lines. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and lacing loops function as a reefing means, and prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

ПАРАШЮТ

FIELD: parachutes. SUBSTANCE: parachute has canopy and lines made at least partially from oriented film material which has alternating elongated and non-elongated sections; non-elongated sections have form of strips. Parachute canopy is made from oriented film polymer material; considerable area of this material has alternating elongated and non-elongated sections in form of strips. EFFECT: simple and effective method of reducing tendency to break at impact load; improved energy absorbing capacity. 6 cl, 5 dwg зоэдггс ПЧ Го РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ЗВО“” 2417 608 Сл (51) МПК В 64 0 17/02 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 94040709/28, 17.04.1989 (30) Приоритет: 18.04.1988 СВ 8809077.4 (46) Дата публикации: 20.08.1998 (56) Ссылки: Ц, 3589653 А, кл. В 64 О 1702, 1969. (71) Заявитель: Оле-Бендт Расмуссен (ОК) (72) Изобретатель: Оле-Бендт Расмуссен (ОК) (73) Патентообладатель: Оле-Бендт Расмуссен (ОК) (54) ПАРАШЮТ (57) Реферат: Изобретение касается парашютов. Парашют имеет купол и стропы, выполненные, по меньшей мере частично, из ориентированного пленочного материала. Указанный материал выполнен С чередующимися вытянутыми и невытянутыми участками, причем невытянутые участки имеют форму полос. Купол парашюта выполнен из ориентированного пленочного полимерного материала, значительная площадь которого выполнена С чередующимися вытянутыми и невытянутыми участками, имеющими форму нескольких полос. Технический результат заключается в создании простого и эффективного способа уменьшения тенденции к разрыву при ударной нагрузке парашюта из пленочного материала и в улучшении способности парашюта к поглощению энергии. 2 с. и4 з.п. ф-лы, 5 ИЛ. -------- 4 —= 0 чушь чБааааь ани пнининие инь |. ^, нии ПИПЦИИНИ > НиваНмии ВиИНИНИИ НИИ ИИ чз». ним НИИ пни ции Оеоаовиии и ПИ Не Ни наи -< ШИ РИ 5 ши Фиг.1 21176081 С1 КО зоэ9дЕгс пы Го КУЗЗАМ АСЕМСУ ГОК РАТЕМТ$ АМО ТКАОЕМАКК$ (19) 13) ВИ "” 2117 608 ' (51) "С° В 64 р 17/02 ...

ПАРАШЮТ

Изобретение касается парашютов, у которых купол и/или стропы изготовлены из ориентируемого полимерного пленочного материала. Парашют по изобретению, имеющий купол и стропы из ориентируемого пленочного полимерного материала, соединяющие купол с грузом, характеризуется тем, что материал строп снабжен рисунком чередующихся вытянутых и невытянутых участков материала, причем невытянутые участки имеют форму полос (лент), простирающихся в направлении, в сущности, параллельном направлению ударных сил, которым подвергаются стропы при открывании парашюта в полете с грузом. Другой аспект изобретения касается парашюта с куполом для поддержания опускаемого груза, который выполнен из ориентируемого полимерного пленочного материала, причем значительная площадь указанного пленочного материала снабжена рисунком чередующихся участков вытянутого и невытянутого материала, при этом невытянутые участки имеют, в сущности, форму нескольких полос, разделенных указанными вытянутыми участками, и указанные полосы ...

МЕШОК ДЛЯ СЫПУЧЕГО ПРОДУКТА, СПОСОБ ИЗГОТОВЛЕНИЯ МЕШКОВ ИЗ ПОЛИМЕРНОГО ПЛЕНОЧНОГО ИЛИ ТРУБЧАТОГО МАТЕРИАЛА, ОРИЕНТИРУЕМЫЙ ТЕРМОПЛАСТИЧНЫЙ ПЛЕНОЧНЫЙ ПОЛИМЕРНЫЙ МАТЕРИАЛ ДЛЯ ИЗГОТОВЛЕНИЯ МЕШКОВ

Использование: мешок для хранения и транспортировки сыпучих грузов, способ изготовления этих мешков и ориентируемый термопластичный пленочный материал для мешков. Сущность изобретения: ориентируемый термопластичный пленочный полимерный материал имеет по меньшей мере одну область вытяжки, в которой материал вытянут в поперечном направлении, и прилегающие к противоположным сторонам указанной области зоны без вытяжки, в которых материал практически не вытянут. Данный материал имеет особое значение для предотвращения разрыва мешков с материалами, в особенности в тех случаях, когда указанные области примыкают к сварному шву в случае наполненного мешка. Мешок для хранения сыпучих грузов выполнен с гофрированными областями поглощения ударной нагрузки, представляющими собой участки с выступами зубцами, расположенными поперечно направлению вытяжки. Способ изготовления мешков содержит операции по изготовлению поперечного шва и размещению областей поглощения ударной нагрузки. 3 с. и 18 з. п. ф-лы, ...

Befestigung von flexibler Bespannung an Holmen

LEINE.

Improvements in and relating to Aeroplanes and other Aircraft.

... 125,655. Smith, W. S. Oct. 12, 1916. Aerostats; cars; planes, construction of; kites. -The planes and other surfaces and the nacelles and fuselages of aeroplanes, as well as those parts of air-ships, balloons, and kites in which fabric or sheet material is used, are covered with a fabric formed wholly or in part of metal filaments and adapted to be tightened by a dope. To enable the dope to be effective, a fabric is employed of substantially 300 threads per inch, woven in linen binding. The materials for forming the filaments may comprise aluminium, aluminium-zinc or aluminium-zinc-copper alloys, duralumin, copper and tin alloys, brass, steel, and iron. Phosphorus and manganese may be used in certain alloys such as phosphor bronze. Alloys which are not good conductors of electricity are preferred.

PARACHUTES

... 1457704 Parachutes BRUGGEMANN & BRAND KG 3 Dec 1974 [5 Dec 1973] 52298/74 Heading B7G To restrain the initial opening of a parachute canopy 1 a continuous strip 4 of material is secured to the rigging lines 3 below the hem 2 of the canopy and between each pair of rigging lines the strip is first folded in its own length to make a loop 4b which is then folded sideways as shown in Fig. 5 to be sandwiched between respective folded portions of the base of the canopy prior to packing of the parachute. Upon release of the parachute from its pack the frictional resistance offered by the folded portions 4b prevents initial shock opening of the canopy and prevents the rigging lines from becoming entangled with the canopy. In a canopy of synthetic material the strip would be made from cotton to ensure adequate frictional resistance and its circumferential length is less than that of the hem of the canopy to create a diverging- converging shape to the inflated canopy.

FILM FROM POLYMERI MATERIAL AND ITS PRODUCTION.

BY RAM AIR OF BLOWN UP WINGS

Aerial delivery devices, systems and methods

According to certain embodiments, an aerial delivery system configured to be deployed from an aircraft comprises a base, a sleeve generally configured to be positioned on the base, a bag configured to receive at least one liquid and a lid assembly attached to the bag using at least one strap. In some embodiments, the strap is attached to the bag in a manner that causes the bag to be selectively compromised once the aerial delivery system is deployed from an aircraft. In one embodiment, the system comprises a cellulose-based material. In other arrangements, the bag comprises polypropylene.

Parachute slider with stiffening elements

An improved slider for use with a parachute, particularly a ram-air type parachute, is provided. The slider includes a generally rectangular piece of material having grommets in the corners through which the suspension lines of the parachute run. At least one retaining structure is attached to or made in the slider material for securing one or more stiffening elements. The stiffening elements are flexible enough to allow for the packing of the parachute, but stiff enough to keep the material of the slider spread open in the fore/aft direction across the short axis of the slider and thereby prevent the slider from folding and flapping once the canopy has opened.

Parachute with inflatable enclosure

CONTAINER FOR AERIAL DELIVERY

A system for aerial delivery of a payload is disclosed. The system comprises a box, a lid adapted to close the box and a harness adapted to support the box and the lid. A parachute is coupled to the harness and the parachute has at least one slit adapted to control the descent of the system. A plurality of inflatable tubes are placed within the box and under and around the payload that are adapted to cushion the payload. Figure 4 405" ...

Cruciform parachute design

PARACHUTE WITH A CIRCULAR CANOPY

PARACHUTE CANOPY

PARACHUTE CANOPY A parachute canopy comprises air entries provided on the canopy itself. The canopy is constituted by an assembly of gores, each gore being composed of three gore portions. The air entries are provided on a predetermined number of gores, the medium gore portion overlapping the lower gore portion. The medium gore portion and the lower one are sewn together only at meridional lines such as to leave a free passage between their overlapping portions which constitutes an air entry.

LIFESAVING PARACHUTE

The present invention relates to a lifesaving parachute, for moving people i n clanger to the ground safety in the case of accidents causing the loss of lives, such as fire of a high-storied building, earthquake and the like, whi ch includes a main body (10) having straps (11 ) for a user to wear the parachute, stick elements (20) formed of a unit length and fixed to the main body (10) along a periphery thereof, elastic elements (21 ) connected to connection elements of the stick elements (20) for applying elastic force to the stick elements (20) in a spreading direction of the stick elements (20), and an empty receiving case (30) having an opened lower part for receiving t he main body (10) as folded.

COMPOSITE, A PROCESS FOR THEIR PREPARATION AND FLIGHT THE WEBS COMPRISING

Improvements with the parachutes

Parachute arrangement for meteorological balloon - has parachute shrouds directly connected to radar reflector structure via cabling traversing central opening of reflector

Improvements with the construction of the caps of parachutes

Improvements with the parachutes

Improvements brought to the parachutes

Improvement with fabrics for parachutes

Process for the manufacture of plastic ends at the end of bands or cables with multiple strands

PERFECTIONNEMENT DES PARACHUTES POUR SONDE METEOROLOGIQUE

PARACHUTE DESTINE A RALENTIR LA DESCENTE D'UNE SONDE METEOROLOGIQUE COMPRENANT AU MOINS UN BALLON 1, UN REFLECTEUR RADAR 7, 8 MUNI D'AU MOINS UNE PARTIE CENTRALE AJOUREE 12 ET UNE RADIO SONDE 11, LE PARACHUTE ETANT DU TYPE COMPRENANT UNE VOILURE 5 RELIEE A DES SUSPENTES 4 CARACTERISE EN CE QUE LESDITES SUSPENTES 4 SONT RELIEES DIRECTEMENT A L'ARMATURE 7 DU REFLECTEUR RADAR 7, 8.

Sophisticated parachute

Parachutes

PARACHUTE COMPOSED OF INDIVIDUAL STRIPS DETACHABLY JOINED TO ONE ANOTHER

The invention relates to a parachute composed of a plurality of individual textile strips (11) separated from one another, at least two groups of individual strips in each case comprising a plurality of individual strips running parallel to one another being aligned in a crossing arrangement and together forming the parachute canopy (10), the respectively crossing individual strips of the individual groups being joined to one another, and shroud lines (13) for holding a load to be attached to the parachute being fitted to the outer ends (12) of the individual strips. The parachute is characterized in that, in order to join the mutually crossing individual strips (11) to one another, in their overlapping regions (17) on the respectively mutually facing surfaces of the individual strips (11), in each case there is fitted at least one loop (21) to receive joining elements (22) detachably joining the loops (21) of the two individual strips (11) to one another.

Container for aerial delivery

A container for aerial delivery of a payload is comprised of a box, a lid adapted to close the box, a harness adapted to support the box and lid, a parachute coupled to the harness, and a plurality of inflatable tubes placed within the box and surrounding the payload. The plurality of inflatable tubes adapted to cushion the payload. The parachute has at least one slit adapted to control the descent of the system.

AIRCRAFT WITHOUT ENGINE

КРЕСТООБРАЗНЫЙ ЛОПАСТНЫЙ ПАРАШЮТ

FIELD: equipment for flying vehicles. SUBSTANCE: parachute is formed by fastening together adjacent edges of side blades 14, 16, 18 and 20 for forming three-dimensional canopy 10 at filling it with air; it is square at the top and round over lower edge. Adjacent edges of blades are fastened together for forming vertical holes and openings 36 for escape of air from under canopy and for forming angular nozzles for escape of air flows, thus making it possible to use material for manufacture of canopy possessing zero or close to zero porosity. Connection of adjacent edges of blades near their external ends makes it possible to obtain continuous edge over lower edge of canopy, thus facilitating the process of packing the parachute and enhancing reliability. Nozzles for escape of air flows are included additionally to angular nozzles formed by connecting the adjacent side edges of blades. EFFECT: stability of descent of parachute within ±5° or even lesser. 27 cl, 6 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß RU (19) (11) 2 267 448 (13) C2 (51) ÌÏÊ B64D 17/02 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2003110321/11, 22.08.2001 (72) Àâòîð(û): ÁÅÐËÀÍ Æàí Ñ. (US) (24) Äàòà íà÷àëà äåéñòâè ïàòåíòà: 22.08.2001 (30) Ïðèîðèòåò: 11.09.2000 (ïï.1-27) US 09/659,782 (73) Ïàòåíòîîáëàäàòåëü(ëè): ÏÀÐÀ-ÔËÀÉÒ, ÈÍÊ. (US) R U (43) Äàòà ïóáëèêàöèè çà âêè: 10.08.2004 (45) Îïóáëèêîâàíî: 10.01.2006 Áþë. ¹ 01 2 2 6 7 4 4 8 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: US 5839695 A, 24.11.1998. DE 8530402 U, 06.02.1986. SU 525287 A1, 09.01.1995. (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 11.04.2003 (86) Çà âêà PCT: US 01/26080 (22.08.2001) 2 2 6 7 4 4 8 R U Àäðåñ äë ïåðåïèñêè: 129010, Ìîñêâà, óë. Á.Ñïàññêà , 25, ñòð.3, ÎÎÎ "Þðèäè÷åñêà ôèðìà Ãîðîäèññêèé è Ïàðòíåðû", ïàò.ïîâ. Ñ.À.Äîðîôååâó C 2 C 2 (87) Ïóáëèêàöè PCT: WO 02/22441 (21.03.2002) (54) ÊÐÅÑÒÎÎÁÐÀÇÍÛÉ ËÎÏÀÑÒÍÛÉ ÏÀÐÀØÞÒ (57) Ðåôåðàò: ...

IMPROVEMENTS RELATING TO PARACHUTES

... 1,220,172. Parachutes. R. KOHNKE, [trading as RICHARD KOHNKE FALLSCHIRMWERK]. 29 Jan., 1968 [27 Jan., 1967], No. 4472/68. Heading B7G. A parachute canopy is made of a thin, rolled out, bonded; non-woven material of synthetic fibres. The gores 5 are preferably cut in one piece from the material. The parachute may be used for dropping goods, and may be used once only as it is said to be cheaper to construct and of cheaper materials than prior art canopies. The construction of prior art gores from woven fabric is also described, Figs. 1 to 4 (not shown).

PARACHUTES

Improvements in or relating to paper canopies or sails for parachutes

... 583,037. Paper for parachutes. FRIEDER, L. P. Oct. 12, 1943, No. 16711. Convention date, Aug. 25, 1942. [Classes 96 and 140] [Also in Group XXXIII] Paper sails or canopies of parachutes have a coating of glycerine, castor oil, liquid petroleum or sulphonated oil which may be applied in alcohol, carbon tetrachloride, or ethylene dichloride &c. to facilitate opening &c. The coated paper may be dusted with talc.

CROSS PARACHUTE WITH CONNECTED CROSS THIGHS

AIRPLANE WITHOUT ENGINE.

MATERIALS FOR PARACHUTES

PARACHUTE WITH REINFORCEMENT MATERIAL

Verbindungsglied und dessen Verwendung

Die Erfindung betrifft ein Verbindungsglied (1) mit einem eine Öffnung aufweisenden Grundkörper (10) und einem in der Öffnung aufnehmbaren Verschlussteil (4), wobei das Verschlussteil ein erstes Ende (41) aufweist, welches am Grundkörper schwenkbar gelagert ist und ein zweites Ende (42) aufweist, welches mittels einer Verriegelungsvorrichtung (3) am Grundkörper festlegbar ist, wobei die Verriegelungsvorrichtung einen Schwenkhebel (33) enthält und das Verbindungsglied weiterhin eine Sicherungseinrichtung (2, 8, 9, 17) aufweist, welche dazu eingerichtet ist, ein unbeabsichtigtes Schwenken des Schwenkhebels zu verhindern, wobei die Sicherungseinrichtung einen Verriegelungsstift (8) und einen Betätigungsknopf (2) enthält, der Verriegelungsstift in eine zugeordnete Bohrung (17) am Grundkörper eingreift und im Betätigungsknopf aufgenommen ist, welcher axial verschiebbar am Schwenkhebel aufgenommen ist. Weiterhin betrifft die Erfindung die Verwendung eines solchen Verbindungsgliedes.

Method of dispersing material to a target location with an aircraft

II ~~x2 I WDo -l, '''I There is disclosed a method of dispersing material to a target location with an aircraft, the method comprising the steps of: providing an unarmed system including a rupturable container within an exterior support for supporting the rupturable container when storing a filler material in the rupturable 5 container prior to dropping the system toward the target location, a parachute and a strap which is detached between attached to the parachute and the rupturable container; filling the rupturable container with the material while the parachute is detached and disposed away from an opening of the rupturable container for ease of filling; loading the system onto an aircraft; prior to dropping the rupturable container from the aircraft, attaching the parachute and the rupturable container with the 10 strap to arm the system; and dropping the system from the aircraft toward the target location. -44 i ' 52 4 4460f4 60^ 62 s0 30 ...

Manufactoring process of parachutes of spherical form by means of bands

PROCESS AND DEVICE Of OPENING Of a WALL GONFLEE

The method involves cutting an inflated wall (1) by displacing a filamentary cutting member i.e. cutting cord (2), over the inflated wall along a cutting line for creating a deflation opening to deflate the inflated wall. The cutting cord is initially extended over a portion of a face of the inflated wall and is initially fixed to a fixing point (3) of the inflated wall, where the cord is made of material e.g. metal, vegetal based material, synthetic material e.g. plastic or Kevlar(RTM: para-aramid synthetic fiber), and/or biological/animal based material e.g. silk or spider silk. An independent claim is also included for a device for deflating an inflated wall.

Improvements brought to the ropes and the similar elements such, in particular, that suspending rods and ropes

Fabric for parachutes

Improvements with the aerofoils of parachute

Twist

MECHANICALLY OPENING PARACHUTE

The mechanically opening parachute (10) is a parachute that may be opened quickly at low altitudes, such as during an emergency exit from an office building, for example. The mechanically opening parachute (10) includes a telescopic tube (18) having opposed upper and lower ends. A harness (12) adapted for releasably holding the user is secured to the lower end of the telescopic tube (18). The mechanically opening parachute (10) operates similarly to a conventional umbrella, with the telescopic tube (18) automatically opening upon actuation by the user, and with a conventional umbrella stretcher (22) opening a plurality of ribs (24) secured to a parachute canopy (28).

Method for making a parachute

A method of manufacturing a parachute having a canopy with an outer peripheral skirt and a plurality of spaced apart attachment points comprises selecting one of the attachment points as a starting point and winding a continuous fiber from the starting point to other attachement points until a net of reinforcement fiber is formed among the attachment points. A canopy is then attached to the resulting reinforcement net. Nonporous material can be used for the canopy because of the strong reinforcement achieved.

Manufacture of parachutes

Life preserving apparatus

Parachute canopy

Perforierter Fallschirm

Вращающийся парашют с куполом из коаксиальных колец

Полезная модель Вращающийся парашют с куполом из коаксиальных колец относится к парашютной технике. Целью заявляемой полезной модели являются увеличение коэффициента сопротивления Сп парашюта, уменьшение площадь купола, уменьшение массы парашюта, уменьшение нагрузки, действующей на спускаемый объект во время раскрытия купола, исключение возможности разрушения спускаемого объекта в результате частичного разрушения купола. Поставленная цель достигается тем, что купол выполнен из нескольких полотнищ, представляющих собой кольца, коаксиально расположенных друг относительно друга и соединенных друг с другом с помощью силовых лент, причем нижнее кольцо выполнено с соплами, из которых при опускании парашюта выходит воздух и реактивными силами заставляет вращаться купол и весь парашют. Применение заявляемой полезной модели позволит увеличить коэффициента сопротивления Сп парашюта, уменьшить площадь купола, уменьшить массу парашюта, уменьшить нагрузку, действующую на спускаемый объект во время раскрытия купола, исключить разрушение спускаемого объекта при частичном разрушении купола. 1 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 209 691 U1 (51) МПК B64D 17/02 (2006.01) B64D 17/10 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК B64D 17/02 (2022.02); B64D 17/10 (2022.02) (21)(22) Заявка: 2021133725, 18.11.2021 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Белущенко Василий Иванович (RU) Дата регистрации: 18.03.2022 Приоритет(ы): (22) Дата подачи заявки: 18.11.2021 (45) Опубликовано: 18.03.2022 Бюл. № 8 2 0 9 6 9 1 R U (54) Вращающийся парашют с куполом из коаксиальных колец (57) Реферат: Полезная модель Вращающийся парашют с относительно друга и соединенных друг с другом куполом из коаксиальных колец относится к с помощью силовых лент, причем нижнее кольцо парашютной технике. Целью заявляемой выполнено с соплами, из которых при опускании полезной модели являются увеличение парашюта ...

Composites, Method for Preparation of Same and Flying Sails Containing Them

This invention relates to a composite comprising two polyurethane films, identical or different, that are connected to one another and between which a reinforcement mesh and at least one textile reinforcement thread oriented according to at least one predetermined stress line is inserted. The invention also relates to sails including such a composite. 1. Composite comprising two polyurethane (PU) films , identical or different , which are connected to one another and between which a reinforcement mesh and at least one textile reinforcement thread oriented according to at least one predetermined stress line is inserted.2. Composite according to claim 1 , wherein the polyurethane is an aromatic or aliphatic polyether-based polyurethane.3. Composite according to claim 1 , wherein the polyurethane is an aliphatic polyester-based polyurethane.4. Composite according to claim 1 , wherein the PU films are connected to one another by welding.5. Composite according to claim 1 , wherein the PU films are connected to one another by lamination.6. Composite according to claim 1 , wherein the mesh has a mesh opening ranging from 2 to 20 mm.7. Composite according to claim 1 , wherein the mesh has a mesh opening ranging from 4 to 15 mm.8. Composite according to claim 1 , wherein a reinforcement fabric is placed inside the composite and arranged with respect to a portion of the composite.9. Composite according to claim 8 , wherein the fabric is laminated to the interior of the composite by a PU adhesive.10. Sail including at least one composite according to .11. Sail including at least one composite according to .12. Sail including at least one composite according to .13. Sail including at least one composite according to .14. Sail according to claim 10 , consisting of a flying sail.15. Paraglide sail including a leading edge consisting of a composite according to claim 10 , and/or including internal partitions consisting of a composite according to .16. Paraglide sail including a ...

PRE-DEPLOYED PARACHUTE

A pre-deployed parachute includes a double-drag balloon parachute with an inflation canopy and a first drag generating space, a universal joint attached to the double-drag balloon parachute by a universal joint, a pre-deployed canopy with a second drag generating space and attached to the universal joint, a load attached to the pre-deployed canopy. The inflation of the inflation canopy allows the pre-deployed canopy to be deployed without requiring height difference and any dynamic energy. With the buoyancy and the first drag generated by the double-drag balloon parachute and the second drag generated by the pre-deployed canopy, the pre-deployed parachute is capable of producing three drag forces, and therefore, the pre-deployed parachute can be brought to a stable condition within a very short time, which prevents the discomfort feeling of a sudden free fall at the beginning stage of the parachuting. 1. A pre-deployed parachute comprising:a double-drag balloon parachute being a symmetrical structure which is symmetrical with respect to a central axis and comprising an inflation canopy which defines a first drag generating space, the inflation canopy being formed with an inner inflation space, the inflation canopy is provided with a valve in communication with the inner inflation space, the inflation canopy including a peripheral wall which defines the first drag generating space, the first drag generating space including a first open end;a universal joint attached to the double-drag balloon parachute by a plurality of first cords, the first cords each having one end fixed to one end of the universal joint, and another end fixed to the double-drag balloon parachute, so that the double-drag balloon parachute is able to rotate with respect to the universal joint;a pre-deployed canopy including an arc-shaped top surface and an annular peripheral surface which defines a second drag generating space, the arc-shaped top surface being attached to a first end of the annular ...

Aircraft having Manned and Unmanned Flight Modes

In some embodiment, an aircraft includes an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system. A pod assembly is selectively attachable to the flying frame. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flying frame has a manned flight mode and an unmanned flight mode. 1. An aircraft comprising:a flying frame including an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system; anda pod assembly selectively attachable to the flying frame,wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode; andwherein, the flying frame has a manned flight mode and an unmanned flight mode.2. The aircraft as recited in wherein the airframe further comprises first and second wing members having a plurality of pylons extending therebetween.3. The aircraft as recited in wherein claim 2 , in the vertical takeoff and landing mode claim 2 , the first wing member is forward of the pod assembly and the second wing member is aft of the pod assembly and wherein claim 2 , in the forward flight mode claim 2 , the first wing member is below the pod assembly and the second wing member is above the pod assembly.4. The aircraft as recited in wherein claim 2 , in the vertical takeoff and landing mode claim 2 , the first and second wing members are above the pod assembly and wherein claim 2 , in the forward flight mode claim 2 , the first wing member is below the pod assembly and the second wing member is above the pod assembly.5. The aircraft as recited in wherein the propulsion system further comprises a distributed propulsion system including a plurality of propulsion assemblies.6. The aircraft as recited in wherein the pod assembly and the flying frame have at least one communication channel therebetween operable to enable communication between the pod assembly and ...

Transportation Method for Selectively Attachable Pod Assemblies

In some embodiments, a transportation method includes coupling a flying frame to a passenger pod assembly; lifting the passenger pod assembly into the air in a vertical takeoff and landing mode with the passenger pod assembly in a generally horizontal attitude; transitioning from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; transporting the passenger pod assembly toward a second location in the forward flight mode; transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the passenger pod assembly, which remains in the generally horizontal attitude; landing the flying frame at the second location in the vertical takeoff and landing mode; and releasing the passenger pod assembly. 1. A transportation method comprising:coupling a flying frame including an airframe, a propulsion system and a flight control system to a first passenger pod assembly at a first location;lifting the first passenger pod assembly into the air with the flying frame in a vertical takeoff and landing mode with the first passenger pod assembly in a generally horizontal attitude;transitioning the flying frame from the vertical takeoff and landing mode to a forward flight mode by rotating the flying frame relative to the first passenger pod assembly such that the first passenger pod assembly remains in the generally horizontal attitude;transporting the first passenger pod assembly from the first location toward a second location with the flying frame in the forward flight mode;transitioning the flying frame from the forward flight mode to the vertical takeoff and landing mode by rotating the flying frame relative to the first passenger pod assembly such that the first passenger pod assembly remains in the generally horizontal attitude;landing the flying frame at the second ...

Passenger Pod Assembly Transportation System

In some embodiments, a passenger pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a passenger pod assembly having a current location and a destination; upload a flight plan to a flight control system of a flying frame including an airframe and a propulsion system; dispatch the flying frame to the current location of the passenger pod assembly; couple the flying frame to the passenger pod assembly at the current location of the passenger pod assembly; transport the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; and decouple the passenger pod assembly from the flying frame at the destination of the passenger pod assembly. 1. A transportation services method comprising:receiving, at a transportation services provider system, a request for transportation of a passenger pod assembly having a current location and a destination;uploading a flight plan to a flight control system of a flying frame including an airframe and a propulsion system;dispatching the flying frame to the current location of the passenger pod assembly;coupling the flying frame to the passenger pod assembly at the current location of the passenger pod assembly;transporting the passenger pod assembly by air from the current location of the passenger pod assembly to the destination of the passenger pod assembly; anddecoupling the passenger pod assembly from the flying frame at the destination of the passenger pod assembly.2. The method as recited in further comprising:selecting, at the transportation services provider system, the flying frame from a fleet of flying frames;generating, at the transportation services provider system, the flight plan based upon the flying frame location, ...

Aircraft having a Fault Tolerant Distributed Propulsion System

In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

AIRCRAFT PROVIDED WITH A SECONDARY FLIGHT ASSEMBLY

A remote piloted aircraft comprising a secondary flight assembly adapted to intervene in case of failure or an emergency of the aircraft, said secondary flight assembly being provided with an additional control unit configured to process flight relevant data and which includes an additional receiver configured to receive commands from the remote pilot by means of a remote control unit, in case of failure or emergency said additional control unit being configured to generate, as a response, an activation command adapted to activate a first device to expel an upper wing placed in a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft, and also to generate an interdiction command of the primary propulsion unit, said upper wing being maneuverable by means of a further remote control unit. 1. A remote piloted aircraft comprising a primary propulsion unit with at least one engine suitable to put in rotation a plurality of propellers and a main control unit comprising at least one receiver configured to receive commands from a remote control unit , said aircraft has a secondary flight assembly suitable to intervene in case of failure or emergency of the aircraft , said secondary flight assembly being provided with an additional control unit configured to process data relevant to the flight and which includes an additional receiver configured to receive commands from a further remote control unit , in case of failure or emergency said additional control unit being configured to generate , as a response , an activation command suitable to activate a first device for the expulsion of an upper wing placed into a first compartment of the aircraft and to inflate a lower wing housed in a second compartment of the aircraft , and also to generate an interdiction command of the primary propulsion unit , said upper wing being maneuverable by means of said further remote control unit , the lower wing being shaped to cooperate ...

Parachute inlet control system and method

A parachute inlet control system is configured to provide an improved inflation profile for solo and/or clustered parachutes. An inlet parachute is coupled to a main parachute via a plurality of inlet control suspension lines and/or reefing rings. The inlet control suspension lines may be passed through the reefing rings and coupled to an anchor point below the main parachute. The inlet parachute is located in the inlet area of the main parachute, and causes the inlet of the main parachute to rapidly form a desirable shape. The inlet parachute and inlet control suspension lines function as a reefing system to prevent full inflation of the main parachute until a reefing cutter has functioned. In this manner, parachute failures, such as those due to leading and/or lagging parachutes in a parachute cluster, may be reduced or eliminated.

APPARATUS FOR CAPTURING AERIAL VIEW IMAGES

An apparatus for capturing aerial view images via an image capturing device is provided. The apparatus includes a base; a housing defining a cavity allowing for insertion of the image capturing device, wherein the housing is engaged with the base; at least one extension member, each extension member including an upper end and a lower end, wherein the lower end of each extension member is engaged with the base, wherein each extension member extends upwardly from the base; and an air resisting element engaged with the upper end of each extension member. 1. An apparatus for capturing aerial view images via an image capturing device , comprising:a base;a housing defining a cavity allowing for insertion of the image capturing device, wherein the housing is engaged with the base;at least one extension member, each extension member including an upper end and a lower end, wherein the lower end of each extension member is engaged with the base, wherein each extension member extends upwardly from the base; andan air resisting element engaged with the upper end of each extension member.2. The apparatus of claim 1 , wherein the housing is removably engaged with the base.3. The apparatus of claim 2 , wherein the at least one extension member is removably engaged with the base.4. The apparatus of claim 3 , wherein the air resisting element is removably engaged with each of the at least one extension member.5. The apparatus of claim 1 , wherein the air resisting element includes at least one strip.6. The apparatus of claim 5 , the upper end of each of the at least one extension member defining at least one opening claim 5 , wherein the air resisting element is threaded through each opening defined in the at least one extension member.7. The apparatus of claim 1 , the base defining at least one aperture claim 1 , wherein the image capturing device has at least one sensor claim 1 , wherein each sensor of the image capturing device is aligned with one of the at least one aperture ...

Wing cargo parachute system utilizing dynamic braking to reduce opening shock

Methods of reducing wing type parachute opening shock during a parachute drop, and parachute systems with reduced opening shocks are disclosed, the opening force reduction is achieved by dynamic braking, i.e. dynamically adjusting the canopy control lines during the inflation stage of the canopy. Typically, the control lines are set to zero brake length when the parachute canopy is released from the deployment bag, and are at least shortened during the inflation stage, optionally all the way to full brake. Optionally the control lines are also lengthened prior to completion of the canopy inflation. Other features and parachute systems are also disclosed.

PARACHUTE

A parachute includes a resistive body which is formed in a bag shape and receives air resistance, and two suspension lines, one end of each of which is connected to the resistive body and the other end of each of which can be connected to an object to be braked. The resistive body includes an opening through which air passes, a bottom part provided at an opposite side of the opening, and a side part provided extending toward a periphery of the opening from the bottom part while expanding. The side part includes a base part having an approximately constant height from the bottom part, and two tapered extension parts, each of which extends from the base part, while reducing a width thereof, to each of two ends as apexes located symmetrically with each other in the periphery of the opening. 1. A parachute comprising:a resistive body formed in a bag shape and receiving air resistance; andtwo suspension lines, one end of each of said two suspension lines being connected to said resistive body, the other end thereof being connectable to an object to be braked, an opening through which air passes;', 'a bottom part provided at an opposite side of the opening; and', a base part having an approximately constant height from said bottom part over an entirety of said base part; and', 'two tapered extension parts, each of which extends from said base part, while reducing a width thereof, to each of two ends as apexes located symmetrically with each other in said periphery of said opening with respect to a center of said opening,, 'a side part extending toward a periphery of said opening from said bottom part while expanding, wherein said side part comprises], 'wherein said resistive body compriseswherein one end of each of said two suspension lines is connected to each of said two ends of said two tapered extension parts.2. The parachute according to claim 1 , wherein said base part comprises of two parts which are symmetrical to each other about a center axis of said opening ...

CINCHED PARACHUTE

A cinched parachute is disclosed. In various embodiments, a cinched parachute as disclosed herein includes a canopy comprising one or more sections of canopy material, and a device integrated with the canopy that controls dimensions of the canopy material. For example, in some embodiments the device may be used to control the size of an opening atop the parachute. 1. A cinched parachute , comprising:a canopy comprising one or more sections of canopy material, wherein a first panel of the canopy is configured to be moved in a first direction and a second panel of the canopy is configured to be moved in a second direction different from the first direction; and a tether configured to control an amount of air entering the canopy;', 'a holding device configured to constrain or release the tether; and', 'a severing device configured to sever the tether, wherein the control device is integrated with the canopy and controls dimensions of the canopy material including widening an opening atop the parachute in response to the first panel and the second panel moving in different directions., 'a control device including2. The cinched parachute of claim 1 , wherein the control device is threaded through the parachute.3. The cinched parachute of claim 1 , wherein the control device controls a size of the opening atop the parachute.4. The cinched parachute of claim 1 , wherein the control device is positioned between tethers of the parachute and the opening atop the parachute.5. The cinched parachute of claim 1 , wherein the control device is positioned to pull a section of the canopy material into a packed state.6. The cinched parachute of claim 1 , wherein the control device traverses a casing in the canopy of the parachute.7. The cinched parachute of claim 1 , wherein at least one end of the tether is secured in the holding device that releases or pulls in the tether.8. The cinched parachute of claim 1 , wherein the holding device allows the tether to travel in one direction ...

RIGIDIZED ASSISTED OPENING SYSTEM FOR HIGH ALTITUDE PARAFOILS

A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle 1. A high altitude parafoil comprising:a base structure configured to be attached with a payload and to be releasably attached to a high altitude balloon;a first elongated wing tip support hingedly connected with the base structure;a second elongated wing tip support hingedly connected with the base structure; anda canopy connected to the first and second wing tip supports,wherein the first and second wing tip supports are configured to flex in a stowed configuration and to be released from the stowed configuration to spring open into a deployed flight configuration.2. The high altitude parafoil of claim 1 , further comprising a restraint configured to restrain the first and second wing tip supports in the stowed configuration.3. The high altitude parafoil of claim 2 , wherein the restraint is a closure loop configured to restrain the canopy and the first and second wing tip supports in the stowed configuration.4. The high altitude parafoil of claim 1 , wherein the first and second elongated wing tip supports are configured to rotate freely relative to the base structure ...

SURFACE MODIFICATION OF SILICONES

A process for modifying a silicone elastomeric-based surface of a textile article where the coefficient of friction (COF) of the silicone elastomeric-based surface is generally reduced by at least 5% is disclosed. The process comprises subjecting the silicone elastomeric-based surface of the textile article to vacuum ultraviolet (UV) radiation. 1. A process for modifying a silicone elastomeric-based surface of a textile article , said process comprising:subjecting the silicone elastomeric-based surface of the textile article to vacuum ultraviolet radiation;wherein the coefficient of friction of the silicone elastomeric-based surface is reduced by at least 5%.2. The process according to claim 1 , wherein the silicone elastomeric-based surface of the textile article consists of silicone elastomer.3. The process according to claim 2 , wherein the silicone elastomer is the reaction product of a hydrosilylation or peroxide cure of an alkenyl-functional organopolysiloxane and a Si—H functional organopolysiloxane.4. The process according to claim 1 , wherein the textile article is an airbag.5. The process according to claim 1 , wherein the textile article is a silicone elastomer coated airbag.6. The process according to claim 1 , wherein the textile article is coated claim 1 , and is subsequently subjected to vacuum ultraviolet radiation.7. The process according to claim 1 , wherein the vacuum ultraviolet radiation is performed using an excimer lamp.8. The process according to claim 1 , wherein the vacuum ultraviolet radiation is performed using a lowpressure mercury lamp.9. The process according to claim 1 , wherein the vacuum ultraviolet radiation is performed on a conveyor belt.10. A textile article having a silicone elastomeric-based surface claim 1 , which surface is modified by the process according to .11. The textile article according to claim 10 , wherein the silicone elastomeric-based surface has a modified surface layer of less than 1 mm in thickness.12. ( ...

PARACHUTE SLIDER WITH STIFFENING ELEMENTS

An improved slider for use with a parachute, particularly a ram-air type parachute, is provided. The slider includes a generally rectangular piece of material having grommets in the corners through which the suspension lines of the parachute run. At least one retaining structure is attached to or made in the slider material for securing one or more stiffening elements. The stiffening elements are flexible enough to allow for the packing of the parachute, but stiff enough to keep the material of the slider spread open in the fore/aft direction across the short axis of the slider and thereby prevent the slider from folding and flapping once the canopy has opened. 1. An improved slider for use with a ram air parachute comprising a generally rectangular body having corner grommets through which suspension lines of the parachute pass , the body having a long axis and a short axis , the long axis being generally parallel with the longitudinal span of the ram air parachute canopy when fully inflated , the body having a plurality of retaining structures for securing a plurality of fore/aft extending stiffening elements , said stiffening elements keeping the slider spread open across said short axis when the ram air parachute is fully inflated to prevent folding and flapping of the slider.2. The improved slider as set forth in claim 1 , wherein the retaining structures include channels extending across the short axis of the slider body claim 1 , said stiffening elements being inserted within said channels.3. The improved slider as set forth in claim 2 , wherein the channels are sewn onto the slider body.4. The improved slider as set forth in claim 3 , wherein the stiffening elements are flexible rods made of a flexible nylon polymer monofilament.5. The improved slider according to claim 4 , wherein the flexible nylon polymer monofilament has a diameter of about 0.080 inches to about 0.155 inches.6. The improved slider as set forth in claim 1 , wherein the retaining ...

Instantaneous Wireless Network Established by Simultaneously Descending Parafoils

A method is described that involves establishing a wireless network between a wireless access node of an existing network and a remote location by wirelessly linking a plurality of electronic processing circuits each transported by a respective parafoil. The wirelessly linked processing circuits are to route packets from the wireless access node to the remote location. 1. A method comprising:establishing a wireless network between a wireless access node of an existing network and a remote location by wirelessly linking a plurality of electronic processing circuits each transported by a respective parafoil, said wirelessly linked processing circuits to route packets from said wireless access node to said remote location.2. The method of wherein said wireless network is established while said parafoils are descending.3. The method of further comprising causing said wireless network to be no longer operative before said parafoils land.4. The method of further comprising sending notice to said remote location that communication to said remote location is desired.5. The method of further comprising configuring routing tables of said electronic processing circuits.613-. (canceled) The application claims the benefit of U.S. Provisional Application No. 61/324,222 entitled, “Method and System For Optimized Terminal Guidance Of Autonomous Aerial Delivery Systems”, filed on Apr. 14, 2010 and U.S. Provisional Application No. 61/324,551 entitled, “Method and System for Improving Touchdown Accuracy Of Aerial Payload Delivery Using Ground Weather Station Uplink”, filed on Apr. 15, 2010, and U.S. Provisional Application No. 61/323,792 entitled, “Method and System For Control Of Autonomous Aerial System via GSM Cellular Network”, filed on Apr. 13, 2010 and U.S. Provisional Application No. 61/323,750 entitled, “Method and System For Establishing A Short-term Network Mesh Using Miniature Autonomously Guided Parafoils”, filed on Apr. 13, 2010 and U.S. Provisional Application No. 61/323 ...

Aerial delivery system

An aerial delivery box for release from an aircraft comprises a hold for a payload; and an impact absorbing zone for protecting the payload of the hold. The hold and the impact absorbing zone are formed of biodegradable materials. The impact absorbing zone comprises at least one layer having a honeycomb structure, the honeycomb structure defining a cellular network extending in the plane of the layer. Also disclosed is an aerial delivery assembly comprising: the aerial delivery box; a parachute; and a plurality of shroud lines connecting the parachute to the aerial delivery box. Also disclosed is a method of delivering goods by aerial delivery, comprising releasing the aerial delivery assembly from an aircraft. The aerial delivery assembly may be released from a cargo pod of an aircraft, in particular a cargo pod comprising: a first casing attached to the aircraft; and a second casing attached to the first casing rearwardly of the first casing. The first and second casings define an opening to receive the assembly. The second casing is adapted to be releasable from the first casing so as to expose the parachute and thereby allow the parachute to inflate and extract the aerial delivery box from the first casing.

Systems and methods for using computer vision for parafoil flight control

Disclosed herein are systems and methods for using computer vision for parafoil flight control. According to an aspect, a method includes capturing an image of a parafoil including multiple indicator points distributed thereon. The method further includes determining positioning of the indicator points based on the captured image. The method further includes determining a condition of the parafoil based on the positioning of the indicator points. The method further includes controlling flight inputs based on the condition of the parafoil.

CINCHED PARACHUTE

A cinched parachute is disclosed. In various embodiments, a cinched parachute as disclosed herein includes a canopy comprising one or more sections of canopy material, and a device integrated with the canopy that controls dimensions of the canopy material. For example, in some embodiments the device may be used to control the size of an opening atop the parachute. 1. A cinched parachute , comprising:a canopy comprising one or more sections of canopy material; anda device integrated with the canopy that controls dimensions of the canopy material.2. The cinched parachute of claim 1 , wherein the device comprises a control tether.3. The cinched parachute of claim 1 , wherein the device is threaded through the parachute.4. The cinched parachute of claim 1 , wherein the device controls a size of an opening atop the parachute.5. The cinched parachute of claim 1 , wherein the device is positioned between tethers of the parachute and an opening atop the parachute.6. The cinched parachute of claim 1 , wherein the device is positioned to pull a section of the canopy material into a packed state.7. The cinched parachute of claim 1 , wherein the device traverses a casing in the canopy of the parachute.8. The cinched parachute of claim 2 , wherein at least one end of the control tether is secured in a holding device that releases or pulls in the control tether.9. The cinched parachute of claim 8 , wherein the holding device allows the control tether to travel in one direction and not in a reverse direction through the holding device.10. The cinched parachute of claim 8 , wherein the holding device comprises a brake pad or a clamp.11. The cinched parachute of claim 8 , wherein the holding device is positioned on or in an object that is tethered to the parachute.12. The cinched parachute of claim 8 , wherein the holding device is positioned adjacent to the canopy of the parachute.13. The cinched parachute of claim 2 , wherein the control tether is positioned such that a severing ...

WIND ESTIMATION USING REMOTELY-DROPPED DROPSONDE

Payload delivery to a drop zone includes selecting a remote location at which to measure a remote wind stick and doing so based at least in part on current weather conditions. This is followed by determining a release point, flying to it, and then dropping the payload from the release point. Determining the release point includes estimating a wind stick at the drop zone based at least in part on the measurement of the remote wind stick. 1. A method comprising delivering a payload to a drop zone , wherein delivering said payload comprises based at least in part on current weather conditions , selecting a remote location at which to measure a remote wind stick , determining a release point , flying to said release point , and dropping said payload from said release point , wherein determining said release point comprises estimating a wind stick at said drop zone based at least in part on said measurement of said remote wind stick.2. The method of claim 1 , wherein selecting said remote location at which to measure said remote wind stick comprises selecting said remote location at least in part on the basis of a confidence level of said estimate of said wind stick at said drop zone.3. The method of claim 2 , further comprising determining said confidence level at least in part on the basis of current weather conditions.4. The method of claim 1 , further comprising releasing a dropsonde at said remote location claim 1 , collecting data from said dropsonde claim 1 , and determining said release point based at least in part on said collected data.5. The method of claim 1 , wherein determining said release point comprises providing said remote wind stick to an operational model that has been configured to provide a transformation based on historical weather data and applying said transformation to said remote wind stick to obtain an estimate of a drop-zone wind stick at said drop zone.6. The method of claim 5 , further comprising obtaining said operation model by providing ...

DANGER AVOIDANCE APPARATUS AND METHOD OF USE

The present disclosure provides danger avoidance apparatuses and related methods, such as for use to avoid avalanches. An apparatus may include a container configured to couple to a user, a lift providing mechanism, a descent control mechanism and at least one rip cord engaged with the container and selectively operable by the user. Both the lift providing mechanism and the descent control mechanism may be movably coupled to the container between a packed position within the container and a deployed position exterior to the container controlled via the at least one rip cord. The lift providing mechanism may include an airfoil that provides lift to the user at a first velocity of the user along a first direction. The descent control mechanism may control the descent and reduce the velocity of the user along the first direction from the first velocity in the deployed position. 1. A danger avoidance apparatus , comprising:a container configured to couple to a user;a lift providing mechanism movably coupled to the container between a packed position within the container and a deployed position exterior to the container including an airfoil that provides lift to the user at a first velocity of the user along a first direction;a descent control mechanism movably coupled to the container between a packed position within the container and a deployed position exterior to the container that controls the descent and reduces the velocity of the user along the first direction from the first velocity; andat least one rip cord engaged with the container and selectively operable by the user,wherein the at least one rip cord is configured to activate the lift providing mechanism from its packed position to its deployed position and subsequently activate the descent control mechanism from its packed position to its deployed position upon the selective operation of the at least one rip cord by the user.2. The apparatus of claim 1 , wherein the lift providing mechanism and the descent ...

Trimming device for controlling the glide slope and descent speed of a parafoil

A parafoil system having an adjustable trim angle during flight to control glide slope and descent speed of a parafoil is provided. The parafoil system may include a pulley cluster comprising first and second variable trim pulleys, each having a different diameter. The pulley cluster may be coupled to forward and aft suspension lines of a parafoil canopy such that the pulley cluster may rotate to retract or extend the forward and aft suspension lines to adjust the trim angle during flight. The parafoil system may further include a motor for rotating the pulley cluster to extend or retract the suspension lines to adjust the trim angle during flight. By adjusting the trim angle of the canopy during flight, the glide slope and descent speed of the parafoil system may be controlled.

Aerial vehicle safety apparatus and aerial vehicle

An aerial vehicle safety apparatus includes an expandable object, an ejection apparatus, a bag-shaped member, and a gas generator. The expandable object is wound or folded in a non-expanded state and generates at least any of lift and buoyancy in an expanded state. The ejection apparatus is coupled to the expandable object by a coupling member and ejects the non-expanded expandable object into air. The bag-shaped member is provided in the expandable object and wound or folded together with or separately from the non-expanded expandable object, and expands the non-expanded expandable object by at least partially being inflated like a tube. The gas generator is provided in the expandable object and inflates the bag-shaped member by causing gas generated at the time of activation to flow into the bag-shaped member.

GLIDE MODULATOR SYSTEM AND METHOD FOR A RAM AIR PARACHUTE

A system and method is provided for shortening specific suspension lines near the center of a ram air parachute in order to distort the airfoil section only in the center section of the canopy. This distortion of the center section results in a significant alteration of the glide ratio of the parachute by simultaneously reducing the forward speed and increasing the rate of descent. Meanwhile, because the canopy is only distorted in the center section, the wingtips remain extended and pressurized so that the steering apparatus at the trailing edge of the canopy remains fully functional to direct the heading. 1. A glide path modulation system for a personnel ram air gliding parachute or a cargo ram air gliding parachute comprising:a ram air gliding parachute having a canopy, a plurality of B lines extending across a span of said canopy, and a plurality of C lines extending across said span of said canopy and located rearwardly of said plurality of B lines with respect to a leading edge of the parachute, said B lines including a first pair of B lines nearest a center section of said canopy along said span, one of said first pair of B lines being attached to the canopy on either side of a center cell, and at least a second pair of B lines spaced outwardly from said first pair of B lines on either side of the canopy, said C lines including a first pair of C lines nearest a center section of said canopy along said span, one of said first pair of C lines being attached to the canopy on either side of the center cell, and at least a second pair of C lines spaced outwardly from said first pair of C lines;a steering apparatus located at the trailing edge of said canopy, said trailing edge steering apparatus being used to steer the parachute; anda device activated during flight to shorten said first pair of B lines only in the center section of the canopy and/or said first pair of C lines only in the center section of the canopy in order to distort only the center section of ...

TAILED PARACHUTE-PARAGLIDER

Tailed parachute-paraglider () comprising a first portion (A) of a substantially squared/rectangular shape with sides () two by two substantially parallel and opposed, and a second portion (B) with trapezoidal shape, comprising a couple of opposite parallel sides with the longest side of said couple of opposite parallel sides jointed to a side of said first portion (A) and the smallest side of said couple of opposite parallel sides comprising wires suitable for being jointed to legs and/or feet of a user (); said second portion (B) being rotatable substantially around a transverse axis (Y) orthogonal to a longitudinal plane (X-X) of said tailed parachute-paraglider (), wherein said transverse axis is substantially coinciding with said longest side of said couple of opposite sides and with a side of said first portion (A). 1. Tailed improved parachute-paraglider , characterized in that it comprises a first portion (A) with substantially squared/rectangular shape as top view , the front portion respective to an advancement direction F , with sides two by two substantially parallel and opposed and a second portion (B) with trapezoidal shape as top view , the rear portion , comprising a couple of opposite sides of which a first bigger side of said couple of opposite sides coincides to a side of said first portion (A) and a second smaller side of said couple of opposite sides comprising wires suitable for being jointed indirectly to legs and/or feet of a user; the whole or a part of said second portion (B) and eventually whole second portion (B) and part of the first portion (A) from limit-barycentric band to the bigger side of the second portion (B) rotates around an ideal axis (Y) , a transversal axis of said improved parachute-paraglider.2. Tailed improved parachute-paraglider according to claim 1 ,characterized in that it comprises at least a bundle of reinforcement radials, a band passing for the centre of mass in a “flat” situation and for a firmer and secure ...

AERIAL VEHICLE

An aerial vehicle comprising: a source of thrust, for propelling the vehicle forwards; and a canopy attachment arrangement having at least one securement point for at least one line of a canopy securable to the vehicle in use for providing lift to the vehicle, wherein the canopy attachment arrangement is configured such that the at least one securement point is movable between a first position below the line of thrust and a second position above the line of thrust.

Rigidized Assisted Opening System for High Altitude Parafoils

A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle. 1. A method of opening a parafoil comprising a canopy and a plurality of flexible members , the method comprising:deforming the flexible members, thereby storing elastic potential energy in the flexible members, wherein a top end of each flexible member is connected to the parafoil canopy;securing the parafoil canopy and the deformed flexible members in a stowed configuration;attaching the parafoil to a flight vehicle;detaching the parafoil from the flight vehicle;releasing the parafoil canopy and the flexible members; andthe flexible members returning to their undeformed shape, thereby at least partially deploying the parafoil canopy.2. The method of wherein a base end of each flexible member is connected to a base member connected to a payload.3. The method of wherein a base end of each flexible member is connected to the base member via a hinge.4. The method of comprising one or more suspension lines claim 2 , but not all suspension lines claim 2 , supporting the weight of the payload during flight of the flight vehicle claim 2 , the suspension lines connecting the ...

Transportation Services for Pod Assemblies

In some embodiments, a pod assembly transportation system includes a transportation services provider computing system and a plurality of flying frame flight control systems, wherein the system is configured to receive, at the transportation services provider computing system, a request for transportation of a pod assembly; upload a flight plan to a flight control system of a flying frame including an airframe and a distributed propulsion system coupled to airframe; dispatch the flying frame by air to the current location of the pod assembly; couple the pod assembly to the flying frame; transport the pod assembly by air from the current location of the pod assembly to the destination of the pod assembly including transitioning the flying frame between a vertical takeoff and landing mode and a forward flight mode; and decouple the pod assembly from the flying frame at the destination of the pod assembly.

RIGIDIZED ASSISTED OPENING SYSTEM FOR HIGH ALTITUDE PARAFOILS

A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle 1. A high altitude parafoil comprising:a base structure;a first elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical direction, the first wing tip support comprising a first flexible rod configured to flex to store energy of flexure;a second elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to the vertical direction, the second wing tip comprising a second flexible rod configured to flex to store energy of flexure; anda canopy extending between a first wingtip end and a second wingtip end opposite the first wingtip end, the first wingtip end of the canopy coupled with the upper end of the first wing tip support, and the second wingtip end of the canopy coupled with the upper end of the second wing tip support,wherein the parafoil is configured to be restrained in a stowed configuration and to be released from the stowed configuration to ...

RISER RELEASE FLARING SYSTEM FOR PARAFOILS

Described herein are features for a riser release flaring system for parafoils and other descent flight vehicles for controlled descent and landing of the flight vehicle. The descent flight vehicle may have a payload suspended by a canopy. The descent flight vehicle may be released from a high altitude lighter-than-air (LTA) system, from another system, or may not be associated with any other flight system. The riser release auto flare system is used with the descent system, such as the parafoil, for controlled and safe landing of the payload. Riser lines are released at a controlled rate and for a fixed distance to automatically cause the payload to pull control lines to flare the parafoil and slow a descent and/or forward speed of the vehicle. The riser lines may be released in response to the descent system satisfying a landing criterion, such as altitude. 1. A riser release system for controllably landing a descending flight vehicle , the flight vehicle having a payload suspended underneath a parafoil canopy wherein the parafoil canopy has a leading edge and a trailing edge or tail , the riser release system comprising:a plurality of control lines, each control line having a first end fixedly connected with the tail of the canopy and a second end fixedly connected with the payload;a plurality of riser lines, each riser line having a first end fixedly connected with the canopy and a second end; and an upper bracket fixedly connected to the riser line second ends;', 'a lower bracket fixedly connected to the payload;', 'a coupling mechanism releasably coupling the upper bracket to the lower bracket;', 'a de-coupling mechanism for de-coupling the upper bracket from the lower bracket and configured to cause the upper bracket to separate a distance from the lower bracket;', 'a distance control device for controlling the distance of separation of the brackets; and', 'a rate control device coupled to at least the upper bracket and configured to resist separation and ...

Canopy control system

Provided herein is a canopy control system comprising a yoke, configured to be pivotably securable to a vehicle and securable to a line system of a canopy in use, such that the yoke pivots with respect to the vehicle in a first direction when the canopy is subjected to a wind force; and a control mechanism configured to apply a control force to the canopy line system to cause the canopy to oppose the wind force, such that yoke pivots with respect to the vehicle in a second direction which is opposite to the first direction.

DANGER AVOIDANCE APPARATUS AND METHOD OF USE

The present disclosure provides danger avoidance apparatuses and related methods, such as for use to avoid avalanches. An apparatus may include a container configured to couple to a user, a lift providing mechanism, a descent control mechanism and at least one rip cord engaged with the container and selectively operable by the user. Both the lift providing mechanism and the descent control mechanism may be movably coupled to the container between a packed position within the container and a deployed position exterior to the container controlled via the at least one rip cord. The lift providing mechanism may include an airfoil that provides lift to the user at a first velocity of the user along a first direction. The descent control mechanism may control the descent and reduce the velocity of the user along the first direction from the first velocity in the deployed position. 1. A danger avoidance apparatus , comprising:a container configured to couple to a user;a combined lift providing and descent control mechanism movably coupled to the container between a packed position within the container and a deployed position exterior to the container, the combined lift providing and descent control mechanism comprising an airfoil portion that provides lift to the user at a first velocity of the user along a first direction to elevate the user from on a ground surface to an elevated position above the ground surface, and a canopy portion that reduces the velocity and controls descent of the user along the first direction from the first velocity and the elevated position; andat least one activation member engaged with the container and selectively operable by the user,wherein the at least one activation member is configured to activate the lift providing and descent control mechanism from its packed position to its deployed position upon the selective operation of the at least one activation member by the user.2. The apparatus of claim 1 , wherein the combined lift providing ...

CONTAINER FOR AERIAL DELIVERY

A container for aerial delivery of a payload is disclosed. The container is comprised of a fixed box, a lid adapted to close the fixed box, and a sleeve surrounding the fixed box. The sleeve is movable between a first, collapsed position and a second, extended position. 1. A container for aerial delivery of a payload , comprising:a fixed box;a lid adapted to close the fixed box;a sleeve surrounding the fixed box, wherein the sleeve is open on at least one end and is movable between a first, collapsed position and a second, extended position; andat least one one-way slide sheet positioned between the fixed box and the sleeve, the one-way slide sheet comprising a first component positioned on the fixed box and a second component poisoned on the sleeve;wherein the on-way slide sheet is adapted to allow unrestricted movement of the sleeve toward the second position and resists movement of the sleeve toward the first position during impact with the ground.2. The container of claim 1 , wherein the sleeve is maintained in the first position during storage and transportation and transitions to the second position during aerial deployment of the container.3. The container of claim 2 , wherein upon impact with the ground claim 2 , the sleeve is forced into the first position.4. The container of claim 3 , wherein the movement of the sleeve from the second position to the first position during impact with the ground slows the decent of the container and reduces impact forces over the impact forces experienced by a container without the sleeve impacting the ground.5. The container of claim 1 , wherein one one-way slide sheet is positioned at each corner of the fixed box.6. The container of claim 1 , wherein:the first component poisoned on the fixed box is a loop pile fabric; andthe second component positioned on the sleeve is a molded strip having direction hoods facing in one direction.7. The container of claim 2 , further comprising at least one pull strap coupled to the fixed ...

PARACHUTE DEVICE, FLIGHT DEVICE, AND FLYING BODY EJECTION MECHANISM

To prevent a parachute from being damaged. A parachute device () includes a flying body () including a parachute (), a parachute accommodation section () configured to accommodate the parachute, at least one flying body () connected to the parachute, an ejection section () having a tube shape and configured to hold the flying body and to eject the held flying body, a gas generating device () configured to generate gas, and an extrusion member () capable of being at least partially inserted into the ejection section, the extrusion member being configured to extrude the flying body from the ejection section due to receiving pressure of the gas generated from the gas generating device. 18-. (canceled)9. A parachute device comprising:a parachute;a parachute accommodation section configured to accommodate the parachute;at least one flying body connected to the parachute;an ejection section having a tube shape and configured to hold the flying body and to eject the flying body held;a gas generating device configured to generate gas;an extrusion member capable of being at least partially inserted into the ejection section, the extrusion member being configured to extrude the flying body from the ejection section due to receiving pressure of the gas generated from the gas generating; anda movement limiting section configured to limit a range of movement of the extrusion member, whereinthe parachute accommodation section includesa side wall portion being continuous in a circumferential direction and having a tube shape, anda bottom portion formed to block an opening at one end side of the side wall portion,the parachute is disposed in an accommodation space defined by the side wall portion and the bottom portion, andthe ejection section is disposed at an outer circumferential surface of the side wall portion.10. The parachute device according to claim 9 , further comprising:a gas introduction path configured to introduce the gas generated from the gas generating device to ...

Polyolefin film having an improved adhesive layer for airbag applications

The present invention provides a two layer polyolefin film including a polymer barrier layer, and an adhesive layer including a polyolefin grafted with maleic anhydride and ungrafted polyolefins. The adhesive layer has a maleic anhydride surface concentration (cm) from about.025 g/m2 to about.250 g/m2 calculated according to the surface concentration formula cm = fm x fg x fa x pff x tf wherein fm is the weight fraction of the maleic anhydride in the grafted polyolefins, fg is the weight fraction of the grafted polyolefins in the adhesive layer, fa is the weight fraction of the adhesive layer in the film, pf is the density of the film, and tf is the total thickness of the film. The two layer polyolefin film is bonded to synthetic fabric, such as nylon or polyester, and useful for airbag applications.

Aircraft equipped with auxiliary flight node

FIELD: aviation. SUBSTANCE: remotely piloted aircraft contains a main power plant with at least one engine suitable for rotating multiple propellers, a main control unit containing at least one receiver capable of receiving commands from a remote control unit, an auxiliary flight node with an additional control unit capable of processing flight-related data, which includes an additional receiver capable of receiving commands from an additional remote control unit, it also contains an upper wing, a lower wing and a device for ejecting the upper wing and inflating the lower wing placed in a certain way. EFFECT: increase in landing safety is provided for the aircraft and for people under it. 12 cl, 10 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 767 803 C2 (51) МПК B64C 39/02 (2006.01) B64D 17/80 (2006.01) B64D 25/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B64C 39/02 (2021.05); B64D 17/80 (2021.05); B64D 25/00 (2021.05) (21)(22) Заявка: 2019130663, 27.02.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): РПС АЭРОСПЕЙС С.Р.Л. (IT) 22.03.2022 01.03.2017 IT 102017000022745 (43) Дата публикации заявки: 01.04.2021 Бюл. № 10 (56) Список документов, цитированных в отчете о поиске: RU 2527633 C1, 10.09.2014. RU 2094325 C1, 27.10.1997. EP 3093239 A1, 16.11.2016. US 6416019 B1, 09.07.2002. WO 2016141928 A1, 15.09.2016. (45) Опубликовано: 22.03.2022 Бюл. № 9 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 01.10.2019 2 7 6 7 8 0 3 Приоритет(ы): (30) Конвенционный приоритет: R U 27.02.2018 (72) Автор(ы): ЛУНЕРТИ, Джакомо (IT), ВЕЦЦОЛИ, Навзикая Азия (IT), БЕРНА, Андреа (IT) IB 2018/051236 (27.02.2018) C 2 C 2 (86) Заявка PCT: (87) Публикация заявки PCT: R U 2 7 6 7 8 0 3 WO 2018/158686 (07.09.2018) Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, стр. 3, ООО "Юридическая фирма Городисский и Партнеры" (54) ЛЕТАТЕЛЬНЫЙ АППАРАТ, СНАБЖЕННЫЙ ...

Multi-canopy wing system

FIELD: aviation. SUBSTANCE: invention relates to the field of means of flight. Wing system for use in a paraglider, parachute, or hang glider consists of wings with convex-plane, curved-plate, rigid or soft wing profiles. Wings of a greater elongation, installed at predetermined attack angles for gliding, and forming a predetermined pitch angle in space by the trailing edges of the wings, are fastened by lateral stabilisers into a multi-wing canopy so as to approximately equalise the width and the length of the wing canopy. The lateral stabilisers are installed at predetermined attack angles for the vertical and horizontal components of dynamic pressure. The multi-wing canopy of the wing system can be assembled by the sling, suspension, and control systems into a paraglider, a hang glider, or a parachute. EFFECT: increase in the lift. 4 cl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 770 501 C2 (51) МПК B64D 17/02 (2006.01) B64C 31/028 (2006.01) B64C 31/036 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК B64D 17/02 (2021.08); B64C 31/028 (2021.05); B64C 31/036 (2021.05); Y10S 244/90 (2021.05) (21)(22) Заявка: 2020129374, 05.09.2020 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Решетников Михаил Иванович (RU) Дата регистрации: 18.04.2022 (43) Дата публикации заявки: 05.03.2022 Бюл. № 7 (45) Опубликовано: 18.04.2022 Бюл. № 11 2 7 7 0 5 0 1 R U (54) Многокупольная крыльевая система (57) Реферат: Изобретение относится к области средств полета. Крыльевая система для использования в параплане, парашюте или дельтаплане состоит из крыльев с плосковыпуклыми, пластиноизогнутыми, жесткими или мягкими профилями крыла. Крылья большего удлинения, которые установлены под заданными углами атаки для планирования и образуют в пространстве заданный угол тангажа по задним кромкам крыльев, скреплены боковыми стабилизаторами Стр.: 1 в многокрыльевой купол так, чтобы примерно уравнять ширину и ...

Parachute canopy

내용 없음

High cylinder hat type low altitude lifesaving umbrella

本发明公开了一种高筒帽式低空救生伞，包括环形支撑架、与环形支撑架中心相连接的帽型固定带、铺设在支撑架上的伞面、与伞面中心相连接的高筒帽式鼓风包、铺设在支撑架处的伞面上设有与支撑架固定的径向加固带、与伞面中心连接的高强度抗拉伸的软绳；在伞的外缘绳的下半部四个方位各设有一组手动拉环可以调节降落方向，这些外缘绳底部与中心绳相连接，并在结扣处设有一个挂设安全带的钢环。在待用状态下，伞面的长出支撑架的外沿部分被折叠后，装在由高筒帽式鼓风包折叠下来用若干按扣(磁铁、粘扣)连接组成的口袋中。本发明可以解决高层建筑在出现灾难时，能够自救逃生的技术问题。

Kite type sail with improved line attachment

The invention relates to an aerodynamic wing, comprising an upper deck, wherein a plurality of ribs are connected to the upper deck, said ribs lying in a plane parallel to the direction of the vertical lifting force and the direction of the wind flow; the aerodynamic wing being coupled to a base platform arranged below the wing in service via a plurality of fastening lines, whereby the fastening lines are secured to the ribs of the wing, at least two fastening lines are secured to one rib at two line attachment points arranged at a distance from each other in the longitudinal direction; wherein the at least two line attachment points are connected to each other by a reinforcing load transfer line extending from the line attachment point of the first one of the two fastening lines to the line attachment point of the second one of the two fastening lines; whereby the reinforcing load transfer line is attached to the respective rib along substantially the whole length of the load transfer line and follows a curved path along the rib.

Mastless sails

Mastless sails for a boat or ship which comprise sails having capability for utilizing static and dynamic lift in combination with drag, gravity, and line tension to provide stability and propulsion forces for the boat or ship, communication capability located near said sails when aloft for use for said boat or ship, sensing capability located near said sails when aloft for use by said boat or ship, and apparatus for raising and lowering the communication and sensing apparatus.

Aerodynamic wing with improved line attachment

The invention relates to an aerodynamic wing, including an upper deck extending in operation in a longitudinal direction and in a transversal direction; wherein the upper deck is shaped and arranged to produce a vertical lifting force which is oriented perpendicular to the longitudinal and the transversal direction when the aerodynamic wing is exposed to a wind flow in a direction oriented parallel to the longitudinal direction; wherein a plurality of ribs are connected to the upper deck, said ribs lying in a plane parallel to the direction of the vertical lifting force and the direction of the wind flow; the aerodynamic wing being coupled to a base platform arranged below the wing in service via a plurality of fastening lines, whereby the fastening lines are secured to the ribs of the wing, at least two fastening lines are secured to one rib at two line attachment points arranged at a distance from each other in the longitudinal direction; wherein the at least two line attachment points are connected to each other by a reinforcing load transfer line extending from the line attachment point of the first one of the two fastening lines to the line attachment point of the second one of the two fastening lines; whereby the reinforcing load transfer line is attached to the respective rib along substantially the whole length of the load transfer line and follows a curved path along the rib.

Aircraft with auxiliary flight assembly

遠隔操縦航空機（１）は、航空機（１）の故障の場合又は緊急事態の際に介入するように適合されている副飛行アセンブリ（４）を備える。前記副飛行アセンブリ（４）は、飛行に関連するデータを処理するように構成されている追加制御部（５）と、遠隔地のパイロットから遠隔制御装置を介してコマンドを受信するように構成されている追加受信器（２７）とを備える。故障又は緊急事態の際に、前記追加制御部（５）は、応答として、前記航空機（１）の第１区画（１２）に配置された上翼（９）の排出し、前記航空機（１）の第２区画（２５）に収容された下翼（１７）の膨張するための第１装置（８）の作動に適した作動コマンド（Ｓ１）を発生するとともに、主推進部（２３）の停止コマンド（Ｓ２）を生成する。前記上翼（９）は、更なる遠隔制御部（７０）を介して操縦可能である。【選択図】図６

SAFETY DEVICE FOR CONFIGURING THE FLIGHT OF PLANING WINGS, OF THE WING TYPE, FOR THE PRACTICE OF ASCENSIONAL PARACHUTISM AND SLOPE FLIGHT.

Patent JPS59501742A

(57)【要約】本公報は電子出願前の出願データであるため要約のデータは記録されません。

PROPULSIVE WING

L'INVENTION CONCERNE UNE AILE TRES LEGERE, EVOQUANT UN FUSEAU SPHERIQUE, DESTINEE A LA TRACTION ET A LA SUSTENTATION DE CHARGES DIVERSES. CETTE AILE COMPORTANT UN BORD D'ATTAQUE 1 ET UN BORD DE FUITE 2, EST MATERIALISEE PAR UNE ARMATURE GONFLABLE 3 ET 4 RECOUVERTE D'UNE ENVELOPPE SOUPLE 5 EN INTRADOS I COMME EN EXTRADOS S, AGENCEE DE FACON A OBTENIR UN PROFIL D'AILE D'AVION. CHACUNE DE SES POINTES 6 RECOIT PAR L'INTERMEDIAIRE D'UNE PLAQUETTE DE REGLAGE 7 L'UNE DES DEUX EXTREMITES DU FILIN DE COMMANDE 8. CELUI-CI PASSE DANS UNE POULIE FIXEE SUR L'ENGIN A DEPLACER, OU SUR UNE PERSONNE PAR L'INTERMEDIAIRE D'UN HARNAIS. DE PAR SA SIMPLICITE DE CONCEPTION ET D'UTILISATION, L'AILE A DE NOMBREUSES APPLICATIONS POSSIBLES DONT LES PLUS EVIDENTES CONCERNENT LES SPORTS DE GLISSE, LE YACHTING, LE VOL A VOILE. THE INVENTION CONCERNS A VERY LIGHT WING, EVALUATING A SPHERICAL SPINDLE, INTENDED FOR THE TRACTION AND THE SUSTENTATION OF VARIOUS LOADS. THIS WING INCLUDING A TAKING EDGE 1 AND A TRAINING EDGE 2, IS MATERIALIZED BY AN INFLATABLE ARMATURE 3 AND 4 COVERED WITH A SOFT ENVELOPE 5 IN INTRADOS I AS IN EXTRADOS S, ARRANGED SO AS TO OBTAIN A WING PROFILE PLANE. EACH OF ITS POINTS 6 RECEIVES THROUGH AN ADJUSTING PLATE 7 ONE OF THE TWO ENDS OF THE CONTROL WIRE 8. THIS PASSES THROUGH A PULLEY FIXED ON THE MACHINE TO BE MOVED, OR ON ONE PERSON PER L 'INTERMEDIATE OF A HARNESS. BY ITS SIMPLICITY OF DESIGN AND USE, THE KING HAS MANY POSSIBLE APPLICATIONS OF WHICH THE MOST OBVIOUS ARE RELATED TO BOARDING SPORTS, YACHTING, SAILING.

Parachute of the flexible, box-structure wing type

Parachute of the flexible box-structure wing type comprising flexible elements linking the boxes 1 to means for attaching a load, as well as means, 11, 4, 13, 14 allowing a cable C to be attached the other end of which may be linked to a fixed or movable point, characterised in that the means 11, 4, 13, 14 for attaching the said cable C are arranged in such a way that the line of action of the cable C when the wing is balanced passes through a point H which is situated substantially between the centre of lift P and the mid-point B of the attachment means, with PH lying between a quarter and three-quarters of the length PB. Autostability of the parachute according to the invention.

Integral harness for paraglider pilot.

CLOSED EDGE ON WING PARACHUTE.

Towing wing with negative dihedral, e.g. for kite surfing, has transverse supple line to vary distance between ends of wing for enhanced stability

The wing (18) consists of an inflatable structure (20) with a curved leading edge (22) and has a transverse line (70) connected to two points (72A, 72B) located symmetrically on opposite sides of the wing to draw them together. At least one of the points (72A, 72B) is in the form of a loop through which the line passes and is connected to a control line (44A, 44B). The wing's inflatable structure comprises a main tube (28) along its leading edge and a number of transverse tubes (30) scross it from the leading edge.

DEVICE FOR STEERING AN INFLATABLE VEHICLE.

Parachute for aviator

RIGID WING WITH INFLATABLE FRAME WITH TENSIONED MEMBRANE

SURFACE REDUCTION DEVICE FOR FLEXIBLE DOUBLE SURFACE WINGS

Closed leading edge on parachute-wing

L'INVENTION CONCERNE UN DISPOSITIF PERMETTANT D'AMELIORER LES CARACTERISTIQUES AERODYNAMIQUES D'UNE AILE A STRUCTURE SOUPLE OU SEMI-RIGIDE. IL EST CONSTITUE PAR LA FERMETURE TOTALE OU PARTIELLE DU BORD D'ATTAQUE PAR DES SURFACES EN TISSU OU MATERIAUX SOUPLES. LE GONFLAGE DE LA PARTIE FERMEE PEUT S'EFFECTUER PAR DES OUVERTURES PRATIQUEES LATERALEMENT OU SUR LES SURFACES D'INTRADOS OU (ET) D'EXTRADOS. LE DISPOSITIF, SELON L'INVENTION, CONCERNE LES AILES DE TYPE PARACHUTE-AILE, PARACHUTE DE PENTE.

Parachute for aviator

RIGID WING WITH INFLATABLE FRAME WITH TENSIONED MEMBRANE

The invention concerns a wing with membrane rigidified by the pressure of its inflatable armature. The wing consists of a leading edge and inflatable strips designed and arranged so that the pressure generates tension over the whole assembly of the wing surface and in three dimensions. Said wing can be used as a sport implement and more particularly for water sports, such as FLYSURF or KITESURF.

Improvements to parachutes

PROPULSIVE WING WITH NEGATIVE DIEDRE

Patent FR2420481B1

WIND PROPULSION GLIDER

PARACHUTE OF THE FLEXIBLE BOX TYPE WING

SAIL

An inflatable device is specified which has at least two surfaces (1, 2) which are each in the form of at least one bulge (dome) (3, 4, 6, 7), the surfaces (1, 2) being connected to one another at the ends of their respective bulges (3, 6; 4, 7) and being separated from one another between the ends, in order to form interspaces (intermediate spaces) (9, 10) for a fluid passing through, the concave sides of the bulges being directed in the same direction. Fields of application include, in particular, parachutes, hang gliders, portable items of clothing for jumping from heights and propulsion sails for maritime or land vehicles.

Sealed-cell device for paragliders

The invention relates to a device making it possible to enhance the performance of a paraglider by thinning its profile while preventing it deflating. It consists of 2 or more cells per box structure: a front cell 1 which is open to the front 4 and a rear cell 2 with underside air intakes 5, with or without non-return valves 15, which is composed of a flap 16 linked to the underside 12 by stitching 17 and lanyards 10 which can be fitted with a deflating lanyard 11 passing through the upper surface 13. This valve 15 may also be fixed onto inter-cell apertures 6. The device according to the invention is particularly intended for enhancing flight by a paraglider.

SAFETY DEVICE FOR THE AIR SUPPLY OF A PARAGLIDER PROFILE.

BIONIC PARAGLIDER WITH MODULAR WING

WING PARACHUTE VALVE.

Parachute

DEVICE FOR CONTROLLING AN INFLATABLE VESSEL.

L'invention concerne un dispositif pour piloter une voilure gonflable de type parapente ou parachute par déplacement du centre de gravité du pilote. Il est constitué de transversales (3) et (4) auxquelles sont fixées les faisceaux de suspentes avant (1) et arrière (2). Des traverses rigides (7) maintiennent l'écartement des transversales et reçoivent les éléments de pilotaae (5) et le point d'ancrage (6) du pilote au dispositif. Le déplacement du centre de gravité du pilote est obtenu par action sur les éléments de pilotage (5). Le pilotage de la voilure gonflable s'apparente au pilotage pendulaire des deltaplanes. Le dispositif selon l'invention est particulièrement destiné au pilotage de voilures gonflables par déplacement du centre de gravité du pilote. The invention relates to a device for piloting an inflatable wing of the paraglider or parachute type by displacement of the pilot's center of gravity. It consists of transverse (3) and (4) to which the front (1) and rear (2) hanger bundles are attached. Rigid cross members (7) maintain the spacing of the cross members and receive the pilotaae elements (5) and the anchor point (6) of the pilot to the device. The displacement of the pilot's center of gravity is obtained by acting on the piloting elements (5). The piloting of the inflatable canopy is similar to the pendular piloting of hang-gliders. The device according to the invention is particularly intended for the piloting of inflatable wings by displacement of the pilot's center of gravity.

Parachute training

SADDLE HARNESS FOR PARACHUTE OF THE FLEXIBLE WING TYPE

Parachute

Arrangement comprising a flexible and deformable sheet-type support, a traction strand and an arcuate force distribution part, harness for paraglider and paraglider

Un agencement (10) comprend un support (11) sous la forme d’une nappe constituée dans un matériau souple et déformable et au moins un brin de traction (12) solidaire du support (11) dans une zone prédéterminée (13) du support (11) et destiné à exercer une force de traction (F) sur le support (11) au niveau de la zone prédéterminée (13). A proximité de la zone prédéterminée (13) du support (11), l’agencement (10) comprend une pièce de diffusion d’efforts (14) associée audit brin de traction (12), la pièce de diffusion d’efforts (14) étant solidaire du support (11), formée par un profilé constitué dans un matériau élastiquement déformable et conformé selon une forme arquée. La pièce de diffusion d’efforts (14) est orientée par rapport au support (11) de sorte que la zone prédéterminée (13) est agencée du côté de la concavité délimitée par la forme arquée et de sorte que la pièce de diffusion d’efforts (14) est globalement orientée transversalement à la direction suivant laquelle la force de traction (F) est susceptible d’être appliquée par le brin de traction (12). Il est décrit aussi une sellette (100) et un parapente (200). Figure 2 An arrangement (10) comprises a support (11) in the form of a web made of a flexible and deformable material and at least one traction strand (12) integral with the support (11) in a predetermined area (13) of the support (11) and intended to exert a tensile force (F) on the support (11) at the level of the predetermined zone (13). Close to the predetermined zone (13) of the support (11), the arrangement (10) comprises a force diffusion part (14) associated with said traction strand (12), the force diffusion part (14). ) being integral with the support (11), formed by a section made of an elastically deformable material and shaped in an arcuate shape. The force diffusion part (14) is oriented relative to the support (11) so that the predetermined zone (13) is arranged on the side of the concavity delimited by the arcuate shape and so ...

AERIAL LOCOMOTION METHOD AND MULTIPURPOSE AIRCRAFT WITH INFLATABLE WING (S) USING THE SAME

Procédé de locomotion aérienne applicable à un engin du genre aérodyne comportant, d'une part, au moins un propulseur motorisé (3) capable d'assurer un déplacement aérien dudit engin et dont le fonctionnement engendre un courant ou flux de fluide gazeux et, d'autre part, au moins une aile souple gonflable (2), caractérisé en ce qu'au moins une partie du courant ou flux de fluide gazeux soufflé par ledit propulseur motorisé (3) est récupérée et insufflée à l'intérieur de ladite aile gonflable (2) pour assurer le gonflage et le maintien à l'état gonflé de cette dernière. Method for aerial locomotion applicable to a machine of the aerodyne type comprising, on the one hand, at least one motorized thruster (3) capable of ensuring an overhead movement of said machine and the operation of which generates a current or flow of gaseous fluid and, d on the other hand, at least one inflatable flexible wing (2), characterized in that at least a part of the current or flow of gaseous fluid blown by said motorized thruster (3) is recovered and blown inside said inflatable wing (2) to ensure inflation and maintenance in the inflated state thereof.

BIONIC PARAGLIDER WITH MODULAR WING

L'invention concerne une série de dispositifs pour une aile de parapente, destinés à l'amélioration des qualités de vol, de pilotage et de sécurité du pilote, qui confèrent à la voilure du parapente les fonctionnalités similaires à celles des oiseaux planeurs. Le parapente selon l'invention comporte une aile (1) dont la voûte est munie d'extrémités de voilure (2) à concavité inversée, et d'une partie centrale (3) invaginée en forme de V. L'aile (1) comporte au bord de fuite une fente entre les tissus extrados (5) et intrados (6). Une commande (11) permet de réduire l'envergure par invagination de la partie centrale. Une commande (20) permet d'augmenter la flèche par plissement du bord de fuite. Deux commandes (34) permettent de moduler la voûte par modification de la longueur du suspentage. Les ouvertures de bord d'attaque sont munies de clapets (39) pour prévenir le dégonflage du parapente. The invention relates to a series of devices for a paraglider wing, intended to improve the qualities of flight, piloting and safety of the pilot, which give the wing of the paraglider the functionality similar to those of gliding birds. The paraglider according to the invention comprises a wing (1) whose vault is provided with wing ends (2) with inverted concavity, and with a central part (3) invaginated in the form of V. The wing (1) comprises at the trailing edge a slit between the upper surface (5) and lower surface (6) fabrics. A control (11) makes it possible to reduce the wingspan by invagination of the central part. A control (20) makes it possible to increase the deflection by folding the trailing edge. Two controls (34) make it possible to modulate the arch by modifying the length of the lines. The leading edge openings are fitted with valves (39) to prevent deflation of the paraglider.

ADVANCED MULTI-CELLULAR PARACHUTE

Ce parachute à voilure multi-cellulaire du type aile planante comportant une paroi d'extrados et une paroi d'intrados réunies par des nervures formant cloisons délimitant des cellules parallèles ouvertes au bord d'attaque et des drisses de commande de manoeuvre fixées au bord de fuite afin de permettre de déformer une partie de celui-ci formant volet de courbure, comporte dans sa paroi d'extrados au moins un passage de sortie d'air ayant la forme d'une fente et orienté vers l'arrière de façon à diriger un courant laminaire tangentiellement à l'extrados. This parachute with multi-cellular wing of the planing wing type comprising an upper surface wall and an lower surface wall joined by ribs forming partitions delimiting parallel cells open to the leading edge and maneuvering control halyards fixed to the edge of leak in order to allow deformation of a part of the latter forming a curvature flap, comprises in its upper surface wall at least one air outlet passage in the form of a slot and oriented towards the rear so as to direct a laminar current tangentially to the upper surface.

Improvements to parachutes

SHOCK ABSORBER DEVICE FOR PARAGLIDING HARNESS

Inflatable trailing edge cells for parachute wings

The invention relates to a device for trailing edge cells, with low internal pressure in order to thin the rear of a parachute wing and thus enhance its performance. It consists of cells (1) at the rear of box sections (2), separated from them by partitions (3) of fabric and slightly inflated by air intakes (4) on the lower surface (5), a site of low pressure, in order to obtain a finer profile at the trailing edge (10). These cells can have air outlets (9). The arrows (12) represent the streams of air entering or exiting the wing. The device according to the invention is particularly intended for parapents, small-scale models, kites and sail boats using the principle of multicellular wings.

PARACHUTE-GLIDER

Device for adjusting the speed of a parapent and parapent equipped with such a device

The present invention relates to a device for adjusting the speed of a parapent during flight by modifying the profile of the wing and its angle of incidence in the air. This device (22) includes two identical control elements (23) linked to three groups of risers (16, 17, 18). The risers (16, 17) are each formed of two strands (16a, 16b; 17a, 17b) linked to the control element (23). This element makes it possible to retain and move the positions of the attachment points (E, D) of the strands (16a, 16b) of the riser (16), the load carrying strand (17b) of the riser (17) being linked directly to the loop (21) for supporting the pilot's harness, the strand (17a) being linked to this loop by means of a member (26) for blocking the element (23) so as to keep the device in a defined position, and the riser (18) being fixed directly to this element (23). Application: parapents and similar contrivances.

WATERPROOF WELL DEVICE FOR PARACHUT WINGS

Assembling of rigid ribs with delta plane wing leading edge

The assembling of rigid ribs (2) with the leading edge (3) of a delta plane wing comprises adjusting the position of the ribs into a vertical plane. The adjustment means comprises a threaded insert (4) fixed to one of the front top or bottom ends of the ribs into which is screwed an adjustment piece (5). The adjustment piece is connected to the leading edge by a removable piece (6).

Parachute with multicellular wing plan

It comprises an upper surface wall 2 and a lower surface wall 4 joined by ribs 6 delimiting cells which are open at the leading edge, shrouds 8 being fixed to the wing plan. It comprises means 10, 14 for bringing the lower surface wall 4 and the upper surface wall 2 together at at least one point situated between the leading edge and the trailing edge.

FLEXIBLE FENDER HAVING ACTIVE AIR INPUT AND PASSIVE AIR INTAKE

L'invention concerne une aile (100) souple comprenant une voilure (1) et une pluralité de suspentes (2) reliées à la voilure (1), ladite voilure (1) comprenant une paroi supérieure (11) et une paroi inférieure (12), définissant un volume intérieur, au moins une entrée d'air active (3) et au moins un dispositif de gonflage (30) actif configuré pour injecter de l'air depuis l'extérieur dans le volume intérieur via l'entrée d'air active (3). L'aile (100) est remarquable en ce que la voilure (1) comprend au moins une entrée d'air passive (4) et au moins un dispositif anti-retour (40) configuré, pour autoriser une circulation d'air depuis l'extérieur vers le volume intérieur de la voilure (1) lorsque la pression intérieure est inférieure à la pression extérieure et pour interdire une circulation d'air entre le volume intérieur de la voilure (1) et l'extérieur lorsque la pression intérieure est supérieure à la pression extérieure. The invention relates to a flexible wing (100) comprising a wing (1) and a plurality of lines (2) connected to the wing (1), said wing (1) comprising an upper wall (11) and a lower wall (12). ), defining an interior volume, at least one active air inlet (3) and at least one active inflator (30) configured to inject air from the outside into the interior volume via the inlet of active air (3). The wing (100) is remarkable in that the wing (1) comprises at least one passive air inlet (4) and at least one anti-return device (40) configured, to allow air circulation from the outside to the interior volume of the wing (1) when the internal pressure is lower than the external pressure and to prevent air circulation between the interior volume of the wing (1) and the outside when the internal pressure is higher at the external pressure.

METHOD AND DEVICE FOR OPENING AN INFLATED WALL

L'invention concerne un procédé et un dispositif de dégonflage d'une paroi (1) gonflée, caractérisé en ce qu'on découpe ladite paroi (1) gonflée en utilisant au moins un organe de coupe adapté pour couper la paroi (1) gonflée selon une ligne de coupe ayant pour effet de provoquer une ouverture de dégonflage de la paroi (1) gonflée. L'invention s'applique en particulier à l'enveloppe gonflée d'un ballon d'aérostat. The invention relates to a method and a device for deflating an inflated wall (1), characterized in that said inflated wall (1) is cut off by using at least one cutting element adapted to cut the inflated wall (1). along a cutting line having the effect of causing a deflation opening of the wall (1) inflated. The invention applies in particular to the inflated envelope of an aerostat balloon.

Patent DE8903279U1

Emergency warning and signaling system

A warning and signaling system includes a kite attached to a flexible tether rope wherein one end of the rope is secured to a person or a lifeboat. The kite is made from a material having high visibility and includes radar reflective material. The tether rope may carry an antenna for a radio transmitter and receiver. An optional inflatable chamber provides rigidity to the kite. The kite may be provided with a tail having radar reflective swatches attached thereon.

Multi-cellular aerofoil type parachute - has control lines controlling openings at rear of some of the cells

The aerofoil type parachute has an upper surface and a lower surface connected by walls forming cells which are open at the leading edge, and closed at the trailing edge. During a gliding descent, air is trapped in the cells under pressure to form a stationary air zone acting as a solid leading edge deflecting the air stream over the upper and over the lower surfaces of the canopy, as in an aeroplate wing. In addition to the usual suspension cords (9) control lines (11) are attached to the outside of the trailing edge, ending in handgrips within reach of the parachutist. The extra control lines control the openings at the rear of some of the cells, these openings providing a through a flow of air and greater control.

Glider with a variable lift-to-drag ratio

Pair glider of the wing width control system

본 고안은 패러글라이더의 날개폭(크기) 조절장치에 관한 것이다. 패러글라이더는 양력, 향력, 추진력, 영각, 양각, 활공비와 같은 항공역학 이론이 고르게 적용되고 있어 항공 동호인들에게 가장 많이 보급되어 있는 최신 항공레져가 되고 있는 것이다. 이의 안전하고 훌륭한 비행을 위해서는 비행사의 체중과 글라이더의 크기가 적절해야 한다. 따라서 이의 크기는 S사이즈(22㎡), M사이즈(24㎡), L사이즈(26㎠)로 분류되어 있고 S사이즈의 경우 비행사의 체중은 50∼70kg, M사이즈의 경우 비행사의 체중은 60∼80kg, L사이즈의 경우 비행사 체중은 75∼95kg이면 적당한 것이다. 몸무게 70kg의 비행사의 경우는 S사이즈는 체중에 대한 면적이 적으므로 글라이더의 익면 하중이 높아진다. 따라서 속도는 빨라지지만 침하율이 높아지므로 오래 탈수 없게 된다. 그래서 좀더 오래 탈 욕심으로 조금 큰 M사이즈를 선택하게 된다. 그러나 날씨는 항상 일정하지는 않다. 바람이 약할 경우는 별상관 없지만 셀 경우는 문제가 발생하기 때문에 높은 언덕이나 산에까지 메고 올라가서 바람이 세다고 그 자리에서 기체를 당장 작은 사이즈로 바꿀 수 없는 것이고 바람이 셀 때를 대비해서 크고 작은 두 개를 가지고 다닐 수도 없는 것이다. 그리고 패러글라이더의 특성 중에 가장 중요한 곳은 속도이다. 글라이더 마다 고유의 설계 속도가 정해져 있고 적절한 비행사의 체중을 요구한다. 바람이 셀 때나 속도를 요하는 레이스의 경우는 속도를 증가시키는 방법으로 엑셀레이터(풋바)를 밟는 방법과 밸러스트를 차는 방법이 있다. 엑셀레이터로서 속도를 높이는 것은 순간적으로 속도를 높이는 방법이고 지속적으로 유지시킬 수 없기 때문에 일반적으로 밸러스트를 차서 속도를 높이고 있으며 이 경우는 일반적으로 물주머니나 흙 또는 돌을 이용한다. 물의 경우는 착륙장 부근에서 콕을 열어 쏟아 버리면 착륙중량을 줄일 수 있으나 이륙지점인 높은 곳에는 물이 없기 때문에 물을 일일이 메고 올라가야 흙이나 돌의 경우는 이륙지점에서 쉽게 얻을 수 있으나 착륙시 공중에서 버릴 수 없기 때문에 착륙충격을 심하게 받게 되는 폐단이 있었던 것이다. 본 고안은 이상의 문제점을 해결하고자 창안한 것으로 이의 고안요지는 다수의 공기방이 연속 형성된 날개몸체(1)의 중심선에서 좌우 대칭부에 있는 2∼4개 범위의 공기방(4)에 있어 이 공기방을 형성하고 있는 격판(2)의 상하붕착선을 따라 지퍼(5)(5')를 부착하여 잠금쇠(6)로서 잠그면 공기방(4)의 크기가 감소부(a)(a')만큼 감소될 수 있고 지퍼의 잠금쇠(6)를 열면 감소부(a)(a')는 없어지고 공기방(4)이 원상으로 복원되게 하므로서 상황에 따라 이에 알맞는 익면 하중(날개의 크기)을 조절할 수 있게 한 것이다.

Brake parachute for supply drop - with pyramid shape and small hole in apex to prevent flattening in winds

The brake parachute for supply drop has a series of trapezoidal panels (2) sewn into a pyramid shape, when inflated. A hole at the apex (5) spills out the air collected under the canopy, which is non porous. When extended, the half diameter (e) of the canopy is less than the height of the pyramid. The cross sectional area of the hole is about 1% of the total area of the canopy. The airflow under the canopy prevents it from flattening even in high winds. The load is dropped in a near vertical trajectory with high accuracy, and with a minimum of swinging. The terminal speed is slow enough to prevent damage to the load.