Автоматизированный измерительный комплекс для определения гидрогазодинамических характеристик закрученных потоков в аппаратах с узкими кольцевыми каналами переменного сечения

Изобретение относится к измерительной технике и может быть использовано для исследования гидрогазодинамических характеристик закрученных потоков и преобразования полученных параметров в расчетные значения полей скоростей, полей давлений, полей температур в аппаратах с узкими кольцевыми каналами переменного сечения. Заявленный комплекс содержит электронно-вычислительную машину, модуль ввода данных в электронно-вычислительную машину, блок управления, координатный механизм и датчик измерения скорости потока газа. В качестве датчика измерения скорости потока газа используют трубку Пито-Прандтля, напорные линии которой соединены с двумя датчиками абсолютного давления, а в качестве координатного механизма используется устройство, состоящее из линейного привода с шаговым двигателем и поворотной платформы с сервоприводом, обеспечивающих пошаговое линейное перемещение в поперечном направлении канала и пошаговое вращение вокруг оси линейного перемещения датчика скорости в канале исследуемого аппарата ...

СТЕНД ДЛЯ ОПРЕДЕЛЕНИЯ СКОРОСТИ ВИТАНИЯ СЫПУЧИХ МАТЕРИАЛОВ

Изобретение относится к устройствам для измерения скорости витания частиц сыпучих материалов в кольцевом канале. Стенд для определения скорости витания сыпучих материалов включает входной коллектор, трубу витания, фильтр и автотрансформатор. Входной коллектор выполнен в виде стакана с окнами прямоугольной формы на боковых поверхностях, наверху которого жестко закреплен фланец входного коллектора, на котором жестко закреплен нижний фланец. Труба витания выполнена с постоянным поперечным сечением полностью из прозрачного материала, на ее концах установлены верхний и нижний фланцы, а в центре выполнено отверстие, в которое установлена трубка Пито-Прандтля, которая соединена с электронным дифференциальным микроманометром. Внутри трубы витания установлен разъемный набор сегментов, каждый сегмент выполнен из пластмассы в форме цилиндра, на одном из торцов которого выполнен глухой паз круглого сечения, а на другом - выступ, геометрические параметры которого полностью повторяют размеры паза. Достигается ...

MESSONDE UND VERFAHREN ZUR ERMITTLUNG VON STROEMUNGSMITTELDATEN

Vorrichtung zur Messung eines Stroemungsdruckes

Improved apparatus for indicating the air speed and direction of aircraft

... 624,844. Airspeed indicators. SPERRY GYROSCOPE CO., Inc. Aug. 11, 1944, No. 15359. Convention date, Aug. 13, 1943. [Class 69 (i)] [Also in Group XXXVIII] In a rotary-winged aircraft, means are provided for measuring the cyclical variation in the air-speed of a rotating wing. As shown, the dynamic and static orifices 37, 34, of a pitot tube 31, mounted on the end of a rotating wing 32, and which is directed into the wind by a vane 46 and a rotatable mounting 44, are connected to a bellows 49 and a static chamber 48 respectively. An electromagnet 52 is connected to the bellows 49, the other end of which electromagnet is slidable within a fixed coil 57 in which voltages are induced dependent on the amplitude of the variation in air-speed and which may be measured by an A.C. voltmeter graduated in miles per hour. Since the variations in air-speed during one revolution of the wing have a definite phase relation with the direction of motion of the aircraft through the air, a signal having a fixed ...

HELICOPTER ATTITUDE AIRSPEED AND RETENTION SYSTEM

Pitot flow meters

A sensing head (12) for an anemometer or other flow meter comprises a hollow disc-like body having a peripheral wall (40) and an axis (44). Four similar chambers (C1-C4) are formed in the body, and the wall has, for each chamber, a plurality of Pitot holes (42) extending through the wall into the respective chamber. The holes are generally symmetrically arranged around the axis. Means (30) are provided to enable the pressure difference between each diametrically-opposite pair (C1,C3; C2,C4) of the chambers to be sensed. The provision of two or more Pitot holes for each chamber (i.e. eight or more Pitot holes in total) produces a substantially lobe-less characteristic for the anemometer, and the head can still be used to produce a measurement (albeit somewhat inaccurate) even if one of the holes becomes blocked. The provision of the four chambers, each serving two or more of the Pitot holes, enables wind velocity to be measured by sensing only two pressure differences.

Pressure testing apparatus

The present invention relates to a pitot-static system on an aircraft, which is used as the basis for measuring airspeed and altitude. The present invention provides an apparatus for unblocking the lines 6,12 comprising a means 22,24 to introduce a pressurised fluid flow into the line and a means for determining, from the resultant pressure, whether or not a blockage is present. Furthermore, there is also provided a means for introducing a pressurised fluid flow into the line thereby ejecting the blockage.

Helicopter attitude and airspeed acquisition and retention system

The description is substantially identical to that of Patent Specification GB 2081474A but the claims are directed to a helicopter pitch axis autopilot system to achieve a smooth transition between airspeed hold at cruise speeds and pitch attitude hold below cruise speeds.

Fluid pressure sensitive electrical signal generating device with flexural pivot

... 934,465. Measuring electrically. BENDIX CORPORATION. Sept. 29, 1961 [Oct. 7, 1960], No. 35283/61. Class 40 (1). Ambient atmospheric pressure is measured by a balanced pair of bellows whose expansions and contractions produce corresponding rotations of a spring-suspended synchro rotor, whereby signals from the stator indicate the change in ambient pressure, representing e.g. the change in an aircraft altitude or speed. As shown (Fig. 1), two bellows 1, 3, supported by leaf springs 10 and temperature-compensating bi-metallic elements 8, are connected to a shaft 17 carrying the rotor 19 of a synchro 22 whose housing 21 is rotatable about end bearings 30 except when locked by brake elements 27, 28. The shaft 17 is centrally supported inside the housing 21 by springs 25, whereby when the brake elements 27, 28 are released the housing 21 and rotor 19 move together. At a given altitude or speed, a solenoid 40 is energized to operate brake members 27, 28, and the output signal from the stator of ...

Improvements in Apparatus for Indicating or Measuring the Velocity of Flow of Water from Fire Hose Nozzles.

... 10. Morris, J. Jan. 1. Pitot-tube apparatus. - Comprises means for measuring the velocity of flow and the water discharged by fire-hose nozzles. A Pitot-tube meter D, E graduated in any desired manner is carried by the nozzle sheath A, which is screwed to the pipe C. A scale a is marked on the side of the sheath A so that by means of the indicating-rim a<1>, the distance of the Pitot tube from the end of the nozzle may be read. The sheath A also forms a water shield.

HELICOPTER ATTITUDE AIRSPEED AND RETENTION SYSTEM

Improvements relating to the indication of the speed of movement of bodies such as ships relative to fluids

... 520,286. Pressure gauges. PETROFF, A., and IMPROVED SUBMERGED LOG CO., Ltd. Oct. 15, 1938, No. 29932. [Class 106 (ii)] [Also in Group XXIX] Means for indicating the speed of ship; &c. relative to fluids comprises a Pitot. tube and a static pressure tube connected respectively to upper and lower Bourdon tubes 28 carried by a common post 29; the upper tube 28 acts through a link 33, lever 34, long link 35 and short link 47 carried by a post 46 adjusted by a graduated screw &c. 32, the link 35 acting through a pivot 54 and arcuate slot 56 to rock a toothed sector 41 which drives a spring-pressed indicating pointer through a pinion. The free end of the lower tube 28 is connected through a link with a pivoted lever carrying the pivot 53 of the lever 34 whereby the readings of the pointer are corrected to allow for static pressure.

Improvements in air speed indicators

... 526,269. Air speed indicators. HELMORE, W. March 11, 1939, No. 7891. [Class 69 (i)] In an air speed indicator for aircraft in which change of pressure in a Pitot head is indicated by an instrument remote from the head, and the latter is provided with heating means to prevent ice-formation thereon, the heating means is controlled bv an ice-accretion detector to provide heating of the head only when ice is present. A Pitot-head 11, with an electrical heating coil 14, is enclosed in a casing 12 with openings 13 to act as a static head ; the Pitothead and static head are connected by pipes 21, 22, to act on opposite sides of a collapsable capsule 17 to operate an indicating pointer 20. The ice-accretion detector comprises a tubular part 23 surrounded by an electric heater 39 and provided with one or more openings 24 smaller than the opening of the Pitot-head, the tubular part 23 being connected by pipe 27 to a casing 25 divided by a diaphragm 26 ; the Pitothead 11 is connected by pipes 21, ...

Maximum allowable air speed switch

... 1,015,595. Fluid actuation of switches. KELLSMAN INSTRUMENT CORPORATION. June 15, 1962 [June 20, 1961], No. 23201/62. Heading H2B. [Also in Division B7] An aircraft instrument producing an electrical signal when the aircraft approaches its maximum permissible speed comprises static pressure and airspeed detectors connected by a linkage when the aircraft approaches said speed, whereby the signal is produced, the linkage comprising a first member driven by a detector and a second member driven by the first by means of a plurality of co-operating pairs of lever arms of different drive ratios which become operative during different parts of the range of displacement of the members. The interior of a housing 14 is maintained at static ambient pressure by a connection 17, the interior of a capsule 15 is connected to the total pressure orifice of a pilot tube by connection 18, and the capsule is connected by mechanism 22, 24, 26 and 27, to a shaft 20 having arms 39, 40, 41, adapted to engage arms ...

Vorrichtung zur Geschwindigkeitserfassung mit einer Kielsonde

Es wird eine Vorrichtung (1) zur Geschwindigkeitserfassung mit einer Kielsonde (2), die eine Strömungsgeschwindigkeitssonde aufweist, die von einem eine Venturidüse bildenden Mantelkörper (3) umfasst ist, beschrieben. Um vorteilhafte Messbedingungen zu schaffen, wird vorgeschlagen, dass der Mantelkörper (3) als Mehrlochstaudrucksonde mit über den Mantelumfang verteilt angeordneten Löchern (4) im Mantelkörper (3) ausgebildet ist.

METHOD OF LINEARIZING A FLOW VELOCITY SENSOR AND A LINEARIZED FLOW VELOCITY MEASUREMENT APPARATUS

The invention relates to a method and apparatus for linearizing a flow velocity sensor based on pressure difference measurement. According to the method, such a difference of two pressure signals (4, 5) is measured from the flow under measurement that is proportional to the square of the flow velocity, the difference of said two pressure signals (4, 5) is measured using a micromechanically manufactured symmetrical capacitive differential pressure sensor (20) based on the force balance principle, in which sensor the pressure-induced deviation from force balance is compensated for by inducing on the pressuresensing diaphragm (23) of said differential pressure sensor (20) a force-balance-restoring electrostatic pressure so that the pressuresensing diaphragm (23) is subjected to the force-balance-restoring electrostatic force, whereby the amplitude of the force-balance-restoring electrical feedback control signal, which also acts as the system output signal, is directly proportional to the ...

Schleppkörper für hohe Geschwindigkeiten.

Druckmessanlage an Flugzeugen.

Vorrichtung zur Messung des Verhältnisses zweier Kräfte.

Fahrtmesser für Flugzeuge.

Procédé pour la mesure de la vitesse d'un mouvement relatif entre un fluide et une sonde immergée dans celui-ci et de la distance parcourue au cours de ce mouvement, et installation pour la mise en oeuvre de ce procédé

ARRANGEMENT FOR PRODUCING AN AIRSPEED SIGNAL.

УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ СКОРОСТИ ТЕКУЧЕЙ СРЕДЫ

Изобретение касается устройства для измерения скорости текучей среды (1), в частности воздуха, в отсасывающих трубопроводах (2). Устройство снабжено датчиком (3) по меньшей мере с двумя точками замера (4, 5) для определения перепада давления. Согласно изобретению датчик (3) выполнен в виде объёмного профиля несущей поверхности.

Measuring apparatus speed for planes

SYSTEM Of ACQUISITION AND RETENTION the TRUE SPEED AND ATTITUDE Of a HELICOPTER

OPTICAL ANEMOMETRIC PROBE HAS TWO AXES OF MEASUREMENT

METHOD FOR ESTIMATING THE SPEED OF AN AIRCRAFT RELATIVE TO THE SURROUNDING AIR, AND SYSTEM THEREFOR

Air mass static pressure estimating device for aircraft, has correction module for determining corrected static pressure based on local static pressure and height information indicating height of aircraft with respect to ground

Un dispositif d'estimation de la pression statique d'une masse d'air reposant sur un sol et traversée par un aéronef, comprend des moyens de mesure d'une pression statique locale (Psi) et des moyens (CORR) pour déterminer une pression statique corrigée (Pcorr) sur la base de la pression statique locale (Psi) et d'une information de hauteur (alt) indicative de la hauteur de l'aéronef par rapport au sol. Un dispositif de détermination de la vitesse de l'aéronef dans la masse d'air, des procédés associés à ces dispositifs et un aéronef équipe de ces dispositifs sont également proposés.

METHOD AND DEVICE FOR CONTROLLING BRAKING POWER

The invention relates to a method for controlling the braking power transmitted onto a brake disk on an axle of a railway vehicle, especially a high-speed railway vehicle, by means of a caliper, the braking power being controlled depending on the vehicle speed. The vehicle speed is determined indirectly via the relative wind and the impact pressure is detected to determine the relative wind and is forwarded to a control device as the switching pressure or control pressure. The invention further relates to a control device for a braking system of a railway vehicle, especially a high-speed railway vehicle, for controlling the braking power transmitted onto a brake disk by means of a caliper and to a braking system comprising said control device.

METHOD AND DEVICE FOR CONTROLLING BRAKING POWER

The invention relates to a method for controlling the braking power transmitted onto a brake disk on an axle of a railway vehicle, especially a high-speed railway vehicle, by means of a caliper, the braking power being controlled depending on the vehicle speed. The vehicle speed is determined indirectly via the relative wind and the impact pressure is detected to determine the relative wind and is forwarded to a control device as the switching pressure or control pressure. The invention further relates to a control device for a braking system of a railway vehicle, especially a high-speed railway vehicle, for controlling the braking power transmitted onto a brake disk by means of a caliper and to a braking system comprising said control device.

DUCT

Apparatus and method for providing the apparatus, the apparatus including: a duct; and a non-return valve; wherein the duct has a first portion and a second portion; the first portion has a first end and a second end; the first end is open to a fluid (e.g. air); the second end is connected to the second portion such that fluid is permitted to flow between the first portion and the second portion; the non-return valve is positioned at or proximate to the second end; and the non-return valve is arranged such that, upon application of a suction force to the first portion at the first end, fluid flows into the first portion via the non-return valve from outside the duct, and through the first portion from the second end to the first end. 1. Apparatus comprising:a duct; anda non-return valve; whereinthe duct includes a first portion and a second portion;the first portion has a first end and a second end;the first end is open to a fluid;the second end is connected to the second portion such that fluid is permitted to flow between the first portion and the second portion;the non-return valve is positioned at or proximate to the second end; andthe non-return valve is arranged such that, upon application of a suction force to the first portion at the first end, fluid flows into the first portion via the non-return valve from outside the duct, and through the first portion from the second end to the first end.2. Apparatus according to claim 1 , wherein:the second portion has a third end and a fourth end;the second end is connected to the third end;the fourth end is connected to a device; andupon application of a suction force to the first portion at the first end, the non-return valve acts to reduce an effect of the suction force on the device.3. Apparatus according to claim 2 , wherein the device is a pressure transducer.4. Apparatus according to claim 1 , wherein the second portion has a fifth end claim 1 , and the non-return valve is positioned at the fifth end.5. ...

Device for Checking a Flow Pressure Measurement Probe, and Probe Comprising the Device

A device is provided for checking a flow pressure measurement probe as well as a probe comprising the device. The probe includes an internal volume and at least one orifice for communication with the outside of the volume. The device includes: an acoustic transmitter and an acoustic receiver that are intended to be connected to the internal volume so that the transmitter transmits an acoustic signal that propagates in the internal volume and so that the receiver picks up an observed acoustic signal; and, means for comparing the observed signal with a reference signal. The device may be a stand-alone device or may be integrated into the probe.

Method for wind turbine yaw control

A method for yaw control for a wind turbine (1) comprising a rotor with at least one rotor blade (2), the rotor defining a rotor axis (8) and a rotor plane (6, 7) to which the rotor axis (8) is perpendicular, in which the rotor axis (8) is turned such as to minimise the yaw angle (10) between the ambient wind direction (9) and the rotor axis (8) is provided, wherein the turning of the rotor axis (8) is performed based on the measurement of a wind speed in the rotor plane (15) at at least one rotor blade (2). Furthermore, a wind turbine (1) comprising a rotor which comprises a rotor axis (8) and a rotor plane (6) perpendicular to the rotor axis (8) and an anemometer (3) for measuring the ambient wind speed (9) is provided, which is characterised in that the wind turbine (1) further comprises at least one anemometer (3) which is located such at a rotor blade (2) at a particular distance (4) from the rotor axis (8) as to allow for measuring a wind speed in the rotor plane (6).

СПОСОБ ДЛЯ ОПРЕДЕЛЕНИЯ И УЧЕТА НАГРУЗОК БОКОВОГО ВЕТРА ДЛЯ НАХОДЯЩЕГОСЯ В ДВИЖЕНИИ РЕЛЬСОВОГО ТРАНСПОРТНОГО СРЕДСТВА И СООТВЕТСТВЕННО ВЫПОЛНЕННЫЙ ПОСЛЕДНИЙ ВАГОН РЕЛЬСОВОГО ТРАНСПОРТНОГО СРЕДСТВА

Изобретение относится к способам для учета нагрузок бокового ветра для движущегося рельсового транспортного средства. Способ для определения нагрузок бокового ветра заключается в определении аэродинамических данных измерения на боковом участке поверхности рельсового транспортного средства, определении скорости рельсового транспортного средства. Осуществляют доступ к просмотровой таблице. Вычисляют величины и направления преобладающего бокового ветра на основе измеренных данных. Определяют участок рельсового пути, внутри которого проводится измерение. Сохраняют вычисленные данные бокового ветра в соответствии с определенным участком рельсового пути в качестве координат местоположения. Способ для учета условий бокового ветра заключается в получении профиля бокового ветра для определенного участка рельсового пути во время прохождения последнего, прогнозировании условий бокового ветра для расположенного впереди участка рельсового пути на основе полученного профиля бокового ветра. Последний ...

СИГНАЛИЗАТОР ЧИСЛА М

Полезная модель относится к области измерения числа М и может быть использована на авиатранспорте для сигнализации о приближении критической скорости полета. Устройство содержит приемник давления полного аэродинамического торможения, проточный приемник статического давления, соединительные трубопроводы, мембранно-решающее контактное устройство. При этом отношение площадей узкого и входного сечений проточного приемника статического давления выбрано из условия достижения скорости звука в узком сечении, соответствующего точке срабатывания сигнализатора числа М. Технический результат заключается в повышении точности измерения числа М. 2 ил.

Verfahren zum Erfassen und Berücksichtigen von Seitenwindbelastungen bei einem in Fahrt befindlichen Schienenfahrzeug und dessen entsprechend ausgeführter Endwagen

Ein Verfahren zum Erfassen von Seitenwindbelastungen bei einem in Fahrt befindlichen Schienenfahrzeug umfasst folgende Schritte: DOLLAR A a) Erfassen von aerodynamischen Messdaten (z. B. Drücke) an wenigstens einem ersten seitlichen Oberflächenabschnitt des Schienenfahrzeugs, DOLLAR A b) Erfassen einer Geschwindigkeit des Schienenfahrzeugs, DOLLAR A c) Zugreifen auf eine Verweistabelle, welche Zusammenhänge zwischen in Schritt a) erfassbaren aerodynamischen Messdaten des in Fahrt befindlichen Schienenfahrzeugs und der zugehörigen Anströmrichtung des in Fahrt befindlichen Schienenfahrzeugs enthält, DOLLAR A d) Berechnen von Betrag und Richtung des herrschenden Seitenwinds aufgrund der Messdaten aus Schritt a), der Fahrzeuggeschwindigkeit aus Schritt b) und der Verweistabelle, auf die in Schritt c) zugegriffen wird, DOLLAR A e) Erfassen des Gleisstreckenabschnitts, innerhalb dessen die Messung aus Schritt a) durchgeführt wird, und DOLLAR A f) Speichern der in Schritt d) berechneten Seitenwinddaten ...

Gas flow metering by Pitot tube - has articulated scissors in channel providing stops for Pitot tube at intersection points

The scissors, adjustable to individual measuring points in the cross section of the channel, have stops for the Pitot tube at their intersections. Pitot tubes consisting of a shaft and an angled measuring part are fastened to the intersections of the scissors. The tubes are arranged next to one another and to move longitudinally. The measuring parts lie in a plane and their openings are flush. A tube sealed at the front end sides and having an outflow is provided with openings the periphery and is used to measure the static pressure.

Measurement of the velocity or velocity profile of a golf club head using a sensor arrangement that is mounted partially on the head and partially on the shaft and linked to a velocity and velocity profile display on the shaft

Device (100) comprises a measurement arrangement (10) that is placed partially on the club head (210) and partially on the head-side of the shaft (220) to measure the head speed or head speed profile. A display (30) is connected via a flexible electrical conductor (20) or a wireless link to the measurement arrangement to show the measured speed and or its profile. An independent claim is made for use of an impact pressure measurement device, radar measurement device or a throttle measurement device for measuring club head velocity.

Flowmeter for use in internal combustion engine of automobile area, has connector part comprising inflow side and outflow side, and two pressure tapping points provided at side wall and at outer wall of connector part, respectively

The flowmeter (118) has a connector part (116) comprising an inflow side (122) and an outflow side (124), where the flowmeter is made from ceramic material or powder metallurgical material. An accumulation chamber (126) is accessible through an opening and formed in the connector part. Two pressure tapping points are provided at a side wall and at an outer wall of the connector part, respectively. The connector part has a cleaning channel that connects the chamber with the outflow side, where the chamber includes a rounded cross-section. An independent claim is also included for a method for manufacturing a flowmeter for measuring flow of a fluid medium flowing through a flow pipe.

Fühler für Luftfahrzeuge zum Messen der aerodynamischen Parameter der umgebenden Strömung.

Staudruckmesser fuer Geschwindigkeitsprofile

Improvements in or relating to fluid pressure sensing devices

... 1, 072, 748. Measuring Pitot and static pressures. ROSEMOUNT ENGINEERING CO. June 15, 1965 [June 26, 1964], No.25299/65. Heading G1R. In a Pitot tube assembly the fluid passes through a sharp edged conical mouth 12 to a bore 13, a moisture trap 15 and then downwardly through an opening 17 to a chamber 30 and two tubes 35, 36, provided with restriction orifice plates 41, 42 to instruments A, B at a remote location. The tube is electrically heated by a coil 28. A similar assembly may be applied to dual static pressure lines.

Method And Apparatus For Obtaining Improved Accuracy And Range For Air Data Parameters Inferred From Independent Measurements Of Interdependent Pressures

HINGE JOINTS

HELICOPTER ATTITUDE AND AIRSPEED ACQUISITION AND RETENTION SYSTEM

Improvements in or relating to venturi and pitot tubes for aircraft

... 499,429. Venturi and Pitot tubes for aircraft. WALLIS, H. C. Dec. 13, 1937, No. 34430. [Class 69 (i)] To prevent the entry of dust, water, and other foreign matter into a Venturi or Pitot tube 10 used on an aircraft, a movable closure 18 is provided for the air-reception end which tends to move to closing position and is controlled in accordance with the air-speed so that when this is above a predetermined limit it moves to the open position. In the construction shown, the closure 18 is formed at one end of a lever pivoted to a clamp 11 secured to the tube 10, the other end 16 of the lever being formed as an aerofoil which, on the predetermined speed being attained, causes the lever to rock and lower the closure 18 from the mouth of the tube. The closure is returned to closing position by the weight of the aerofoil, or a spring 19, or both.

Helicopter airspeed measuring system

The specification is substantially identical to that of Patent Specification GB 2081474A but the claims are directed to apparatus for providing an aircraft air speed signal (10) derived from a Pilot Static sensor (12) and a longitudinal accelerometer (14) as shown in Fig. 1. The provision of integrators (15), (19) and amplifier (20) eliminates short-term variations in airspeed signal from the sensor (12) which might arise from wind gusts and turbulence. Changes in inertial speed in the short term are however sensed by accelerometer (14). ...

FLOW METER

Vorrichtung zur Geschwindigkeitserfassung mit einer Kielsonde

Es wird eine Vorrichtung (1) zur Geschwindigkeitserfassung mit einer Kielsonde (2), die eine Strömungsgeschwindigkeitssonde aufweist, die von einem eine Venturidüse bildenden Mantelkörper (3) umfasst ist, beschrieben. Um vorteilhafte Messbedingungen zu schaffen, wird vorgeschlagen, dass der Mantelkörper (3) als Mehrlochstaudrucksonde mit über den Mantelumfang verteilt angeordneten Löchern (4) im Mantelkörper (3) ausgebildet ist.

LOW AIRSPEED ASSIST ALGORITHM FOR AIR DATA COMPUTER APPLICATIONS

A method of estimating the airspeed of an aircraft during low airspeed conditions includes measuring a negative impact pressure using a pitot-static probe on the aircraft. Then, the method includes estimating a non-zero airspeed of the aircraft as a function of the measured negative impact pressure.

PRESSURE SENSOR FOR DETERMINING AIRSPEED, ALTITUDE AND ANGLE OF ATTACK

METHOD AND APPARATUS FOR MONITORING FLUID DYNAMIC DRAG

SYNTHETIC AIR DATA OUTPUT GENERATION

In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.

Apparatus to measure the speed of air vehicles

DISPOSITIF PERMETTANT D'AFFICHER LA VITESSE D'UNE PLANCHE A GLISSER SUR L'EAU

L'INVENTION CONCERNE UN DISPOSITIF PERMETTANT D'AFFICHER LA VITESSE D'UNE PLANCHE A GLISSER SUR L'EAU EQUIPEE D'AU MOINS UNE DERIVE 1. CE DISPOSITIF, COMPORTANT UN INSTRUMENT 2 DE MESURE DE LA VITESSE ASSOCIE A UN INSTRUMENT 3 INDICATEUR DE CETTE DERNIERE ET PLACE SUR LE PONT DE LA PLANCHE, EST REMARQUABLE EN CE QUE L'INSTRUMENT DE MESURE 2 EST CONSTITUE PAR UNE SONDE DE PRESSION LOGEE A L'INTERIEUR DE LA DERIVE 1. LA PRISE DE PRESSION 2A DE CETTE SONDE 2, DEBOUCHANT SUR LE BORD D'ATTAQUE 1A DE LA DERIVE 1 A UN POINT DE PRESSION D'ARRET, PERMET DE MESURER UNE PRESSION DONT LA VALEUR EST SENSIBLEMENT PROPORTIONNELLE AU CARRE DE LA VITESSE D'AVANCEMENT DE LA DERIVE 1 DANS LE SENS DE LA FLECHE A. APPLICATIONS : AFFICHAGE DE LA VITESSE DES PLANCHES A VOILE, A "SURF", ETC.

Anemometric antenna consisted two admissions of tube of Pitot laid out in directions opposed to measure speeds indicated of aircraft

Apparatus improved for the clean distance covered and or velocity measurement compared to the air for aircraft

Airspeed indicating apparatus

SAMPLING AND FLOW MEASURING DEVICE

METHOD FOR DETECTING A FAILURE OF AT LEAST ONE SENSOR ON AN AIRCRAFT USING A WIND DETECTION, AND SYSTEM THEREFOR

Ce procédé comprend les étapes suivantes : - mesure d'une vitesse air (Va) de l'aéronef ; - mesure d'une vitesse géographique (Vg) de l'aéronef (12); - détermination d'un vecteur vent instantané (Vv), sur la base de la vitesse air (Va) et de la vitesse géographique (Vg) mesurées. Il comporte les étapes suivantes : - établissement d'un vecteur (dW) de variations de vent instantané, sur la base du vecteur vent instantané (Vv) déterminé ; - projection du vecteur (dW) de variations de vent instantané sur la direction du vecteur d'une vitesse air ou géographique de l'aéronef ; - détermination de la présence d'une panne en fonction de la projection obtenue.

Indicating device of distance covered compared to the air for aircraft

Airflow measuring sound attenuator

An airflow measuring sound attenuator that profiles and stabilizes the pattern of air flowing out of attenuation throats and accurately measures the average velocity of air flowing through the attenautor by a pitot tube array mounted in the region of profiled and stabilized airflow.

Speed display device for a vehicle

A vehicle speed display device includes a plurality of speed sensors of different types for detecting the speed V of a vehicle by different detection methods. A selector mechanism accesses error maps associated with each of the speed sensors that reflects inaccuracies characteristic of the associated speed sensors under various conditions, such as at various speed and/or at various acceleration levels. The selector selects a speed value associated with a minimum error value for the current moving state conditions and the selected speed value is displayed to an operator of the vehicle.

Pitot tube having interior inclined surface

A pitot tube having an inclined surface according to one embodiment may comprise: a housing which forms the outer appearance of the pitot tube; an opening which is arranged on the front side of the housing to allow a fluid to be injected thereinto; a first flow path which is connected to the opening; a slit which is arranged on the side of the housing to allow the fluid to be introduced thereinto; a second flow path which is connected to the slit; and a heater for heating frozen ice introduced into the opening and the slit to liquefy the ice, wherein the first flow path may be located above the center of the opening. Further, an inclined surface may be provided between the first flow path and the opening such that the liquefied fluid collides with the inclined surface after passing through the opening.

Temperature and/or pressure sensor assembly

A sensor assembly (10) includes a housing (12) and a tube (14). The housing has a first leading edge portion (18) which is capable of being located in a compressor/fan inlet flow path and which includes an interior wall section (22). The tube has a proximal portion (24) including an air inlet (28) which is adapted to receive a compressor bleed air flow (30) and a distal portion (26) which is located in the housing and which includes at least one air outlet hole (32). The hole is spaced apart from the interior wall section and is aligned to direct at least some compressor bleed air flow to impinge against the interior wall section. The housing includes an opening (e.g., 48) which receives air from the flow path when the housing is located in the flow path, wherein the opening is adapted for fluid communication with a sensor (16), and wherein the sensor measures at least one of air temperature and air pressure.

SENSOR UNIT FOR FLUIDS

METHOD FOR THE DETECTION AND CONSIDERATION OF CROSSWIND LOADS IN A TRAVELING RAILWAY VEHICLE, AND THE ACCORDINGLY CONFIGURED LAST CAR THEREOF

СТЕНД ДЛЯ ОПРЕДЕЛЕНИЯ СКОРОСТИ ВИТАНИЯ СЫПУЧИХ МАТЕРИАЛОВ

Изобретение относится к области исследования свойств частиц. Сущность изобретения заключается в том, что в конструкции стенда используют полностью прозрачную трубу витания одинакового поперечного сечения по всей длине, а измерение скорости витания осуществляют с помощью трубки Пито-Прандтля, свободно перемещающейся вдоль плоскости поперечного сечения трубы витания, что позволяет измерять скорость воздуха в различных точках воздушного потока. Технический результат – повышение точности и эффективности измерения скорости витания сыпучих материалов. 1 ил.

Verfahren und Vorrichtung zur Geschwindigkeitsmessung einer instationären Strömung

Zeigerinstrument, insbesondere fuer Flugzeuge, zur Anzeige zweier verschiedener, einander zugeordneter Groessen

Method and device for measuring pressure

Flow sensor devices and systems

Improvements relating to ships logs

... 882,659. Ship's logs. WOLDSETH, S. Nov. 5, 1959 [May 5, 1959], No. 37507/59. Class 69 (1). A ship's log of the kind in which an inlet tube 15 with an outer opening 16 facing the direction of travel is fixed concentrically within an outer outlet tube 14, forming an assembly projecting below a ship's bottom 10, 11 and withdrawable through a coaxial sleeve 12, has its inlet 15 and outlet 14 tubes communicating with the inlet 23 and outlet 24 of the loghead 25, 26 through annular chambers 31 and 32 in a manifold 30. The tube 14 has external outlet holes 18. A gate-valve 13 opens and closes a pipe 12 which provides a passage for the log-tube assembly between the plates 10 and 11 of the ship's double bottom.

Improvements in or relating to hinge joints

A head for sensing fluid flow pressure of the kind comprising a swivelling pitot tube wherein the pitot tube is mounted on a hinge joint through which fluid pressure at the pitot tube and the angular position of the pitot tube are transmitted without the use of dynamic seals. The fluid pressure is transmitted via a passageway extending by way of the hollow pivot pin (31) on one member (25) of the hinge joint to which the pitot tube is fixed, a hollow shaft (33) in the other hinge joint member (23) and a flexible tubular connection (41) between the pivot pin (31) and shaft (33), the shaft (33) being coupled to the pivot pin (33) so as to rotate therewith and reduce relative rotation between the ends of the flexible connection (41). The angular position of the shaft (33) indicates the angular position of the pitot tube. The head finds especial application in helicopter airspeed measuring apparatus. ...

Pressure testing apparatus

Improvements in or relating to instrument protectors

... 1,008,048. Ice detectors. ROSEMOUNT ENGINEERING. A. G. June 18, 1964 [Oct. 24, 1963], No. 25327/64. Heading B7W. An ice detector has a probe 25 (Fig. 2, not shown) or 58 (Fig. 5) protruding into an airstream and an aerofoil-section guard 35 or 55 positioned upstream of the probe which shields the probe from hail, gravel and like particles likely to damage the probe, but deflects air and water droplets on to the probe. The probe and guard may be mounted on a panel 65 (Fig. 5) forming part of the skin of an aircraft, either normal or parallel (Fig. 5) to the panel. An Auxiliary member 36 (Fig. 2), 70 (Fig. 5) may be provided to guide the flow over the probe. The guard and auxiliary member may be heated. In the embodiment shown in Fig. 5, the panel 65 is concave so that particles deflected by the guard 55 do not bounce on to the probe.

Improvements in or relating to apparatus for determining the drift of vessels

... 164,788. Paulin, J. G. Jan. 13, 1920. Pitot-tube apparatus.-Apparatus for measuring the drift and speed of vessels comprises Pitot tubes closed at their lower ends and provided with side openings, the openings in one tube or set of tubes being in the longitudinal axis of the vessels, and the openings in the other tube or set being in the transverse axis or slightly forward of it. As shown in Fig. 1, a tube f is divided into compartments h, each communicating with a Pitot tube opening b, c, d, e, and the pairs of opposite compartments communicating with differential manometers for measuring drift and speed. The drift compartments may be connected to a differential manometer m, n, Fig. 4, which operates a visual indicator z and a contact u working over a rheostat v to vary the resistance between leads x, y, this variable resistance being inserted in the main circuit of the log described in Specification 133,056, [Class 106 (ii), Dynamometers &c.], and operating to correct this log for drift ...

Improvements in pitot tube

... 610,427. Pitot tube apparatus. BENDIX AVIATION CORPORATION. April 4, 1946, No. 10496. Convention date, April 7, 1945. [Class 69 (i)] Air-speed velocities are measured by a Pitottube apparatus contained in a torpedo-shaped casing 28 which is freely suspended below an aircraft so that in flight the casing takes up a position in which its longitudinal axis is coincident with the direction of movement through the air. In the detachable nose 24 of the casing is a passage 26 leading into a chamber having one wall formed by a movable gas-tight diaphragm 30 carried by a cylindrical support 36 which is positioned by a shoulder 70 and packing rings 74, 76. Static air pressure is applied to the other side of the diaphragm by way of passages 40 in the casing. The difference in pressure causes movement of the diaphragm and a mechanical system transfers this movement to an electrical transmitter 14 which is connected to an indicator 16 and a source of power 18, both being situated within the aircraft ...

Improved indicating instrument more especially for aircraft

... 499,811. Indicating - instruments. CRANE, C. J., and NESBITT, F. G. May 25, 1937, No. 33205/38. Convention date, May 26, 1936. Divided out of 497,930. Drawings to Specification. [Classes 106 (ii) and 106 (iv)] Comprises a sensitive element fixed in the casing and actuating a pointer co-operating with a dial, characterised in that the dial is rotatably mounted independently of the sensitive element and of the transmitting mechanism connected therewith, and is interconnected with the pointer for simultaneous and synchronous setting rotation therewith in the same direction relative to the casing, and is connected to the sensitive element and to the transmitting mechanism, whereby both dial and pointer may be settably rotated to bring the pointer at any reading to a fixed point relative to the casing. The detailed description is identical with the description of Specification 497,930 except that the detailed description of the rate of climb indicator is omitted, but the claims differ.

PROCEDURE AND DEVICE FOR THE SPEED MEASUREMENT OF AN INTERMITTENT CURRENT

THREE-AXLE AIR DATA SYSTEM FOR AIRCRAFT

FLIGHT CONTROL SYSTEM FOR DETERMINING ESTIMATED DYNAMIC PRESSURE BASED ON LIFT AND DRAG COEFFICIENTS

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality first of operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

METHOD AND DEVICE FOR LEAK CHECK OF AIR DATA SYSTEM

A device for use in a leak check test of an air data system includes a device body, an opening extending into the device body with the opening being configured to allow a probe to be at least partially inserted into the opening, and walls surrounding the opening with the walls being situated to seal a port in the probe such that air is prevented from flowing into or out of the port while the probe is inserted into the opening. A method of performing a leak check test includes covering the port with the device to seal the port, heating air within a gas path in the air data system, measuring the change in pressure of the air resulting from an increase in temperature of the air, and determining whether the air data system is sealed depending on the change in pressure of the air.

HELICOPTER ATTITUDE AND AIRSPEED ACQUISITION AND RETENTION SYSTEM

PRESSURE SENSOR FOR DETERMINING AIRSPEED, ALTITUDE AND ANGLE TTACK

PROCESS AND AUTOMATIC DEVICE Of ESTIMATE a SPEED AIR Of a PLANE

DEVICE Of MAINTENANCE AND AERODYNAMIC ANALYSIS OF PROBE

METHOD FOR ESTIMATING THE SPEED OF AN AIRCRAFT RELATIVE TO THE SURROUNDING AIR, AND SYSTEM THEREFOR

PROCESS AND SURVEILLANCE DEVICE OF the VALIDITY Of INFORMATION OF VITESSED' an AIRCRAFT AND SYSTEM OF GENERATION Of INFORMATION SPEED COMPRISING SO-AND-SO DEVICE

INSTRUMENT Of INDICATION the SPEED Of an AIRCRAFT

DEVICE Of MAINTENANCE AND AERODYNAMIC ANALYSIS OF PROBE

L'invention concerne un dispositif d'entretien et d'analyse (30) de sonde aérodynamique de type à pression d'arrêt destinée à équiper un aéronef. Selon l'invention, le dispositif comprend un canal (31) dont une première extrémité (32) est destinée à pénétrer dans la sonde, des moyens (33) pour créer dans le canal (31) une dépression d'air par rapport à la pression ambiante et des moyens de récupération (41) d'éventuelles particules aspirées dans le canal (31).

Многофункциональный измеритель воздушных данных

Заявляемый в качестве полезной модели многофункциональный измеритель воздушных данных относится к измерительной технике и может быть использован для измерения высотно-скоростных параметров и аэродинамических углов в системах воздушных сигналов летательных аппаратов. Техническим результатом является уменьшение погрешности измерения высотно-скоростных параметров, значительное снижение массы многофункционального измерителя воздушных данных, в первую очередь, за счет исключения пневмотрасс, расположенных между приемником воздушных давлений и узлом датчиков давления. Сущность полезной модели заключается в том, что многофункциональный измеритель воздушных данных содержит приемник воздушных давлений, датчики давлений, вычислитель. Причем датчики объединены в единый корпус датчиков давлений, соединенный с приемником воздушных давлений и вычислителем. Также содержит дополнительный вычислитель высотно-скоростных параметров, соединенный с выходом узла датчиков давлений, и узел контроля обогрева, соединенный с приемником воздушных давлений и вычислителями. Предлагаемый многофункциональный измеритель воздушных данных позволяет уменьшить погрешность измерения аэродинамического угла до значений порядка 0,25° от первоначальных величин порядка 1-1,5°. Также позволяет уменьшить на 20-30% динамическую погрешность измерения высотно-скоростных параметров и на 15-30% уменьшить массу канала измерения высотно-скоростных параметров за счет исключения пневмотрасс. При этом заявляемый в качестве полезной модели многофункциональный измеритель воздушных данных позволяет повысить на 10-40% эффективность электрообогрева. 1 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 183 334 U1 (51) МПК G01L 11/00 (2006.01) G01P 13/02 (2006.01) G01P 5/165 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ПОЛЕЗНОЙ МОДЕЛИ К ПАТЕНТУ (52) СПК G01L 11/00 (2018.05); G01P 13/02 (2018.05); G01P 5/165 (2018.05) (21)(22) Заявка: 2018115924, 27.04.2018 (24) Дата начала отсчета срока действия патента ...

Water flow measurement device

A chiller system including an evaporator for evaporating a refrigerant and a water pipe in fluid communication with the evaporator. The water pipe is configured to allow water to pass through at a flow rate and to circulate the water with the evaporator to exchange heat with the refrigerant in the evaporator. The chiller system includes a flow restrictor tube within the water pipe that is configured to allow the water to flow through the flow restrictor tube at a reduced flow rate relative to the flow rate. The chiller system also includes a measuring probe that passes through walls of the water pipe and the flow restrictor tube and includes an accuracy range of flow rates less than the flow rate. The measuring probe is configured to measure the reduced flow rate within the flow restrictor tube where the reduced flow rate is within the accuracy range.

Aircraft wing and sensor

An apparatus is disclosed which includes an aircraft wing and a sensing unit. The sensing unit includes: a blister on an underside of the aircraft wing; a first and second sensor, at least part of each sensor being either housed in the blister or mounted on or integrated with an outer surface of the blister; wherein the first sensor is arranged to measure a first parameter; the second sensor is arranged to measure a second parameter; a measured value for the first parameter is dependent on a speed of the aircraft in a first direction; a measured value for the second parameter is dependent on a speed of the aircraft in a second direction; the first direction is in a plane perpendicular to an aircraft lateral axis; and the second direction is in a plane perpendicular to an aircraft roll axis.

Device for multipoint acquisition/distribution of fluid, in particular probe for tapping pressure in a turbomachine air inlet

To achieve accurate and rapid acquisition or distribution of fluid—at multipoints—with good spatial resolution and minimal bulk, a twisted arrangement of ducts is provided in the acquisition/distribution zone making it possible to perform several acquisitions/distributions over several heights with one and the same device. The device is a pressure probe in which a probe body exhibits a first part or section for acquiring pressure forming a cylinder less than 6 mm in diameter. The probe exhibits internal ducts forming parallel helicoidal traces on the section and channels formed in a metal alloy body between the ducts and inlet orifices. The number of internal ducts is advantageously equal to nine, including three orifices being disposed over three different heights of the probe body.

Probe for Measuring the Total Pressure of a Flow and Method for Implementing the Probe

A probe for measuring the total pressure of a flow and a method for implementing the probe is provided. The probe is intended to be fitted in an aircraft. The probe comprises a Pitot tube and means for reheating the probe assembly. The probe also comprises means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe. If the temperature delivered by the means for measuring a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow is less than the first reference temperature, then an additional reheating of regions of the Pitot tube likely to accumulate particles conveyed by the flow is triggered. 1. A probe for measuring the total pressure of a flow , the probe being intended to be fitted in an aircraft , the probe comprising:a Pitot tube,means for determining an average temperature of the probe and means for reheating the probe assembly driven by the means for determining the average temperature of the probe, andmeans for determining a local temperature of regions of the Pitot tube likely to accumulate particles conveyed by the flow independently of the means for determining the average temperature of the probe.2. The probe according to claim 1 , wherein the regions of the Pitot tube likely to accumulate particles conveyed by the flow comprise a nose of the Pitot tube claim 1 , the nose comprising an inlet channel and a water trap.3. The probe according to claim 1 , wherein the regions of the Pitot tube likely to accumulate particles conveyed by the flow comprise the walls of a drain hole allowing particles likely to penetrate into the Pitot tube to be discharged.4. The probe according to claim 1 , wherein the means for determining a local temperature are suitable for locally reheating regions of the Pitot tube likely to accumulate particles conveyed by the flow.5. The probe according ...

SYSTEM AND METHOD FOR IMPROVED PILOT SITUATIONAL AWARENESSS

A method includes determining a first speed value based on a first signal from a first data source. The method also includes determining a second speed value based on a second signal from a second data source. The method further includes determining a first likelihood of icing value based on a third signal from a third data source. The method also includes determining a second likelihood of icing value based on a fourth signal from a fourth data source. The method further includes performing a first comparison between the first speed value and the second speed value and performing a second comparison between the first likelihood of icing value and the second likelihood of icing value. The method also includes generating sensor reliability data based on the first comparison and the second comparison and displaying situational awareness data based on the sensor reliability data. 1. An aircraft comprising: determine, for a first time, a first speed value based on a first signal from a first data source;', 'determine, for the first time, a second speed value based on a second signal from a second data source;', 'determine, for the first time, a first likelihood of icing value based on a third signal from a third data source;', 'determine, for the first time, a second likelihood of icing value based on a fourth signal from a fourth data source;', 'perform a first comparison between the first speed value and the second speed value;', 'perform a second comparison between the first likelihood of icing value and the second likelihood of icing value; and', 'generate sensor reliability data based on the first comparison and the second comparison; and, 'a controller configured toa display screen coupled to the controller, the display screen configured to display situational awareness data based on the sensor reliability data.2. The aircraft of claim 1 , wherein the first data source comprises at least one of a pitot tube or a global positioning system receiver.3. The aircraft ...

CONTROLLERS AND AIRCRAFT WITH VARIABLE ENGINE THRUST TAKEOFF SYSTEM

A flight control system for controlling an aircraft during a variable engine thrust takeoff operation operative to perform a method including calculating a calculated acceleration in response to a takeoff distance and a selection of a variable engine thrust takeoff mode, generating an initial thrust control signal in response to the calculated acceleration, controlling a thrust of an aircraft engine in response to the initial thrust control signal, measuring a measured acceleration of the aircraft, generating an updated thrust control signal in response to a difference between the calculated acceleration and the measured acceleration, and controlling the thrust of the aircraft engine in response to the updated thrust control signal. 1. A flight control system comprising:an input configured to indicate a selection of a variable engine thrust takeoff mode;an inertial sensor operative to generate an acceleration data signal indicative of an acceleration of the aircraft;a thrust controller operative to control a thrust of an aircraft engine in response to a thrust control signal; anda processor operative to calculate a calculated acceleration in response to the selection of the variable engine thrust takeoff mode, to generate the thrust control signal corresponding to a first thrust level associated with the calculated acceleration, for determining a measured acceleration in response to the acceleration data signal, and for adjusting the thrust control signal in response to a difference between the calculated acceleration and the measured acceleration.2. The flight control system of wherein the input is a thrust lever.3. The flight control system of wherein the input is pilot user interface.4. The flight control system of wherein the thrust controller is operative to control a fuel supply to the aircraft engine in response to the thrust control signal.5. The flight control system of wherein the measured acceleration is further determined in response to an airspeed ...

Aircraft comprising a measuring probe and method for determining flight parameters of such an aircraft

The invention relates to an aircraft including a fuselage and a first measuring probe including means for measuring the local incidence, means for measuring the static pressure, and optionally means for measuring the total pressure. The fuselage includes at least one first zone where the pressure coefficient of the aircraft depends on the unique local incidence irrespective of the sideslip and incidence values of the aircraft, and the first measuring probe is arranged in said first zone

Flow sensor devices and systems

A flow rate assembly can include a fluid flow interface portion having a front facing wall and a back facing wall. The flow interface portion can include an inlet passage within the fluid flow interface portion, an outlet passage within the fluid flow interface portion, at least one inlet aperture extending through the front facing wall of the fluid flow interface portion into the inlet passage, and at least one outlet aperture extending through the back facing wall of the fluid flow interface portion into the outlet passage. In some cases, the fluid flow interface portion includes a plug forming at least a portion of the inlet passage.

AIR DATA PROBE WITH TURBULENCE-PRODUCING GEOMETRY

An air data probe includes a probe body and an air data sensing port disposed in the probe body. The probe body includes a barrel region, a tapered head region extending forward from the barrel region, and a tip at a forward-most end of the tapered head region. The air data sensing port is disposed in the probe body at a port location aft of the tip. The probe body has a turbulence-producing geometry originating at the tip that produces a turbulent boundary layer of airflow that extends from the tip to the port location. 1. An air data probe comprising:a probe body comprising a barrel region, a tapered head region extending forward from the barrel region, and a tip at a forward-most end of the tapered head region; andan air data sensing port disposed in the probe body at a port location aft of the tip,wherein the probe body has a turbulence-producing geometry originating at the tip that produces a turbulent boundary layer of airflow that extends from the tip to the port location.2. The air data probe of claim 1 ,wherein the turbulence-producing geometry comprises a crenulated geometry including a plurality of projections formed at the tip, each of the plurality of projections separated by one of a plurality of notches.3. The air data probe of claim 2 ,wherein a depth of each of the plurality of notches is uniform.4. The air data probe of claim 2 ,wherein a distance between each of the projections formed at the tip is uniform about a circumference of the tip.5. The air data probe of claim 1 , 'a non-converging outer surface region that extends from the tip in an aft direction to a converging outer surface region of the tapered head region.', 'wherein the turbulence-producing geometry comprises6. The air data probe of claim 1 ,wherein the turbulence-producing geometry comprises a blunt tip.7. The air data probe of claim 6 ,wherein the blunt tip comprises an end surface that is orthogonal to a central axis of the probe body.8. The air data probe of claim 6 ,wherein the ...

Airstream Sensor Devices, Systems and Methods

Airstream sensor devices, systems, and related methods are disclosed. The sensor devices, systems, and methods are incorporated in heating, ventilation, and air conditioning (HVAC) ducts and plenum spaces for providing data used to monitor, manage, troubleshoot and/or control such systems. In an example embodiment, an airstream sensor device includes a housing and a plurality of sensors disposed on the housing. The plurality of sensors is configured to detect the temperature, airflow, and relative humidity of an airstream passing on, over, or through the device.

Pitot Tube Having Interior Inclined Surface

A pitot tube having an inclined surface according to one embodiment may comprise: a housing which forms the outer appearance of the pitot tube; an opening which is arranged on the front side of the housing to allow a fluid to be injected thereinto; a first flow path which is connected to the opening; a slit which is arranged on the side of the housing to allow the fluid to be introduced thereinto; a second flow path which is connected to the slit; and a heater for heating frozen ice introduced into the opening and the slit to liquefy the ice, wherein the first flow path may be located above the center of the opening. Further, an inclined surface may be provided between the first flow path and the opening such that the liquefied fluid collides with the inclined surface after passing through the opening. 1. A pitot tube comprising:a housing configured to form an outer appearance;an opening formed on a front side of the housing to allow a fluid to be introduced thereinto;a first flow path connected to the opening; anda heater configured to apply a heat to an ice formed when the fluid is introduced into the opening to liquify the ice,wherein the first flow path is located above a center of the opening.2. The pitot tube of claim 1 , wherein an inclined surface is formed between the first flow path and the opening such that a liquified fluid passing through the opening collides with the inclined surface as it travels to the first flow path.3. The pitot tube of claim 2 , wherein the heater is disposed rearward of the inclined surface to liquify an ice formed when the fluid is introduced proximate the inclined surface such that a liquified fluid collides with the inclined surface.4. The pitot tube of claim 1 , further comprising:a slit formed on a side surface of the housing to allow a fluid to be introduced thereinto; anda second flow path connected to the slit,wherein the heater is configured to apply a heat to an ice formed when the fluid is introduced into the slit to ...

PITOT TUBE HEAT ALARM

Embodiment of the present invention include a system to alert ground personnel to excessive temperatures of pitot tube sensors. The first end of an attachment arm includes an attachment, such as hook, clamp, annular, or other attachment with a temperature sensor secured to its interior. The second end of the attachment arm is joined to an alarm, the alarm including a controller and a notifier. The temperature sensor is in communication with the controller, providing temperature data. The controller is in communication with the notifier(s), issuing activation instructions to the notifier upon an out of threshold temperature condition. 1. A system for notification of excessive heat on a pitot tube of a stationery vehicle , said system comprising:an attachment arm, at least one temperature sensor, and an alarm;a first end of said attachment arm comprising an attachment operable to removably secure said system to a pitot tube;said temperature sensor operable to provide temperature data from direct contact with said pitot tube or immediate proximity with said pitot tube;said alarm, operable to provide notification of out of threshold temperature values, joined to a distal end of said attachment arm, comprises a controller and a notifier;said temperature sensor in communication with said controller, said temperature sensor providing temperature data to said controller, said controller processing said temperature data for out of threshold values; andsaid controller issuing activation instructions to said notifier upon an out of threshold temperature condition.2. The system of claim 1 , further comprising a hook attachment claim 1 , said hook attachment including a rigid curvilinear section presenting a partial perimeter for engagement to a pitot tube.3. The system of claim 2 , wherein said temperature sensor is fixably mounted on the interior section of said hook attachment.4. The system of claim 1 , further comprising a clamp attachment claim 1 , said clamp attachment ...

THIN FILM HEATING OF AIR DATA PROBES

An air date probe includes a base portion, a strut portion extending from the base portion, and a tube assembly secured to an extending from the strut portion. One or more of the tube assembly or the strut portion includes a sleeve member having a sleeve outer surface positioned at a sleeve frustum angle relative to a sleeve member axis. A thin film heater is positioned at the sleeve outer surface, and the tin film heater and the sleeve member are positioned in a housing member. The housing member has a housing inner surface having a housing frustum angle such that the thin film heater is retained by compression between the housing member inner surface and the sleeve member outer surface. 1. An air date probe , comprising:a base portion;a strut portion extending from the base portion; anda tube assembly secured to an extending from the strut portion; a sleeve member having a sleeve outer surface positioned at a sleeve frustum angle relative to a sleeve member axis;', 'a thin film heater disposed at the sleeve outer surface; and', 'a housing member into which the sleeve member and thin film heater are installed, the housing member having a housing inner surface having a housing frustum angle such that the thin film heater is retained by compression between the housing member inner surface and the sleeve member outer surface., 'wherein one or more of the tube assembly or the strut portion includes2. The air data probe of claim 1 , wherein the sleeve frustum angle is substantially equal to the housing frustum angle.3. The air data probe of claim 1 , wherein the sleeve frustum angle and the housing frustum angle are between 0.5 and 20 degrees.4. The air data probe of claim 1 , wherein the thin film heater is one of a positive temperature coefficient heater based on carbon black/polymer composites or a carbon nanotube/silicone nano-composite heater.5. The air data probe of claim 1 , wherein the thin film heater has a thickness of about 0.03″.6. The air data probe of ...

AIR TEMPERATURE CORRECTION

A system for correcting an air temperature (AT) reading can include a water content sensor configured to measure a water content in an airflow and to output a water content signal indicative thereof, an AT sensor configured to measure an air temperature and output an AT signal indicative thereof, and a correction module operatively connected to the water content sensor and the AT sensor. The correction module can be configured to receive the water content signal and the AT signal and to correct the AT signal based on the water content to output a corrected AT signal. 1. A system for correcting an air temperature (AT) reading , comprising:a water content sensor configured to measure a water content in an airflow and to output a water content signal indicative thereof;an AT sensor configured to measure an air temperature and output an AT signal indicative thereof; anda correction module operatively connected to the water content sensor and the AT sensor, wherein the correction module is configured to receive the water content signal and the AT signal and to correct the AT signal based on the water content to output a corrected AT signal.2. The system of claim 1 , wherein the correction module is configured to use known correlation data to correct the AT signal based on the water content.3. The system of claim 1 , wherein the correction module is configured to output the corrected AT signal to one or more aircraft systems.4. The system of claim 3 , wherein the correction module is included in an air data probe operatively connected to an air data computer to output the corrected AT signal to the air data computer to correct an airspeed value using the AT signal.5. The system of claim 3 , wherein the correction module is included in an air data probe operatively connected to an air data computer claim 3 , wherein the air data probe is configured to locally correct an airspeed value using the AT signal.6. The system of claim 3 , wherein the correction module is included ...

PITOT STATIC SYSTEMS WITH ANGLE OF SIDESLIP DETERMINATION AND COMPENSATION

An air data probe system can include a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations. The system can include an angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location. 1. An air data probe system , comprising:a pitot static system configured to sense at least one total pressure value of a flow at one or more locations, at least one static pressure value of the flow at the one or more locations, and, directly or indirectly, at least one differential static pressure value of the flow at the one or more locations; andan angle of slip (AOS) module configured to determine a local angle of slip (LAOS) value at each location based on the at least one total pressure value at each location, the at least one static pressure value at each location, and the at least one differential static pressure value at each location,2. The system of claim 1 , wherein the AOS module is configured to determine a local angle of attack (LAOA) value at each location based on the at least one differential pressure value at each location claim 1 , or to receive an LAOA value from the pitot static system.3. The system of claim 2 , wherein the AOS module is configured to determine the LAOS at each location based on a comparison of total pressure to static pressure ratio (P/P) against LAOA at a given speed claim 2 , altitude claim 2 , and temperature.4. The system of claim 3 , wherein the AOS module is configured to plot P/Pagainst LAOA and determine the LAOS value based on stored LAOS correlation data for ...

FIRST EQUIPMENT HEATING DEVICE

An aircraft provided with at least two pieces of aeronautic equipment, a first piece of equipment () including a part intended to be arranged at a skin () of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator () associated with functional elements () of the second piece of equipment () of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (), the circuit in which the fluid circulates is formed by a tubular channel with an empty section. 1. An aircraft provided with at least two pieces of aeronautic equipment , a first piece of equipment comprising a part intended to be arranged at a skin of the aircraft and means for heating the part , characterized in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates , the closed circuit comprising an evaporator associated with functional means of the second piece of equipment of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it , and in that outside the evaporator , the circuit in which the fluid circulates is formed by a tubular channel with an empty section.2. The aircraft according to claim 1 , characterized in that the functional means of the second piece of equipment of the aircraft forming a heat source are formed by a part or an electronic board thereof.3. The aircraft according to claim 1 , characterized in that the functional means of the second piece of equipment of the aircraft forming a heat source are formed by an actuator thereof.4. The aircraft according to claim 1 , characterized in that ...

Avionic equipment heating

A piece of aeronautic equipment intended to equip an aircraft, the equipment ( 25 ) including a part intended to be arranged at a skin ( 27 ) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator ( 14 ) associated with functional elements ( 25 a ) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator ( 14 ), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

BIPHASE HEATING

A piece of aeronautic equipment intended to equip an aircraft, the equipment piece () including at least one part intended to be arranged at a skin () outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base () for fastening on the skin of the aircraft from which support elements () for a Pitot tube () provided with lateral static pressure taps () extend. 1. A piece of aeronautic equipment intended to equip an aircraft , the piece of equipment comprising at least one part intended to be arranged at a skin of the aircraft outside the latter and means for heating that part , characterized in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates , the closed circuit comprising an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it , in that outside the evaporator , the circuit in which the fluid circulates is formed by a tubular channel with an empty section , in that at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base for fastening on the skin of the aircraft from which support means for a Pitot tube provided with lateral static pressure taps extend.2. The aeronautic equipment according to claim 1 , characterized in that the channel is configured for the fluid to circulate therein by capillarity.3. The aeronautic equipment according to claim 1 , characterized ...

Plane equipment heating

An aircraft provided with at least one piece of aeronautic equipment, the equipment ( 25 ) including a part intended to be arranged at a skin ( 27 ) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator ( 14 ) associated with functional elements ( 70 ) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

ADDITIVE MANUFACTURING METHOD FOR AN AVIONIC EQUIPMENT

Manufacturing method by addition for at least one part of a piece of aeronautic equipment intended to equip an aircraft, the equipment piece including at least one part intended to be arranged at a skin of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit at least partially integrated, in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit being formed by a tubular channel with an empty section at least partially integral with the equipment piece, at least the part of the equipment piece arranged outside the aircraft is made by additive manufacturing and includes a base for fastening on the skin of the aircraft from which support elements for a Pitot tube extend. 1. A manufacturing method by addition for at least one part of a piece of aeronautic equipment , in particular such as a Pitot probe , intended to equip an aircraft , the piece of equipment comprising at least one part intended to be arranged at a skin of the aircraft and means for heating that part , the heating means including a thermodynamic loop comprising a closed circuit that is at least partially integrated , in which a heat transfer fluid circulates , the closed circuit comprising an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it , outside the evaporator , the circuit in which the fluid circulates is formed by a tubular channel with an empty section at least partially integral with the piece of equipment , at least the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base for fastening on the skin of the aircraft from which support means for a Pitot tube extend.2. The method according to claim 1 , characterized in that the channel is configured ...

ICE RESISTANT PITOT TUBE

A pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening and a radially tapering outer surface extending from the body portion toward the inlet opening. Another pitot tube includes a substantially cylindrical body portion and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening. One or more electrical coils including one or more coil wraps are located at an interior of the pitot tube. One or more bulkeads are located between a forwardmost coil wrap and a drainage feature to limit travel of particles ingested into the interior. 1. A pitot tube comprising:a substantially cylindrical body portion; and an inlet opening; and', 'a radially tapering outer surface extending from the body portion toward the inlet opening., 'a tip portion extending along a pitot tube axis from the body portion, the tip portion including2. The pitot tube of claim 1 , wherein the radially tapering outer surface has a concave arc cross-section.3. The pitot tube of claim 1 , further comprising one or more electrical coils comprising one or more coil wraps disposed at an interior of the pitot tube.4. The pitot tube of claim 3 , further comprising one or more bulkheads disposed at the interior to limit travel of particles ingested into the interior.5. The pitot tube of claim 4 , wherein the one or more bulkeads are disposed between a forwardmost coil wrap and drainage features.6. The pitot tube of claim 4 , wherein the particles are ice crystals.7. The pitot tube of claim 6 , wherein the one or more electrical coils melt the ice crystals.8. The pitot tube of claim 7 , further comprising one or more drain openings disposed between an aftmost bulkhead and the inlet opening to drain remains of the melted ice crystals from the pitot tube.9. A pitot tube comprising:a substantially cylindrical body portion;a tip portion ...

WATER RESISTANT AIRCRAFT PITOT DEVICE

A pitot tube system having a pitot tube containing a porous hydrophobic fabric that blocks water and contaminants from reaching a pressure sensor. The distance in the pitot tube between the fabric and a front orifice of the tube is less than 2.4 times the height of the orifice, and preferably less than or equal to 0.38 times the height. The section of the tube through which the fabric extends defines an opening characterized by a minimum dimension greater than 0.15 inches, and preferably being at least 0.21 inches. The tube is a removable structure that attaches to a mount that forms a passage for communicating the pressure in the tube. That passage contains a second porous hydrophobic fabric that also blocks water and contaminants from reaching a pressure sensor. 1. An aircraft that flies through a relative airflow , and that is characterized by a maximum standard angle of attack in a standard steady-state flight condition , comprising:a pitot device for use in the airflow, includinga pitot housing forming a cavity having a housing external orifice,an air-permeable fabric extending across a section of the cavity and defining a barrel and an internal chamber, anda pressure sensor configured to sense information regarding the pressure within the internal chamber,wherein the pitot device barrel is at a level orientation or lower when the aircraft is flying at the maximum standard angle of attack.2. The pitot device of claim 1 , and further comprising:a static port; andan airspeed calculation system configured to provide an airspeed indication based on the gather information when the external orifice faces into the airflow and the static port is normal to the airflow;wherein the pressure sensor is part of a pressure measurement system configured to gather information indicative of the difference between the pressure within the internal chamber and the pressure at the static port.3. An aircraft control system claim 2 , comprising an autopilot and the pitot device of ...

AIRCRAFT INCLUDING A SYSTEM FOR MEASURING PRESSURE, AND AN ASSOCIATED METHOD

The invention relates to an aircraft () having a system for measuring a static reference pressure in flight, which system comprises: 110. An aircraft () including a system for measuring pressure in flight , the aircraft being characterized in that the measurement system comprises:{'b': 22', '16', '24', '24', '22', '26', '50', '22', '16, 'at least one pressure sensor () connected to the rear portion of the aircraft by an electric cable (), said at least one pressure sensor being associated with a pressure intake () that is arranged downstream from the aircraft when it is in flight and in a zone that is not disturbed by the turbulent flow created around the aircraft, the pressure intake () being arranged upstream from said at least one pressure sensor () and being connected thereto by at least one air feed tube (; ), said at least one pressure sensor () being suitable firstly for measuring an air pressure from at least one pressure signal coming from said pressure intake, and secondly for transmitting at least one electric signal representative of the measured pressure to the aircraft via the electric cable (); and'}{'b': 34', '22', '10, 'a system () on board the aircraft and suitable for determining at least one pressure measurement firstly from said at least one transmitted electric signal and secondly from a position of said at least one pressure sensor () relative to the aircraft ().'}2265024221622. An aircraft according to claim 1 , characterized in that said at least one air feed tube (; ) defines a passage for conveying at least one air pressure signal in a first direction claim 1 , from the pressure intake () to said at least one pressure sensor () claim 1 , and the electric cable () allows said at least one electric signal representative of the measured air pressure to pass in a second direction opposite to the first direction from said at least one pressure sensor () to the aircraft.31626. An aircraft according to claim 2 , characterized in that the electric ...

Method and System of Measurement of Mach and Dynamic Pressure Using Internal Sensors

A system for calculating airspeed and dynamic pressure comprises a system body, an internal accelerometer, located within the system body, an internal pressure sensor, located in the system body, the internal pressure sensor being not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere, and a processor in reception of the internal accelerometer, and the internal pressure sensor, capable of calculating Mach number via an axial acceleration, and capable of calculating a dynamic pressure and a true airspeed via the Mach number. 1. A system for calculating airspeed and dynamic pressure , comprising:a system body;an internal accelerometer located within the system body;an internal pressure sensor located in the system body, the internal pressure sensor not hermetically sealed within the system body and capable of measuring the static pressure of the ambient atmosphere; and,a processor coupled to the internal accelerometer and the internal pressure sensor for calculating Mach number from the axial acceleration detected by said internal accelerometer, and for calculating dynamic pressure and true airspeed utilizing the calculated Mach number.2. The system of claim 1 , further comprising a temperature sensor capable of measuring an ambient air temperature outside of the system body.3. The system of claim 1 , wherein the internal accelerometer is located at the center of gravity of the system body.4. The system of claim 1 , wherein the system body includes entry ports situated to equalize pressure inside and outside of the system body.5. The system of claim 1 , further comprising angle sensors to measure the angles of the control flaps.6. The system of claim 1 , wherein the processor calculates the Mach number using a Mach lookup table.7. The system of claim 1 , wherein the processor calculates the Mach number using a multidimensional polynomial fit.8. The system of claim 1 , wherein the processor calculates the ...

ICE RESISTANT PITOT TUBE

A pitot tube includes a substantially cylindrical body portion having an interior defining a flow passage, and a tip portion extending along a pitot tube axis from the body portion. The tip portion includes an inlet opening, a radially tapered outer surface extending from the body portion toward the inlet opening, one or more bulkheads disposed at the interior to limit travel of particles ingested into the interior, at least one drain opening disposed directly adjacent to one of the one or more bulkheads, and one or more electrical coils comprising one or more coil wraps disposed at an interior of the pitot tube. The one or more coil wraps establish a variable watt density along the interior of the pitot tube. The one or more coil wraps also establish a variable watt density downstream of one or more of the one or more bulkheads. 1. A pitot tube comprising:a substantially cylindrical body portion having an interior defining a flow passage; and an inlet opening;', 'a radially tapered outer surface extending from the body portion toward the inlet opening;', 'one or more bulkheads disposed at the interior to limit travel of particles ingested into the interior;', 'at least one drain opening disposed directly adjacent to one of the one or more bulkheads; and', 'one or more electrical coils comprising one or more coil wraps disposed at an interior of the pitot tube, the one or more coil wraps establishing a variable watt density along the interior of the pitot tube, the one or more coil wraps also establishing a variable watt density downstream of one or more of the one or more bulkheads., 'a tip portion extending along a pitot tube axis from the body portion, the tip portion including2. A pitot tube comprising:a substantially cylindrical body portion having an interior defining a flow passage; and an inlet opening;', 'a radially tapered outer surface extending from the body portion toward the inlet opening; and', 'one or more electrical coils comprising one or more coil ...

ARRANGEMENT OF DAMS IN AIR DATA PROBE

An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe. 1. An air data probe comprising:a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air;at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element;a heater element integrated into the tube of the pitot probe on the outside of the dams; andwherein the at least three dams are oriented within the tube of the pitot probe such that a first pair of the at least three dams includes a first dam located in front of and above a second dam of the at least three dams in a first orientation of the pitot probe, and a second pair of the at least three dams includes a first dam located in front of and above a second dam of the at least three dams in a second orientation of the pitot probe, and, in each orientation, a drain hole is located in front of the second dam.2. The air data probe of claim 1 , whereinat least one of the at least three dams is positioned to provide a barrier to the flow of water or ice crystals along the bottom of the pitot probe when the air data probe is installed in the first orientation, ...

Airfoil Performance Monitor

An airfoil performance monitor comprising a housing mounted on a low pressure face of an airfoil, and defining pitot and static pressure orifices; an airspeed-dependent sensor that senses airflow impinging on the pitot orifices and generates a digital airflow signal indicative of turbulence of the airflow; and a controller that derives a turbulence intensity ratio by filtering turbulence values calculated from the digital airflow signal. 1. An airfoil performance monitor comprising:a housing mounted on a low-pressure face of an airfoil, and including at least one pitot pressure orifice used to determine the total pressure at the airfoil performance monitor and at least one static pressure orifice used to determine the static pressure at the airfoil performance monitor;at least one airspeed-dependent sensor that senses the total pressure at the airfoil performance monitor via the pitot pressure orifice and generates a digital airflow signal indicative of the dynamic pressure at the airfoil performance monitor; anda controller that derives a turbulence intensity ratio by normalizing the turbulence values using the steady-state airflow signal calculated from the digital airflow signal.2. The airfoil performance monitor as claimed in claim 1 , wherein the airspeed-dependent sensor is a pressure sensor and said at least one pitot pressure orifice is in fluid communication with an associated pressure sensor so as to measure the total pressure acting on said airfoil performance monitor.3. The airfoil performance monitor as claimed in claim 1 , wherein the digital airflow signal has steady and overlaid turbulent components.4. The airfoil performance monitor as claimed in claim 1 , further comprising one or more inertial sensors that measure and identify frequency and amplitude data due to mechanical motion vibrations on the mast.5. The airfoil performance monitor as claimed in claim 4 , wherein the controller filters the digital airflow signal using the acceleration ...

AIR DATA PROBE CORROSION PROTECTION

An air data probe with a corrosion protection coating system includes a body with an external and an internal surface and a uniform, pinhole-free first protection layer applied by atomic layer deposition (ALD) to reduce corrosion of the body, including corrosion initiated by sulfur and nitrogen compounds. The air data probe further includes a second protection layer, covering the first protection layer over the external surfaces of the body to protect the air data probe from foreign object impact damage. 1. An air data probe with a corrosion protection coating system , the air data probe comprising:a body with an external and an internal surface;a uniform, pinhole-free first protection layer applied by atomic layer deposition (ALD), covering the external and internal surfaces of the body to reduce corrosion of the body, including corrosion initiated by sulfur and nitrogen compounds; anda second protection layer, covering the first protection layer over the external surfaces of the body to protect the air data probe from foreign object impact damage.2. The air data probe of claim 1 , wherein the body is formed of nickel or a nickel alloy.3. The air data probe of claim 1 , wherein the first protection layer has a thickness from 50 nm to 500 nm claim 1 , inclusive.4. The air data probe of claim 1 , wherein the first protection layer is selected from the group consisting of an oxide claim 1 , nitride claim 1 , semiconductor claim 1 , phosphor claim 1 , fluoride claim 1 , and combinations thereof.5. The air data probe of claim 4 , wherein the oxide is selected from the group consisting of AlO claim 4 , TiO claim 4 , ZrO claim 4 , HfO claim 4 , TaO claim 4 , NbO claim 4 , ScO claim 4 , YO claim 4 , MgO claim 4 , BO claim 4 , SiO claim 4 , GeO claim 4 , LaO claim 4 , CeO claim 4 , PrOx claim 4 , NdO claim 4 , SmO claim 4 , EuO claim 4 , GdO claim 4 , DyO claim 4 , HoO claim 4 , ErO claim 4 , TmO claim 4 , YbO claim 4 , LuO claim 4 , SrTiO claim 4 , BaTiO claim 4 , PbTiO ...

A MULTI-DIRECTIONAL FLUID VELOCITY MEASUREMENT DEVICE (FVMD)

This present application relates generally to the science of fluid flow measurement and provides a multi-directional fluid velocity measurement device (FVMD) employing a plurality of pitot tubes arranged in a 3D configuration and extending from a spherical main body in which measurement sensors are provided. 1. A multi-directional fluid velocity measurement device for measuring three dimensional characteristics of fluid flow , the device comprising:a main body having a substantially spherical outer surface;a plurality of pressure sensors, arranged within the main body;a support for supporting the main body;a plurality of Pitot tubes, each of the Pitot tubes extending outwardly from a proximal end at the main body to a distal end;a plurality of pressure sensors, each pressure sensor being in fluid communication with a respective one of the Pitot tubes, wherein the Pitot tubes are distributed about the outer surface in three dimensions wherein the distal end of each Pitot tube is a sufficient distance from the outer surface of the main body such that the pressure readings taken by the Pitot tubes are not substantially corrupted by the localized pressure variations created by the wind flowing over the main body.2. A device according to claim 1 , wherein the sufficient distance is at least the radius of the main body.3. A device according to claim 2 , wherein the sufficient distance is between twice and ten times the radius of the main body.4. A device according to any preceding claim claim 2 , further comprising a plurality of sockets arranged about the main body claim 2 , wherein each socket is in fluid communication with a pressure sensor and where the Pitot tubes are removably engageable with the sockets.5. A device according to claim 4 , wherein the removable engagement is such that a Pitot tube may be removed by hand.6. A device according to claim 5 , wherein the removable engagement comprises the use of screw fit connection claim 5 , push-fit connection or a push ...

Rotorcraft flight parameter estimation

An aircraft is provided and includes an airframe. The airframe includes first and second rotor apparatuses at upper and tail portions of the aircraft, respectively, to provide for control and navigational drive. The aircraft further includes a stabilizer component disposed at the tail portion in a position displaced from downwash of the first and second rotor apparatuses at airspeed ranges and a control system configured to apply a dither actuation signal to the stabilizer component at the airspeed ranges by which an aircraft response to a stabilizer component input is measurable for airspeed estimation purposes.

Systems and methods for additive manufacturing for air data probes

Systems and methods for additive manufacturing for air data probes are provided. In at least one embodiment a probe comprises a support structure comprising one or more ports for receiving one or more fluids, the support structure comprising an endoskeleton mandrel having an opening for receiving a fluid; and a heating cable encircling an external surface of the endoskeleton mandrel. The probe also comprises an additive coating fused to the external surface of the endoskeleton mandrel and an external surface of the heating cable; and an internal assembly inside the support structure for carrying pressures from the one or more ports to one or more instruments that respond to the one or more fluids to provide a measurement.

Downhole Multiphase Flow Sensing Methods

Provided are systems and methods for in-situ zonal assessment of multiphase fluid flow in one or more production zones of a production well, including for at least one production zone sensing one or more fluid flow parameters via at least one sensor disposed in a production zone; at least one sensor communications node being in electrical communication with an associated sensor, the at least one sensor communications node positioned along a tubular body in the production zone proximate an associated at least one sensor, and receiving signals from the associated at least one sensor; sending the acoustic signals from the at least one sensor communications node to a receiver at a surface via a series of intermediate communications nodes, node-to-node, the signals being indicative of one or more fluid flow parameters, the series of intermediate communications nodes being spaced along the tubular and configured to transmit acoustic waves; assessing one or more fluid flow parameters for the one or more production zones in response to signals received from a topside communications node. 1. An in-situ system for assessing production conditions of one or more production zones of a fluid producing well comprising at least one production zone , the system comprising:at least one sensor disposed along a tubular body in the production zone of the fluid producing well, each sensor configured to measure a parameter indicative of fluid flow within production tubing in that zone;at least one sensor communications node placed along and affixed to a wall of the tubular body in that production zone, the at least one sensor communications node being in communication with at least one associated sensor and configured to receive signals therefrom;a topside communications node;one or more intermediate communications nodes spaced along and attached to the wall of the tubular body, wherein the intermediate communications nodes are configured to transmit signals received from the sensor ...

Instrument and Method for Measuring Low Indicated Air Speed

An improved instrument for measuring low indicated air speed greatly reduces variation with one or more of time, temperature, and ambient pressure change. This is accomplished by periodically re-zeroing the transducer using only a single electronically controlled valve. Re-zeroing may be initiated in response to a change in the internal temperature of the transducer. 1. A compensated indicated air speed instrument , comprising:a pitot tube into which ram air is induced to generate a positive air pressure proportional to air speed;a static port providing a reference air pressure;an electronic pressure transducer having a positive input port and a negative input port, the static port being connected directly to the negative input port of the electronic pressure transducer; and the pressure transducer has an output terminal which provides an electronic signal proportional to transducer internal temperature;only a single electronically controlled valve switchable between the pitot tube and the static port and providing an output to the positive input port of the electronic pressure transducer, the electronically controlled valve normally passing the output of the pitot tube to the positive input port of the electronic pressure transducer;a processor receiving an output of the electronic pressure transducer and computing an indicated air speed based on a differential air pressure output from the electronic pressure transducer, the processor periodically re-zeroing the electronic pressure transducer by controlling the electronically controlled valve to connect the positive input port of the electronic pressure transducer to the static port; anda display connected to the processor to display the computed indicated air speed.2. The compensated indicated air speed instrument of claim 1 , wherein said single electronically controlled valve is a pneumatically actuated valve.3. The compensated indicated air speed instrument of claim 1 , further comprising a temperature sensor ...

ENHANCED PITOT TUBE POWER MANAGEMENT SYSTEM AND METHOD

A system, power management system and method are disclosed. The power management system includes a pitot tube, one or more heating elements disposed in the pitot tube, and one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal. The power management system also includes a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube, and a processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault. 1. A power management system , comprising:a pitot tube;one or more heating elements disposed in the pitot tube;one or more power switches, wherein each power switch of the one or more power switches is coupled to a respective heating element and configured to energize or de-energize the respective heating element in response to a control signal;a temperature detector coupled to the pitot tube and configured to determine a temperature of the pitot tube; anda processor complex coupled to the one or more power switches and the temperature detector and configured to output the control signal to energize or de-energize at least one of the heating elements through a respective at least one of the respective one or more power switches in response to at least the determined temperature of the pitot tube or a detection of a fault.2. The power management system of claim 1 , further comprising:a data transceiver coupled to at least the processor complex and an intra-aircraft communications bus.3. The power management system of claim 1 , wherein the pitot ...

AIR DATA SYSTEM ARCHITECTURES USING INTEGRATED PRESSURE PROBES

An aircraft air data system includes a first air data probe disposed on a first side of the aircraft, a second air data probe disposed on a second side of the aircraft, a first plurality of static pressure sensing ports disposed on the first side of the aircraft, and a second plurality of static pressure ports disposed on the second side of the aircraft. Each of the first air data probe and the second air data probe include a barrel portion configured to extend into an oncoming airflow, a total pressure sensing port, and an integrated total pressure sensor. Each of the first plurality of static pressure sensing ports is connected to one of a first plurality of integrated static pressure sensors. Each of the second plurality of static pressure sensing ports is connected to one of a second plurality of integrated static pressure sensors. 1. An aircraft air data system comprising: a barrel portion configured to extend into an oncoming airflow about an exterior of the aircraft;', 'a total pressure sensing port at a forward tip of the barrel portion; and', 'an integrated total pressure sensor configured to measure the total pressure of the oncoming airflow;, 'a first air data probe disposed on a first side of the aircraft and a second air data probe disposed on a second side of the aircraft opposite the first side, each of the first air data probe and the second air data probe comprisinga first plurality of static pressure sensing ports disposed on the first side of the aircraft, each of the first plurality of static pressure sensing ports connected to one of a first plurality of integrated static pressure sensors configured to measure static pressure of the oncoming airflow; anda second plurality of static pressure sensing ports disposed on the second side of the aircraft, each of the second plurality of static pressure sensing ports connected to one of a second plurality of integrated static pressure sensors configured to measure the static pressure of the oncoming ...

Pitot tube

A pitot tube is provided having a tube wall and a heating arrangement for generating heat for heating thereby at least a portion of the tube wall to prevent the tube from becoming clogged with ice. The heating arrangement includes a radiation absorbing surface configured for absorbing electromagnetic radiation (EMR) and generating the heat. At least one radiation conveying portion is provided for receiving EMR from an EMR source and conveying it to the radiation absorbing surface.

Inductive heating of air data probes

An air data probe includes a faceplate, a body connected to the faceplate, and a heating system comprising a coil, the coil being connected to the faceplate. The coil generates an electromagnetic field that couples with the body to heat the body.

ACOUSTIC AIR DATA SENSOR AND SYSTEM

An acoustic air data sensor for an aircraft includes an acoustic transmitter, an acoustic receiver, an acoustic signal generator, timing circuitry, speed of sound determination circuity, and communication circuitry. The acoustic transmitter is located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft. The acoustic receiver is positioned at a distance from the acoustic transmitter to receive the acoustic signal. The pulse generator causes the acoustic transmitter to provide the acoustic signal. The timing circuitry determines a time of flight of the acoustic signal from the acoustic transmitter to the acoustic receiver. The speed of sound determination circuity determines, based on the time of flight and the distance, a speed of sound through air in the stagnation chamber. The communication circuitry outputs the speed of sound. 1. An acoustic air data sensor for an aircraft , the acoustic air data sensor comprising:an acoustic transmitter located to transmit an acoustic signal through an airflow stagnation chamber that is pneumatically connected to an exterior of the aircraft and configured to receive and stagnate airflow from the exterior of the aircraft, each of an inlet and an outlet of the airflow stagnation chamber having a maximum width that is less than a maximum width of the airflow stagnation chamber;an acoustic receiver positioned at a distance from the acoustic transmitter to receive the acoustic signal transmitted by the acoustic transmitter through the airflow stagnation chamber, wherein each of the acoustic receiver and the acoustic transmitter are located in the airflow stagnation chamber;an acoustic signal generator that causes the acoustic transmitter to provide the acoustic signal;timing circuitry that determines a time of flight of the acoustic signal from the acoustic transmitter to the ...

AIR DATA PROBE REPLACEMENT DETERMINATION SYSTEM

Method and systems of determining when to replace an air data probe are provided. The method includes measuring a temperature of a heating element of an air data probe; tracking an amount of time the heating element is within at least one temperature range; and providing an air data probe replacement indication when a replacement threshold is met that is at least in part based on reaching a cumulative amount of time the heating element has a measured temperature within the at least one temperature range. 1. A method of determining when to replace an air data probe , the method comprising:measuring a temperature of a heating element of an air data probe;tracking an amount of time the heating element is within at least one temperature range; andproviding an air data probe replacement indication when a replacement threshold is met that is at least in part based on reaching a cumulative amount of time the heating element has a measured temperature within the at least one temperature range.2. The method of claim 1 , wherein measuring the temperature of the inner heating element further comprises:determining an operational resistance of the heating element by measuring the current drawn by the heating element for a given drive voltage; andderiving the temperature based on the determined resistance.3. The method of claim 1 , wherein when more than one temperature range is used claim 1 , the method further comprises:applying a cumulated weighted system that tracks the usage and predicts the life expectancy of the air data probe based on temperatures of the heating element over time within each temperature range.4. The method of claim 1 , further comprising:adjusting the replacement threshold based at least in part on gathered data relating to the remaining life of the air data probe.5. The method of claim 1 , further comprising;generating a remaining life estimate based at least in part on the measured temperature of the heating element and the tracked amount of time the ...

SYSTEMS AND METHODS FOR VARIABLE ALIGNMENT AERODYNAMIC PROBES

A variable alignment aerodynamic probe may comprise a probe body having a leading edge and extending radially into a vane case, a sensor element proximate the leading edge, and a bearing coupled to the probe body and the vane case. The probe body may be configured to rotate in response to a turned flow within the vane case. The rotation of the probe body may be configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°. 1. A variable alignment aerodynamic probe comprising:a probe body having a leading edge and extending radially into a vane case;a sensor element proximate the leading edge; anda bearing coupled to the probe body and the vane case;wherein the probe body is configured to rotate in response to a turned flow within the vane case,wherein the rotation of the probe body is configured to maintain an angle of attack of the leading edge with respect to the turned flow between 0° and 15°.2. The variable alignment aerodynamic probe of claim 1 , wherein the sensor element is at least one of a Pitot tube or Kiel probe.3. The variable alignment aerodynamic probe of claim 2 , wherein the probe body further comprises a first shaft coupled to the probe body and rigidly coupled to a first control arm.4. The variable alignment aerodynamic probe of claim 3 , wherein the first control arm is coupled to a first end of a control linkage claim 3 , wherein the control linkage is coupled at a second end to a second control arm.5. The variable alignment aerodynamic probe of claim 4 , wherein the second control arm is rigidly coupled to one of a second shaft or a synchronization ring claim 4 , wherein the second control arm is configured to deflect in response to rotation of a variable vane.6. The variable alignment aerodynamic probe of claim 2 , further comprising:a controller;a first sensor in electronic communication with the controller;a second sensor in electronic communication with the controller;a first servomotor in ...

Pitot-Static System Blockage Detector

Various implementation described herein are directed to a method for identifying a blockage in a pitot-static system. A pressure signal is received. Pressure fluctuations in the pressure signal are identified. A determination is made as to whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations. 1. A method for identifying a blockage in a pitot-static system , comprising:receiving a pressure signal;identifying pressure fluctuations in the pressure signal; anddetermining whether a blockage has occurred in the pitot-static system based on the identified pressure fluctuations.2. The method of claim 1 , wherein the pressure signal comprises a total pressure signal received from a total pressure sensor.3. The method of claim 2 , wherein the total pressure sensor is coupled to a pitot tube of the pitot-static system.4. The method of claim 3 , wherein a predefined airspeed is attained prior to receiving the pressure signal.5. The method of claim 1 , wherein the pressure signal comprises a static pressure signal.6. The method of claim 5 , wherein the static pressure signal is received from a static pressure sensor.7. The method of claim 6 , wherein the static pressure sensor is coupled to a static port of the pitot-static system.8. The method of claim 7 , wherein a predefined flight range of a rotor speed is attained prior to receiving the pressure signal.9. The method of claim 1 , wherein the identified pressure fluctuations comprise a noise component.10. The method of claim 9 , wherein the noise component comprises a rotor blade passage frequency.11. The method of claim 9 , wherein the noise component comprises a longitudinal vibration frequency.12. The method of claim 1 , further comprising isolating the identified pressure fluctuations to identify pressure fluctuations characteristic of an open port.13. The method of claim 1 , wherein the determination of whether the blockage has occurred is processed in a frequency ...

FAIL-SAFE AUTOMATICALLY SELF-REMOVING PITOT TUBE COVER

A pitot tube cover for a pitot tube operable to determine a speed of an aircraft based on an airstream impinging on the pitot tube. The pitot tube cover has a body and a sail extending from the body. The body has a top surface opposite a bottom surface, an elongate cavity and a slot extending from the top surface to the elongate cavity, the elongate cavity sized to receive the pitot tube and the slot having a width narrower than a diameter of the pitot tube to provide a retaining force which retains the body on the pitot tube after the pitot tube is received by the elongate cavity. The sail includes a first substantially planar sail surface and a second substantially planar sail surface extending from the first sail surface distally to the body. 1. A pitot tube cover for a pitot tube operable to determine a speed of an aircraft based on an airstream impinging on the pitot tube , the pitot tube cover comprising:a body having a top surface opposite a bottom surface, an elongate cavity, and a slot extending from the top surface to the elongate cavity, the elongate cavity sized to receive the pitot tube and the slot having a width narrower than a diameter of the pitot tube to provide a retaining force which retains the body on the pitot tube after the pitot tube is received by the elongate cavity;a first substantially planar sail surface disposed at a first angle to a horizontal plane, the first sail surface generating a first force responsive to the airstream based on the speed of the aircraft; and 'wherein the first force and the second force comprise vertical and horizontal components configured to retain the pitot tube cover on the pitot tube until the aircraft reaches a predetermined speed and to overcome the retaining force of the slot to self-remove the pitot tube cover at a speed equal to or higher than the desired speed.', 'a second substantially planar sail surface extending from the first sail surface distally to the body and disposed at a second angle to the ...

CALIBRATION OF AIRCRAFT INSTRUMENTS USING A LASER SENSOR

A method for correcting an ambient pressure measurement, a method for calculating a temperature, and an apparatus for affecting the same for an aircraft measuring system are provided. The methods include the steps of receiving an airspeed measurement from a laser sensor, receiving a total pressure measurement, and calculating an ambient pressure correction. A corrected ambient pressure or a calculated temperature may be calculated. The apparatus includes a laser sensor configured to provide an airspeed measurement, an aircraft instrument configured to provide a total pressure measurement, and a processing system. 1. A method for correcting an ambient pressure measurement outside an aircraft , comprising the steps of:receiving an airspeed measurement from a laser sensor;receiving a total pressure measurement; andcalculating an ambient pressure correction using the airspeed measurement and the total pressure measurement.2. The method of claim 1 , further comprising the step of:calculating a corrected ambient pressure using the ambient pressure measured with the aircraft instrument and the ambient pressure correction.3. The method of claim 1 , wherein the total pressure measurement is determined using a pitot probe and a transducer.4. The method of claim 1 , further comprising the steps of:receiving a plurality of airspeed measurements corresponding to a plurality of total pressure measurements;calculating a plurality of ambient pressure corrections using the plurality of airspeed measurements and the plurality of total pressure measurements; andgenerating a numerical fit to the plurality of ambient pressure corrections.5. The method of claim 4 , further comprising the step of:calculating an interpolated ambient pressure correction using the numerical fit.6. The method of claim 1 , further comprising the step of:correcting the airspeed measurement from the laser sensor to determine a longitudinal airspeed measurement corrected for at least one of a flow angle and a ...

PITOT TUBE HEATER ASSEMBLY

A pitot tube includes an outer tube extending from a first tube end to second tube end. The second tube end defines a tip portion of the pitot tube. A tube sleeve is located inside of the outer tube and defines a tube passage extending from the first tube end to the second tube end. A heating element is located between the outer tube and the tube sleeve. The heating element is isolated from airflow into the tube passage. A method of forming a pitot tube includes installing a heating element to an outer surface of a tube sleeve, the tube sleeve defining a tube passage of the pitot tube. The tube sleeve is secured in an outer tube such that the heating element is between the tube sleeve and the outer tube and is isolated from airflow through the tube passage.

AIRCRAFT AIRFLOW SENSOR HAVING A VANE WITH INTEGRATED PRESSURE TRANSDUCERS

An aircraft airflow sensor including a vane assembly configured to sense a direction of local airflow outside an aircraft, at least one port arranged on the vane assembly, and at least one transducer arranged with the vane assembly configured to measure a pressure within the vane assembly. The at least one transducer being in fluid communication with the at least one port. The aircraft airflow sensor also includes a shaft configured to rotatably hold the vane assembly and allow rotational movement of the vane assembly. 1. An aircraft airflow sensor comprising:a vane assembly configured to sense a direction of local airflow outside an aircraft;at least one port arranged on the vane assembly;at least one transducer arranged with the vane assembly configured to measure a pressure within at least one vane assembly settling chamber, the at least one transducer being in fluid communication with the at least one port; anda shaft configured to rotatably hold the vane assembly and allow rotational movement of the vane assembly.2. The aircraft airflow sensor according towherein the at least one transducer arranged with the vane assembly is configured to measure a pressure within the at least one vane assembly settling chamber for determining at least one of the following: local total pressure, local impact pressure, airspeed, and Mach number; andwherein the at least one transducer arranged with the vane assembly is configured to measure a pressure within the vane assembly for determining at least one of the following: local static pressure, an altitude, and an altitude trend.3. The aircraft airflow sensor according to wherein the at least one port comprises a pitot inlet; and wherein the at least one port comprises a static port.4. The aircraft airflow sensor probe according to further comprising a dual redundant heating system.5. The aircraft airflow sensor according to wherein the vane assembly is configured to sense the direction of local airflow outside the aircraft and ...

ARTICLE IN MOTION COMPRISING HYDROPHOBICALLY-COATED REGION

Articles having a hydrophobically-coated region and processes of using such articles are disclosed. The article includes a substrate material and a hydrophobically-coated region on the substrate material, the hydrophobically-coated region being contacted or configured for contact with a fluid. The hydrophobically-coated region is configured to repulse the fluid from the article while the article is moving through the fluid. The process includes using the article by moving the article through the fluid wherein the hydrophobically-coated region repulses the fluid from the article. 1. An article in motion , comprising:a substrate material; anda hydrophobically-coated region on the substrate material, the hydrophobically-coated region being contacted with a fluid;wherein the hydrophobically-coated region repulses the fluid from the article while the article is moving through the fluid.2. The article of claim 1 , wherein the hydrophobically-coated region includes a fluoro-containing thermal chemical vapor deposition.3. The article of claim 1 , wherein the substrate material is selected from the group consisting of copper claim 1 , brass claim 1 , zinc claim 1 , galvanized steel claim 1 , chrome claim 1 , copper-based alloy claim 1 , nickel-based alloy claim 1 , steel claim 1 , stainless steel claim 1 , and an aluminum alloy.4. The article of claim 1 , wherein the substrate material is super duplex steel claim 1 , carbon steel claim 1 , cast iron claim 1 , or Monel® alloys.5. The article of claim 1 , wherein the substrate material includes copper at concentration greater than 5% claim 1 , by weight.6. The article of claim 1 , wherein the moving of the article in the fluid is preceded by the article entering the fluid from a lower density fluid.7. The article of claim 1 , wherein the article is a bullet.8. The article of claim 1 , wherein the article is a torpedo.9. The article of claim 1 , wherein the article is an arrowhead or spearhead.10. The article of claim 1 , ...

Average Pitot Tube Type Flow Meter

Average pitot-tube type flow meter according to the present invention has a total pressure tube and a static pressure tube. The total pressure tube and the static pressure tube are spaced from each other. Across the total pressure tube and the static pressure tube, a rectifying device and a connection case are installed as they are integrated into one body. The rectifying device is positioned in advance of total pressure holes and the total pressure hole and a static pressure hole are positioned inside the connection case.

AIR DATA PROBE INCLUDING SELF-REGULATING THIN FILM HEATER

An air date probe includes a strut assembly extending from a base, and a tube assembly coupled to the strut assembly. One or both of the strut assembly and the tube assembly comprises a self-regulating thin film heating arrangement. The self-regulating thin film heating arrangement includes at least one circuit including a positive temperature coefficient (PTC) heating element connected in series with a negative temperature coefficient (NTC) heating element. 1. An air date probe , comprising:a strut assembly extending from a base; anda tube assembly coupled to the strut assembly and extending therefrom,a self-regulating thin film heating arrangement in operable communication one or both of the strut assembly and the tube assembly, the self-regulating thin film heating arrangement comprising at least one circuit including a positive temperature coefficient (PTC) heating element connected in series with a negative temperature coefficient (NTC) heating element.2. The air data probe of claim 1 , wherein the strut assembly includes a strut self-regulating thin film heating arrangement and the tube assembly includes a tube self-regulating thin film heating arrangement connected in series with the strut self-regulating thin film heating arrangement.3. The air data probe of claim 2 , wherein the tube self-regulating thin film heating arrangement includes a tube input node and a tube output node claim 2 , and the strut self-regulating thin film heating arrangement includes a strut input node and a strut output node.4. The air data probe of claim 3 , wherein the tube input node is in signal communication with a voltage source and the tube output node is in signal communication with the strut input node claim 3 , and wherein the strut output node is in signal communication with a ground potential.5. The air data probe of claim 4 , wherein the tube self-regulating thin film heating arrangement and the strut self-regulating thin film heating arrangement each include a carbon ...

PITOT TUBE HEATER ASSEMBLY

A pitot tube includes an outer tube extending from a first tube end to second tube end. The second tube end defines a tip portion of the pitot tube. A tube sleeve is located inside of the outer tube and defines a tube passage extending from the first tube end to the second tube end. A heating element is located between the outer tube and the tube sleeve. The heating element is isolated from airflow into the tube passage. A method of forming a pitot tube includes installing a heating element to an outer surface of a tube sleeve, the tube sleeve defining a tube passage of the pitot tube. The tube sleeve is secured in an outer tube such that the heating element is between the tube sleeve and the outer tube and is isolated from airflow through the tube passage. 1. A pitot tube , comprising:an outer tube extending from a first tube end to second tube end, the second tube end defining a tip portion of the pitot tube;a tube sleeve inside of the outer tube defining a tube passage extending from the first tube end to the second tube end; anda heating element between the outer tube and the tube sleeve, the heating element being isolated from airflow into the tube passage.2. The pitot tube of claim 1 , wherein the tube sleeve and the outer tube are formed separately.3. The pitot tube of claim 1 , wherein the heating element is one or more heater coils wrapped around the tube sleeve.4. The pitot tube of claim 3 , wherein the tube sleeve includes one or more sleeve grooves in a sleeve outer surface to accommodate the heater coils.5. The pitot tube of claim 1 , further comprising one or more water dams extending from the tube sleeve into the tube passage.6. The pitot tube of claim 1 , further comprising one or more drain openings extending from the tube passage through the tube sleeve and through the outer tube.7. The pitot tube of claim 1 , wherein the tube sleeve is secured to the outer tube via brazing.8. The pitot tube of claim 1 , wherein the tube sleeve is formed by ...

INDUCTIVE HEATING OF AIR DATA PROBES

An air data probe includes a faceplate, a body connected to the faceplate, and a heating system comprising a coil, the coil being connected to the faceplate. The coil generates an electromagnetic field that couples with the body to heat the body. 1. An air data probe comprising:a faceplate;a body connected to the faceplate; anda heating system comprising a coil, the coil being connected to the faceplate;wherein the coil generates an electromagnetic field that couples with the body to heat the body.2. The air data probe of claim 1 , wherein the coil is embedded within the faceplate.3. The air data probe of claim 1 , wherein the body is attached to an exterior surface of the faceplate claim 1 , and the coil is attached to an interior surface of the faceplate.4. The air data probe of claim 1 , wherein the body comprises an interactive material that couples with the electromagnetic field and produces eddy currents to heat the body.5. The air data probe of claim 4 , wherein the interactive material comprises at least one of iron claim 4 , steel claim 4 , and aluminum.6. The air data probe of claim 4 , wherein the interactive material is a coating on an exterior surface of a portion of the body.7. The air data probe of claim 4 , wherein the interactive material is a coating on an interior surface of a portion of the body.8. The air data probe of claim 7 , wherein the interior surface forms a channel within the body claim 7 , the channel being at least one of a pitot pressure path and a static pressure path.9. The air data probe of claim 4 , wherein the body is made of the interactive material.10. The air data probe of claim 4 , wherein a portion of the body is made of ceramic and the interactive material is a coating on the portion of the body made of ceramic.11. The air data probe of claim 4 , wherein the interactive material responds to a frequency of the electromagnetic field.12. The air data probe of claim 1 , wherein the coil generates an electromagnetic field to ...

AIR DATA PROBE REPAIR

A method of repairing an air data probe includes assessing an air data probe for a damaged portion. The method includes depositing a material on the air data probe to repair the damaged portion of the air data probe. An air data probe includes a probe body including a sense port inlet defined through a wall of the probe body. At least a portion of the wall surrounding the sense port inlet is defined by a deposited material having a different microstructure than a material defining another portion of the wall. 1. A method of repairing an air data probe comprising:assessing an air data probe for a damaged portion; anddepositing a material on the air data probe to repair the damaged portion of the air data probe.2. A method as recited in claim 1 , further comprising scanning the air data probe with an optical inspection device to assess an amount and a location of damage.3. A method as recited in claim 1 , further comprising machining the damaged portion of an air data probe to generate a machined portion.4. A method as recited in claim 1 , wherein the air data probe incudes at least one sense port inlet claim 1 , and the method includes temporarily plugging the at least one sense port inlet to limit contamination from entering the air data probe during repair.5. A method as recited in claim 1 , wherein depositing the material includes depositing the material using at least one of directed energy deposition or powder bed fusion.6. A method as recited in claim 1 , further comprising machining the material to conform to a specified geometry.7. A method as recited in claim 1 , wherein the material includes an alloy having at least one of a higher wear resistance or a higher corrosion resistance than an original material of the air data probe.8. A method as recited in claim 1 , wherein the material includes an alloy having better thermal performance than an original material of the air data probe.9. A method as recited in claim 1 , wherein the air data probe is mounted to ...

SYSTEMS, METHODS, AND DEVICES FOR FLUID DATA SENSING

A fluid sensing device includes an outer body, an inner body coupled to the outer body by one or more inner body support struts and extending at least partially out from the outer body, and an aft body disposed at least partially within the outer body at a location aft of the inner body, the aft body being coupled to the outer body by one or more aft body support struts. The inner body includes a hollow interior for housing one or more inner body sensors, and the aft body houses one or more aft body sensors. The fluid sensing device can measure one or more parameters of fluid flow at high angularity, such as total temperature and total pressure, locally and simultaneously, allowing additional fluid parameters, such as local entropy, to be calculated. 1. A fluid sensing device , comprising:an outer body having a fore side, an aft side, and an interior space, the outer body including a fluid inlet disposed at the fore side;an inner body extending at least partially out of the fluid inlet of the outer body along a longitudinal axis;an aft body disposed at least partially within the outer body at a location aft of the inner body; andone or more vents disposed aft of the fluid inlet to allow passage of fluid through the fluid sensing device,wherein the inner body is configured to induce the Coanda effect in at least a portion of a fluid contacting the inner body at an angle transverse to a longitudinal axis of the inner body.2. The fluid sensing device of claim 1 , wherein the aft body includes an opening oriented toward the fore side of the outer body claim 1 , and wherein the aft body houses one or more aft body sensors.3. The fluid sensing device of claim 1 , wherein the inner body includes a hollow interior housing one or more inner body sensors.4. The fluid sensing device of claim 3 , wherein the one or more inner body sensors include one or more temperature sensor claim 3 , rate gyro claim 3 , GPS unit claim 3 , accelerometer claim 3 , radar device claim 3 , ...

System for Ensuring Failsafe Operation of Pitot Tube Covers for Multiple Types of Pitot Tubes

The present invention is directed to multiple arrangements of a self-disengaging pitot tube cover, which can be triggered by a plurality of different environmental conditions while the cover admits to a plurality of different latching mechanisms and opening configurations to guarantee the expeditious, automatic removal of the pitot tube cover while avoiding damage or contamination of the pitot tube itself. 154.-. (canceled)55. A self-disengaging pitot tube cover having an outer shell surrounding an inner bore defined in part by a rear aperture configured to receive a pitot tube , said pitot tube cover comprising:a) a split cylinder configuration of said outer shell, said split cylinder configured in two halves, each said half interfacing along two outer edges;b) a release mechanism formed as part of said shell and configured to facilitate automatic separation of at least one of said to outer edges of said split cylinder halves; and,c) a temperature sensing mechanism configured to activate said release upon detecting a predetermined temperature.56. The self-disengaging pitot tube cover of claim 55 , wherein said release mechanism is a latch perpendicular to said two outer edges claim 55 , and configured to hold said two outer edges together.57. The self-disengaging pitot tube cover of claim 56 , wherein said latch comprises a material that is deformed by alterations in temperature.58. The self-disengaging pitot tube cover of claim 57 , wherein said perpendicular latch comprises Nitinol®.59. The self-disengaging pitot tube cover of wherein said release mechanism comprises a Nitinol® wire extending along said two outer edges.60. The self-disengaging pitot tube cover of claim 56 , wherein said latch comprises a fusible material.61. The self-disengaging pitot tube cover of claim 60 , further comprising multiple latches.62. The self-disengaging pitot tube cover of claim 61 , wherein said split cylinder configuration of said outer shell comprises multiple sets of two outer ...

Fluid Distribution Manifold and a Method for Manufacturing the Same

An additively manufactured fluid distribution manifold and a method of manufacturing the same are provided. The fluid distribution manifold includes a manifold body defining a plurality of internal passages that may extend through an insulation layer that extends at least partially around the manifold body. The insulation layer includes an external wall and an insulated wall separated by a gap, and the external wall may define a flat surface for receiving a heating element. The fluid distribution manifold may be part of a pitot static test module for testing pitot static tubes in low temperature environments. 1. An additively manufactured fluid distribution manifold comprising:a manifold body defining a plurality of internal passages; andan insulation layer extending at least partially around the manifold body, the insulation layer comprising an external wall and an insulated wall separated by a gap, wherein at least one of the internal passages extends through the insulation layer.2. The fluid distribution manifold of claim 1 , wherein the insulation layer is defined on an external portion of the manifold body.3. The fluid distribution manifold of claim 1 , comprising:a passage wall that extends through the gap and defines at least one internal passage, wherein the passage wall defines a fillet between the passage wall and at least one of the insulated wall and the external wall.4. The fluid distribution manifold of claim 1 , wherein the gap defines a gap thickness and the internal passages each define a passage thickness claim 1 , the gap thickness being substantially equivalent to the passage thickness.5. The fluid distribution manifold of claim 1 , wherein at least one of the plurality of internal passages extends along the insulation layer.6. The fluid distribution manifold of claim 1 , wherein the external wall defines a flat surface claim 1 , the fluid distribution manifold further comprising:a heating element mounted onto the flat surface.7. The fluid ...

SYSTEM AND METHOD FOR PROBE HEATER HEALTH INDICATION

A multi-function probe wire de-icing apparatus is described. The multi-function probe wire de-icing apparatus may include a multi-function probe wire, a main heater wire collocated with the multi-function probe wire, and a sacrificial wire deposed adjacent to the main heater wire. The sacrificial wire is configured to fail prior to the main heater wire failing. 1. A system for determining a main heater wire lifespan comprising:a portion of a channel;a main heater wire disposed within the portion of the channel; anda sacrificial wire disposed within the portion of the channel, wherein the sacrificial wire is configured to fail prior to the main heater wire.2. The system for determining main heater wire lifespan of claim 1 , wherein the main heater wire is collocated within a multi-function probe wire.3. The system for determining main heater wire lifespan of claim 1 , wherein the main heater wire and the sacrificial wire are shrouded within a length of dielectric material.4. The system for determining main heater wire lifespan of claim 1 , wherein the main heater wire is shrouded within a first length of dielectric material; and wherein the sacrificial wire is shrouded within a second length of dielectric material.5. The system for determining main heater wire lifespan of claim 1 , wherein failure of the sacrificial wire indicates replacement of the main heater wire should occur within a predetermined number of operational cycles.6. The system for determining main heater wire lifespan of claim 1 , wherein the main heater wire and the sacrificial wire comprise the same materials.7. The system for determining main heater wire lifespan of claim 1 , wherein the main heater wire and the sacrificial wire comprise different diameters.8. The system for determining main heater wire lifespan of claim 1 , wherein the sacrificial wire is configured to fail in response to a threshold associated with a desired parameter being exceeded.9. The system for determining main heater wire ...

APPARATUS AND METHOD FOR THIN FILM HEATING SYSTEMS FOR AIR DATA PROBES

In one embodiment, an air data probe is provided. The air data probe comprises an inner body having an outer surface, an outer body having an inner surface, a thin film heating system having a first surface and a second surface, a first thermally conductive adhesive disposed between the first surface and the outer surface, a second thermally conductive adhesive disposed between the second surface and the inner surface; and wherein the thin film heating system comprises one or more thin film heaters having one or more heating elements disposed in a thermally conductive, electrical insulator. 1. An air data probe , comprising:an inner body having an outer surface;an outer body having an inner surface;a thin film heating system having a first surface and a second surface;a first thermally conductive adhesive disposed between the first surface and the outer surface;a second thermally conductive adhesive disposed between the second surface and the inner surface; andwherein the thin film heating system comprises one or more thin film heaters having one or more heating elements disposed in a thermally conductive, electrical insulator.2. The air data probe of claim 1 , wherein the air data probe is a pitot tube.3. The air data probe of claim 1 , wherein the thin film heating system has a thickness less than 2 millimeters.4. The air data probe of claim 1 , wherein the thin film heating system further comprises a connection interface claim 1 , coupled to the one or more thin film heaters claim 1 , configured to be coupled to a processing system; andwherein the air data probe is configured to be mounted on an exterior surface of an apparatus.5. The air data probe of claim 4 , wherein a portion of the connection interface is in an opening in the inner body.6. The air data probe of claim 1 , wherein the thin film heating system further comprises one or more temperature sensors coupled to a connection interface.7. The air data probe of claim 1 , wherein the one or more thin film ...

Air data probe corrosion protection

A method can include vapor depositing a corrosion resistant coating to internal and external surfaces of a metallic air data probe. For example, vapor depositing can include using atomic layer deposition (ALD). The method can include placing the metallic air data probe in a vacuum chamber and evacuating the vacuum chamber before using vapor deposition. The corrosion resistant coating can be or include a ceramic coating. In certain embodiments, vapor depositing can include applying a first precursor, then applying a second precursor to the first precursor to form the ceramic coating.

Hybrid material aircraft sensors and method of manufacturing

An air data probe includes a probe body including a probe wall. The probe body is formed from a first material by direct energy metal deposition. An insert is positioned in the probe wall. The insert is formed from a second material different from the first material. The insert is encapsulated in the probe wall via the direct energy metal deposition. A method of forming an air data probe includes forming one or more thermally conductive inserts, and encapsulating the one or more inserts into a wall of an air data probe via direct energy metal deposition. The air data probe is formed from a first material and the one or more inserts are formed from a second material different from the first material.

Probe tip for air data probe

A probe assembly includes a heat source; and a probe tip configured to enhance conduction of heat provided by the heat source into a front end tip of the probe. The probe tip includes: a first region having high thermal conductivity in at least a z-direction, wherein the z-direction is parallel to an axis along which the probe tip is extended; and at least one additional region having thermal characteristics different from the first region.

DEVICE AND METHOD FOR CHECKING A PROBE FOR MEASURING THE PRESSURE OF A FLOW

A device is provided for checking a probe for measuring the pressure of a flow, the probe comprising an internal volume and at least one orifice communicating with the outside of the volume. The device comprises: an acoustic transmitter and an acoustic receiver; connection means to connect the device to the probe, such that the transmitter transmits an acoustic signal propagated in the internal volume, and such that the receiver picks up an acoustic signal observed in the internal volume; processing means suitable for comparing the observed signal to a reference signal. The connection means are configured in such a way that an incorrect connection of the probe disturbs the propagation in the internal volume of an acoustic signal transmitted by the transmitter. The processing means are configured to detect an incorrect connection of the probe by comparing the acoustic signal observed in the internal volume with the reference signal. 1. A device for checking a probe for measuring the pressure of a flow; the probe comprising an internal volume and at least one orifice communicating with the outside of the volume; the device comprising:an acoustic transmitter and an acoustic receiver,connection means intended to connect the device to the probe, in such a way that the transmitter transmits an acoustic signal that is propagated in the internal volume and in such a way that the receiver picks up an acoustic signal observed in the internal volume, andprocessing means suitable for comparing the observed signal to a reference signal;the connection means being configured in such a way that an incorrect connection of the probe disturbs the propagation in the internal volume of an acoustic signal transmitted by the transmitter, andthe processing means being configured to detect an incorrect connection of the probe by comparing the acoustic signal observed in the internal volume with the reference signal.2. The device according to claim 1 , wherein the connection means are ...

Method for checking a probe for measuring the pressure of a flow

A method for detecting the blocking of a drain hole of a pressure measurement probe by means of an acoustic checking device, the probe comprising an internal volume provided with at least one drain hole communicating with the outside of the volume, the checking device being able to be connected to the internal volume of the probe and comprising means for measuring an acoustic imprint of the internal volume. The method comprises: measuring an acoustic imprint by plugging the at least one drain hole from the outside of the volume; measuring an acoustic imprint without plugging the at least one drain hole from the outside of the volume; and comparing the two measured acoustic imprints.

DEVICE FOR CHECKING A PROBE FOR MEASURING THE PRESSURE OF A FLOW

A device is provided for checking a probe for measuring the pressure of a flow, the probe comprising: an internal volume; at least one orifice communicating with the outside of the volume; an acoustic loudspeaker, comprising an enclosure and a membrane sealing an opening of the enclosure; the opening being intended to be connected to the internal volume of the probe, so that the loudspeaker transmits an acoustic signal that is propagated through the opening into the internal volume; an acoustic receiver positioned in the enclosure of the loudspeaker that makes it possible to pick up an acoustic signal originating from outside the enclosure and passing through the membrane; and means for comparing the acoustic signal observed in the enclosure to a reference acoustic signal. 1. A device for checking a probe for measuring the pressure of a flow , the probe comprising:an internal volume,at least one orifice communicating with the outside of the volume,an acoustic loudspeaker, comprising an enclosure and a membrane sealing an opening of the enclosure; the opening being intended to be connected to the internal volume of the probe, so that the loudspeaker transmits an acoustic signal that is propagated through the opening into the internal volume,an acoustic receiver positioned in the enclosure of the loudspeaker that makes it possible to pick up an acoustic signal originating from outside the enclosure and passing through the membrane, andmeans for comparing the acoustic signal observed in the enclosure to a reference acoustic signal.2. The device according to claim 1 , in which the loudspeaker comprises sealing means opposing the ingress claim 1 , into the enclosure through the opening claim 1 , of liquid or of particles present in the internal volume of the probe.3. The device according to claim 1 , wherein the enclosure comprises a vent that makes it possible to maintain the interior of the enclosure at atmospheric pressure.4. The device according to claim 1 , further ...

CONVERSION BETWEEN CALIBRATED AIRSPEED AND TRUE AIRSPEED IN TRAJECTORY MODELING

Systems, methods, aircraft, non-transitory media, and memories are provided. An avionics system for an aircraft includes a storage device and one or more data processors. The storage device stores instructions for converting between airspeed types and the one or more data processors is configured to execute the instructions to: generate a calibrated airspeed of the aircraft; convert the calibrated airspeed to an actual true airspeed of the aircraft; determine an initial approximate relationship between the calibrated airspeed and a computed true airspeed as a function of a pressure altitude of the aircraft; generate an adjusted approximate relationship based on the actual true airspeed and the initial approximate relationship at a chosen pressure altitude; and estimate a future airspeed of the aircraft based on the adjusted approximate relationship and a future altitude. 1. An avionics system for an aircraft , the avionics system comprising:a storage device for storing instructions for converting between airspeed types; and generate a calibrated airspeed of the aircraft;', 'convert the calibrated airspeed to an actual true airspeed of the aircraft;', 'determine an initial approximate relationship between the calibrated airspeed and a computed true airspeed as a function of a pressure altitude of the aircraft;', 'generate an adjusted approximate relationship based on the actual true airspeed and the initial approximate relationship at a chosen pressure altitude; and', 'estimate a future airspeed of the aircraft based on the adjusted approximate relationship and a future altitude., 'one or more data processors configured to execute the instructions to2. The avionics system of claim 1 , wherein the one or more data processors is further configured to execute the instructions to generate the adjusted approximate relationship as an offset of the actual true airspeed from the initial approximate relationship based on a measured air density.3. The avionics system of claim ...

AIR DATA PROBE WITH IMPROVED PERFORMANCE AT ANGLE OF ATTACK OPERATION

An air data probe has a pitot tube with a tap at a forward end that defines an inner flow path. The inner flow path decreases in the cross-sectional area until reaching a throat. The inner flow path has cross-sections that are generally cylindrical and also has sections of removed material. Other embodiment have unique shapes. 1. An air data probe comprising:a pitot tube having a tap with a forward end, and defining an inner flow path, the inner flow path decreasing in cross-sectional area until reaching a throat; andsaid inner flow path having cross-sections which are generally cylindrical, and also having sections of removed material.2. The air data probe as set forth in claim 1 , wherein said sections of removed material include at least one bleed hole extending from an outer periphery of said pitot tube to communicate air into said inner flow path.3. The air data probe as set forth in claim 2 , wherein an inlet of said at least one bleed hole is upstream of said throat.4. The air data probe as set forth in claim 3 , wherein there are a plurality of said at least one bleed hole.5. The air data probe as set forth in claim 1 , wherein said removed material includes at least one slot claim 1 , with said generally cylindrical sections circumferentially spaced between said slots.6. The air data probe as set forth in claim 5 , wherein said at least one slot has a relatively circumferentially thin portion adjacent the forward end of said pitot tube and relatively circumferentially enlarged portions downstream of said relatively thinner portion.7. The air data probe as set forth in claim 6 , wherein there are a plurality of said at least one slots.8. The air data probe as set forth in claim 6 , wherein said at least one slot ends at said throat.9. The air data probe as set forth in claim 1 , wherein said removed portions end at said throat.10. The air data probe as set forth in claim 1 , wherein said pitot tube is provided with a relatively long nose portion of ...

PITOT PROBE WITH MANDREL AND PRESSURE SWAGED OUTER SHELL

A probe head of a pitot probe includes a mandrel having a helical groove, a heater within the helical groove of the mandrel such that an exterior surface of the heater is flush with an exterior surface of the mandrel, and an outer shell having an interior surface in air-tight contact with the mandrel and the heater. 1. A probe head of a pitot probe comprising:a mandrel having a helical groove;a heater within the helical groove of the mandrel, wherein the heater is deformed such that an exterior surface of the heater is flush with an exterior surface of the mandrel; andan outer shell having an interior surface in air-tight contact with the mandrel and the heater.2. The probe head of claim 1 , wherein the heater is directly between the mandrel and the outer shell.3. The probe head of claim 1 , wherein the heater is helical and the groove in the mandrel is helical.4. The probe head of claim 1 , wherein the outer shell has been pressure swaged to the mandrel and the heater.5. The probe head of claim 1 , wherein the exterior surface of the heater contacts the outer shell and the groove of the mandrel.6. A method for forming a pitot probe comprising:inserting a mandrel with a heater into an outer shell of a probe head; andpressure swaging the outer shell onto the mandrel and the heater such that an interior surface of the outer shell is sealed against an exterior surface of the mandrel and an exterior surface of the heater.7. The method of claim 6 , further including machining a groove into the mandrel.8. The method of claim 7 , wherein the groove is helical.9. The method of claim 6 , further including helically winding the heater into a helical groove in the mandrel.10. The method of claim 6 , wherein the heater is helically wound into a groove in the mandrel such that a portion of the exterior surface of the heater is radially outward from the exterior surface of the mandrel.11. The method of claim 6 , wherein inserting the mandrel with the heater into the outer shell ...

Ceramic probe head for an air data probe

A probe head for an air data probe includes a ceramic body and a heater embedded within the ceramic body.

Precipitation detection

An amount and type of precipitation, and a speed of a vehicle is determined. A component in the vehicle is actuated based on the amount and type of precipitation, and the speed of the vehicle.

TAKE-OFF APPARATUS AND METHOD FOR UNMANNED AERIAL VEHICLE WITHOUT LANDING GEAR

A take-off apparatus and method for unmanned aerial vehicle without landing gear includes an unmanned aerial vehicle, a carrier, a lock/release mechanism, a lift or airspeed sensing module, a signal processing module and a release motion sensing module. The lock/release mechanism locks the unmanned aerial vehicle onto the carrier and controllably releases the unmanned aerial vehicle from the carrier. The lift or airspeed sensing module senses an overall lift or airspeed of the unmanned aerial vehicle. When the lift or speed value of the unmanned aerial vehicle is greater than a predetermined threshold, it drives the lock/release mechanism into an unlocked state so that the unmanned aerial vehicle is released from the carrier and takes off more accurately and successfully. 1. A take-off apparatus for unmanned aerial vehicle without landing gear , comprising:an unmanned aerial vehicle, having an autopilot device for controlling a flight operation of the unmanned aerial vehicle;a carrier, fixed onto an auxiliary vehicle, for carrying the unmanned aerial vehicle, such that when the auxiliary vehicle is traveling in a traveling direction with respect to the earth's surface, the carrier carries the unmanned aerial vehicle to travel in the traveling direction with respect to the earth's surface;at least one lock/release mechanism, for locking the unmanned aerial vehicle onto the carrier in a locked state and controllably unlocking and releasing the unmanned aerial vehicle with respect to the carrier;a lift or airspeed sensing module configured to sense the overall lift or airspeed of the unmanned aerial vehicle carried by the auxiliary vehicle to generate a lift sensing signal or an airspeed sensing signal;a signal processing module configured to receive and process the lift sensing signal or the airspeed sensing signal to generate a lift value or an airspeed value, such that if the lift value or the airspeed value is greater than a predetermined threshold, then a control ...

PROBE FOR MEASURING THE TOTAL PRESSURE OF AN AIRFLOW AND METHOD OF USING THE PROBE

A probe for measuring the total pressure of an airflow is intended to equip an aircraft and a method of using the probe. The probe comprises a Pitot tube, two separate heating wires supplied separately and allowing each one to heat an external part of the probe, and means of distribution of a given maximum power to each of the two heating wires as a function of the current temperature of each of the two parts. A method consists in giving priority to the reaching of a predefined minimum temperature of a first of the two parts of the probe by allocating to the first part of the probe a predefined share of the given maximum power for as long as the temperature of the first part is below a predefined minimum temperature. 1. A probe for measuring the total pressure of an airflow , the probe being intended to equip an aircraft , the probe comprising a Pitot tube , two separate heating wires heated separately , allowing each one to heat a part of the probe , and means of distributing a given maximum power to each one of the two heating wires as a function of the current temperature of each of the two parts.2. The probe according to claim 1 , comprising fixing means designed to fix the probe to the skin of the aircraft and a mast connecting the Pitot tube to the fixing means and the first of the two heating wires being intended to heat the Pitot tube forming the first of the two parts and the second of the two heating wires being intended to heat the mast forming the second of the two parts.3. The probe according to claim 1 , the probe being intended to be supplied by means of an AC voltage and the distribution means being arranged to alternately distribute the total available power to each of the heating wires during a number of complete alternations of the AC voltage for each of the heating wires claim 1 , a ratio between the number of alternations of each of the heating wires being defined in order to obtain a desired power distribution.4. The probe according to claim 3 ...

TRIPLE-REDUNDANT AIR DATA SYSTEM ARCHITECTURE

A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first static pressure sensor. A second air data system for providing second aircraft air data parameter outputs is formed by a first electronics channel of a second MFP that is electrically coupled with a second static pressure sensor. A third air data system for providing third aircraft air data parameter outputs is formed by a second electronics channel of the first MFP that is electrically coupled with a second electronics channel of the first MFP. 1. A system comprising:a first multi-function probe (MFP) comprising a first plurality of pressure sensing ports for sensing pressure of an oncoming airflow about an aircraft exterior, the first MFP having a first electronics channel and a second electronics channel;a first static pressure sensor configured to sense static pressure of the oncoming airflow about the aircraft exterior and electrically coupled with the first electronics channel of the first MFP to form a first air data system providing first aircraft air data parameter outputs;a second MFP comprising a second plurality of pressure sensing ports for sensing the pressure of the oncoming airflow about the aircraft exterior, the second MFP having a first electronics channel and a second electronics channel; anda second static pressure sensor configured to sense the static pressure of the oncoming airflow about the aircraft exterior and electrically coupled with the first electronics channel of the second MFP to form a second air data system providing second aircraft air data parameter outputs;wherein the second electronics channel of the first MFP is electrically coupled with the second electronics channel of the second MFP to form a third air data system providing third aircraft air data parameter outputs.2. The system of claim 1 ,wherein the first MFP and the second ...

BOUNDARY LAYER FLOW SENSOR

Apparatus and methods described herein provide for boundary layer flow sensor and corresponding determination of the flow characteristics of an ambient airflow over an aerodynamic surface. According to one aspect of the disclosure provided herein, the boundary layer flow sensor includes a body configured for mounting within or below the aerodynamic surface, a pressure port configurable between an open state for taking pressure measurements within the boundary layer of the ambient airflow and a closed state that protects the pressure port from contaminants when not in use. 1. A boundary layer flow sensor , comprising:a body configured for mounting below an aerodynamic surface and having a pressure tube extending along a longitudinal axis of the body; anda pressure port configurable between an open state and a closed state, the pressure tube fluidly coupled to a lower portion of a boundary layer and aligned with an ambient airflow over the aerodynamic surface when the pressure port is in the open state, and the pressure tube fluidly decoupled from the boundary layer when the pressure port is in the closed state.2. The boundary layer flow sensor of claim 1 , further comprising a movable cover separating the pressure tube from the ambient airflow claim 1 , the movable cover movable between a lowered position in which the pressure port is in the closed state and a raised position in which the pressure port is in the open state.3. The boundary layer flow sensor of claim 2 , wherein the movable cover comprises a hinged cover configured to pivot along a downstream edge.4. The boundary layer flow sensor of claim 2 , wherein the movable cover comprises a deformable cover operative to change shape to reconfigure the pressure port between the open state and the closed state.5. The boundary layer flow sensor of claim 4 , wherein the deformable cover comprises a shape memory alloy configured to change shape in response to a threshold temperature.6. The boundary layer flow sensor ...

SPEEDOMETER INSENSTIVE TO ICY CONDITIONS AND HEAVY RAINFALL

The present invention relates to a speed measurement system allowing the relative speed V of a moving body in relation to an ambient air mass to be measured independently of the atmospheric conditions, the moving body being designed to move at least at subsonic and transonic speeds. The speed measurement system comprises:

Synthetic air data output generation

In one example, a method includes receiving, over an aircraft data communications bus, a plurality of non-pneumatic inputs corresponding to aircraft operational parameters. The method further includes processing the plurality of non-pneumatic inputs through an artificial intelligence network to generate an air data output value, and outputting the air data output value to a consuming system for use when a pneumatic-based air data output value is determined to be unreliable.

Air data probe contamination monitor

An aircraft air data probe contamination monitor includes at least two air data sensor probes, a first probe located on one side of the aircraft, a second probe located on an opposite side of the aircraft, each probe being operable to generate a parameter value from an airflow passing the in-flight aircraft. The monitor also includes a processor operable to compare the generated parameter value from the first probe to the generated parameter value from the second probe to determine if one of the first probe and the second probe is contaminated.

Air data system architecure including pneumatic and laser-based sensor measurements

A first air data system for providing first aircraft air data parameter outputs is formed by a first electronics channel of a first multi-function probe (MFP) that is electrically coupled with a first electronics channel of a second MFP to receive static pressure data from the second MFP. A second air data system for providing second aircraft air data parameter outputs is formed by a second electronics channel of the second MFP that is electrically coupled with a second electronics channel of the first MFP to receive static pressure data from the first MFP. A third air data system for providing third aircraft air data parameter outputs is formed by a laser air data sensor that is configured to emit directional light into airflow about the aircraft exterior and to generate the third aircraft air data parameter outputs based on returns of the emitted directional light.

UNMANNED AERIAL VEHICLE CONTROL METHOD, AND UNMANNED AERIAL VEHICLE

A method for controlling an unmanned aerial vehicle includes generating a course reversal command to control the unmanned aerial vehicle to execute a course reversal action. The course reversal action includes at least a cruising stage. The method further includes, in the cruising stage, measuring one or more flight parameters of the unmanned aerial vehicle and controlling the unmanned aerial vehicle to enter a high wind course reversal stage in response to determining that the unmanned aerial vehicle is in a high wind retardant state according to the one or more flight parameters. The method also includes, in the high wind course reversal stage, measuring the one or more flight parameters, and controlling the unmanned aerial vehicle to return to the cruising stage in response to determining that the unmanned aerial vehicle is not in the high wind retardant state according to the one or more flight parameters. 1. A method for controlling an unmanned aerial vehicle comprising:generating a course reversal command to control the unmanned aerial vehicle to execute a course reversal action, the course reversal action includes at least a cruising stage;in the cruising stage, measuring one or more flight parameters of the unmanned aerial vehicle, and controlling the unmanned aerial vehicle to enter a high wind course reversal stage in response to determining that the unmanned aerial vehicle is in a high wind retardant state according to the one or more flight parameters; andin the high wind course reversal stage, measuring the one or more flight parameters, and controlling the unmanned aerial vehicle to return to the cruising stage in response to determining that the unmanned aerial vehicle is not in the high wind retardant state according to the one or more flight parameters.2. The method according to claim 1 , wherein the high wind retardant state includes at least one of a speed retardant state or a heading deviation state.3. The method according to claim 2 , wherein: ...

SYSTEM AND METHOD FOR PITOT TUBE BLOCKAGE DETECTION

A method of detecting blockage of a pitot tube includes measuring a pitot tube temperature via one or more temperature sensors located inside a pitot tube, measuring an outside ambient air temperature, comparing the measured pitot tube temperature to a minimum pitot tube temperature threshold for the measured outside ambient air temperature, and determining the pitot tube has a blockage condition when the measured pitot tube temperature is below the minimum pitot tube temperature threshold. 1. A method of detecting blockage of a pitot tube , comprising:measuring a pitot tube temperature via one or more temperature sensors disposed inside a pitot tube;measuring an outside ambient air temperature;comparing the measured pitot tube temperature to a minimum pitot tube temperature threshold for the measured outside ambient air temperature; anddetermining the pitot tube has a blockage condition when the measured pitot tube temperature is below the minimum pitot tube temperature threshold.2. The method of claim 1 , further comprising:determining whether a pitot tube heater is operational; andselecting the minimum pitot tube temperature threshold based on the measured outside ambient air temperature and an operational status of the pitot tube heater.3. The method of claim 1 , further comprising alerting a flight crew regarding the blockage condition.4. The method of claim 3 , wherein the alert is a visual and/or aural alert.5. The method of claim 1 , wherein the minimum pitot tube temperature threshold is obtained from a temperature calibration database.6. The method of claim 1 , wherein measuring a pitot tube temperature comprises measuring three of more pitot tube temperatures via three or more temperature sensors located at three or more longitudinal locations of the pitot tube.7. The method of claim 6 , wherein the three or more temperature sensors are located at three or more circumferential locations of the pitot tube.8. A pitot tube system claim 6 , comprising:a pitot ...

Apparatus and methods for a portable avionics system to provide flight information in a general aviation aircraft

Apparatus and methods for a portable avionics system to provide flight information in a general aviation aircraft are described herein. The portable avionics system includes a portable sensor pod and a head mounted display system. The portable sensor pod houses sensors and solid state components in a portable container, thereby allowing the pod to be ported to a plurality of general aviation aircraft. The head mounted display system includes a hardware box in wireless communication with the portable sensor pod. Sensor data from the portable sensor pod is transmitted to the head mounted display system and processed so that essential flight information becomes readily available on a wearable display. The wearable display conveys essential flight data to a general aviation pilot without interfering with the pilot's vision.

FLIGHT CONTROL SYSTEM FOR DETERMINING ESTIMATED DYNAMIC PRESSURE BASED ON LIFT AND DRAG COEFFICIENTS

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality first of operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient. 1. A flight control system for an aircraft , the flight control system comprising:one or more processors; and receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft;', 'determine a drag coefficient and a lift coefficient based on the plurality first of operating parameters; and', 'determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient., 'a memory coupled to the one or more processors, the memory storing data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to2. The flight control system of claim 1 , wherein the one or more processors executes instructions to:receive as input a measured longitudinal acceleration and a measured vertical acceleration;determine an estimated longitudinal acceleration and an estimated vertical acceleration based on the drag coefficient and the lift coefficient;determine an acceleration error value for a first difference between the estimated longitudinal acceleration and the estimated vertical acceleration and a second difference between the measured longitudinal acceleration and the measured vertical acceleration; anddetermine a residual Kalman value by ...

System for Ensuring Failsafe Operation of Pitot Tube Covers for Multiple Types of Pitot Tubes

The present invention is directed to multiple arrangements of a self-disengaging pitot tube cover, which can be triggered by a plurality of different environmental conditions while the cover admits to a plurality of different latching mechanisms and opening configurations to guarantee the expeditious, automatic removal of the pitot tube cover while avoiding damage or contamination of the pitot tube itself. 1. A self-disengaging pitot tube cover having an exterior surface and an interior structure for supporting said exterior surface and for receiving and supporting a pitot tube , said pitot tube cover constituted in two separate connectable halves , said halves of said pitot tube cover together comprising:a) a plurality of heat-resistant, flexible, split discs supported by said interior structure; andb) an upper connecting mechanism located proximate opposing upper longitudinal edges of said halves and formed by a single heat-sensitive fusible link inserted between clips from each said half.2. The self-disengaging pitot tube cover of claim 1 , further comprising:c) a lower connecting mechanism arranged along the lower longitudinal edges of said halves, opposite said upper longitudinal edges, and comprising a flange with at least one latch structure.3. The self-disengaging pitot tube cover of claim 2 , wherein said lower connecting mechanism includes three latches claim 2 , each said latch having a hook on a first half and a complementary aperture in said flange on said second half.4. The self-disengaging pitot tube cover of claim 1 , wherein said pitot tube cover comprises four heat-resistant claim 1 , flexible split discs claim 1 , each said split disc having an aligned aperture to collectively hold an external pitot tube.5. The self-disengaging pitot tube cover of claim 4 , wherein said aligned apertures are sized to prolapse around said external pitot tube claim 4 , exerting a spring-like force to hold said pitot tube claim 4 , and to drive said halves away from ...

Probe tip for air data probe

A probe assembly includes a heat source; and a probe tip configured to enhance conduction of heat provided by the heat source into a front end tip of the probe. The probe tip includes: a first region having high thermal conductivity in at least a z-direction, wherein the z-direction is parallel to an axis along which the probe tip is extended; and at least one additional region having thermal characteristics different from the first region.

AIR DATA PROBE WITH OPTICAL PRESSURE INTEGRATION

An air data probe includes a probe head, a port within the probe head in fluid communication with external airflow, and a pneumatic pressure sensor mounted within the port. 1. An air data probe comprising:a probe head;a port within the probe head in fluid communication with external airflow; anda pneumatic pressure sensor mounted within the port.2. The air data probe of claim 1 , wherein the pneumatic pressure sensor is flush-mounted within the port.3. The air data probe of claim 1 , wherein the port is a static port.4. The air data probe of claim 1 , wherein the port is a pitot port.5. The air data probe of claim 1 , wherein the port is a pitot port and the pneumatic pressure sensor is mounted downstream of a water dam.6. The air data probe of claim 1 , wherein the pneumatic pressure sensor is an optical fiber pressure sensor.7. The air data probe of claim 6 , wherein the optical fiber pressure sensor utilizes a fiber Bragg grating to perform pressure measurement.8. The air data probe of claim 6 , wherein the optical fiber pressure sensor utilizes a Fabry-Perot interferometer to perform pressure measurement.9. The air data probe of claim 1 , wherein the pneumatic pressure sensor includes a diaphragm and an optical fiber connected to the diaphragm such that the optical fiber extends through the probe head.10. The air data probe of claim 9 , wherein the diaphragm is made of sapphire.11. An air data probe comprising:a body;a port within the body in fluid communication with external airflow; andan optical fiber pressure sensor mounted within the port.12. The air data probe of claim 11 , wherein the air data probe is a flush static plate.13. The air data probe of claim 11 , wherein the optical fiber pressure sensor is flush-mounted within the port.14. The air data probe of claim 11 , wherein the port is a static port.15. The air data probe of claim 11 , wherein the port is a pitot port.16. The air data probe of claim 11 , wherein the body is a probe head.17. The air ...

Air data probes

An air data probe includes a probe head defining a longitudinal axis between a forward tip and aft base. A port opening is defined in the forward tip. A first conduit is in fluid communication with the port opening to guide fluid flow from the port opening to a first chamber. The first chamber is downstream from the port opening. A second conduit, offset radially and circumferentially from the first conduit, is in fluid communication with the first chamber to guide fluid flow from the first chamber to a second chamber. The second chamber is downstream from the first chamber. The offset between the first and second conduits is configured to prevent particle ingestion from the port opening from entering the second conduit.

METHODS AND SYSTEMS FOR DETERMINING AIRSPEED OF AN AIRCRAFT

Aircraft and methods and systems for determining airspeed of an aircraft. The methods and systems allow for calculation of airspeed in near-ground and on-ground aircraft operation. A GPS altitude and a vertical acceleration of the aircraft are obtained for a current time frame. A geometric altitude for the previous time frame is determined, and the difference between the GPS altitude and geometric altitude are combined with the vertical acceleration to calculate a geometric altitude rate of change. The geometric altitude rate of change is used to calculate a pressure altitude rate of change, which is used to calculate a pressure altitude for the aircraft. A static pressure is calculated from the pressure altitude, and the airspeed is calculated using the static pressure. 1. A method of determining an airspeed of an aircraft , the method comprising:obtaining, from a GPS device of the aircraft, a GPS altitude of the aircraft for a current time frame;obtaining, from an inertial reference device of the aircraft, a vertical acceleration of the aircraft for the current time frame;obtaining a geometric altitude of the aircraft for a previous time frame, the previous time frame occurring prior to the current time frame;determining a difference between the GPS altitude and the geometric altitude;calculating a geometric altitude rate of change of the aircraft using the vertical acceleration and the difference between the GPS altitude and the geometric altitude;calculating a pressure altitude rate of change using the geometric altitude rate of change;calculating a pressure altitude for the current time frame from the pressure altitude rate of change;calculating a static pressure for the current time frame using the pressure altitude; andcalculating the airspeed of the aircraft using the static pressure.2. The method of wherein the GPS altitude is a first GPS altitude claim 1 , the vertical acceleration is a first vertical acceleration claim 1 , the geometric altitude of the ...

IMAGE-BASED INSPECTION FOR PHYSICAL DEGRADATION OF AN AIR DATA PROBE

Inspecting an air data probe for physical degradation includes generating a silhouette of the air data probe based on an identification of the air data probe to be inspected. The silhouette is simultaneously displayed with an image of the air data probe produced by a camera, and the displayed image of the air data probe is caused to conform to the silhouette on the display. An image of the air data probe is captured while the displayed image of the air data probe conforms to the silhouette on the display. The captured image is analyzed to identify physical degradation of the air data probe. A maintenance recommendation for the air data probe is generated based on the identified physical degradation. 1. A method of inspecting an air data probe for physical degradation , the method comprising:providing an identification of the air data probe to be inspected;generating a silhouette of the air data probe based on the identification, the silhouette comprising an outline of a periphery of at least a portion of the air data probe;simultaneously displaying, on a display, the silhouette and an image of the air data probe produced by a camera, the silhouette displayed as a graphical overlay on the image of the air data probe;causing the displayed image of the air data probe to conform to the silhouette on the display by adjusting at least one of a relative location, a relative orientation, and a relative size of the displayed image of the air data probe and the silhouette so that the displayed image of the air data probe conforms to the silhouette on the display;capturing an image of the air data probe while the displayed image of the air data probe conforms to the silhouette on the display;analyzing the captured image to identify physical degradation of the air data probe;generating, based on the identified physical degradation of the air data probe, a maintenance recommendation for the air data probe; andoutputting the maintenance recommendation.2. The method of claim 1 , ...

Dust measurement system for filter

A dust measurement system measuring the build up of dust on a filter includes a monitoring device, a pitot tube, and an environment control unit. The pitot tube head aligned with the filter. The environment control unit receives the measured speed of air flow and compares the measured speed with a preset value. When the measuring speed is greater than the preset value, the environment control unit outputs the first control signal to the monitoring device, to control the monitoring device to display that the filter does not need to be replaced. When the measuring speed is less than or equal to the preset value, the environment control unit outputs the second control signal to the monitoring device, to control the monitoring device to display that the filter needs to be replaced.

AIR DATA PROBES

An air data probe includes a probe head defining a longitudinal axis between a forward tip and aft base. A port opening is defined in a side of the probe head and opening at an angle with respect to the longitudinal axis. A bulkhead within the probe head has a chamber in fluid communication with the port opening. The chamber includes a single chamber inlet having an elongated cross-sectional shape. The single elongated chamber inlet is in fluid communication with two downstream pressure conduits to provide redundancy in case one of the two pressure conduits is blocked. 1. An air data probe comprising:a probe head defining a longitudinal axis between a forward tip and aft base;a port opening defined in a side of the probe head and opening at an angle with respect to the longitudinal axis; anda bulkhead within the probe head having a chamber in fluid communication with the port opening, wherein the chamber includes a single chamber inlet having an elongated cross-sectional shape, and wherein the single elongated chamber inlet is in fluid communication with two downstream pressure conduits to provide redundancy in case one of the two pressure conduits is blocked.2. An air data probe as recited in claim 1 , further comprising a thermocouple having a sense end in the forward tip to measure the temperature in the forward tip.3. An air data probe as recited in claim 2 , wherein the sense end of the thermocouple is held by the bulkhead.4. An air data probe as recited in claim 2 , further comprising a strut extending from the aft base of the probe head claim 2 , wherein the thermocouple extends from the forward tip of the probe head to a base of the strut and terminates in a thermocouple connector.5. An air data probe as recited in claim 2 , further comprising a heater coil positioned within the probe head claim 2 , wherein the thermocouple includes a thermocouple coil claim 2 , wherein windings of the thermocouple coil are wound between windings of the heater coil.6. An air ...

Air data probe assembly method

An air data probe includes a strut including a socket defining an interior surface of the strut and an interior groove extending radially into the interior surface. The air data probe also includes a probe head partially positioned within the socket, the probe head including an exterior surface and an exterior groove extending radially into the exterior surface, the exterior groove being axially alignable with the interior groove. The air data probe further includes a retaining ring partially positionable within the exterior groove and partially positionable within the interior groove when the exterior groove and the interior groove are axially aligned to axially retain the probe head to the strut while allowing the probe head to rotate relative to the strut.

METHOD OF FORMING AN ICE RESISTANT PITOT TUBE

A method of forming a pitot tube includes forming a substantially cylindrical body portion including an outer surface, a tip portion having an inlet opening and an interior defining a flow passage, radially tapering the outer surface from the body portion toward the inlet opening, and disposing at least one electrical coil including one or more coil wraps along the flow passage of the pitot tube. 1. A method of forming a pitot tube comprising:receiving a pitot tube having a substantially cylindrical body portion including an outer surface, a tip portion having an inlet opening, an interior defining a flow passage, a radially tapering outer surface that tapers from the body portion toward the inlet opening and at least one bulkhead positioned along the flow passage to limit travel of particles ingested into the pitot tube; andarranging one or more coil wraps along the flow path downstream of the at least one bulkhead.2. The method of claim 1 , wherein the radially tapered outer surface has a concave curve.3. The method of claim 1 , wherein arranging the at least one electrical coil includes arranging the one or more coil wraps to establish a variable watt density along the flow path.4. The method of claim 1 , further comprising: forming at least one drain opening in the substantially cylindrical body portion fluidically connecting the flow path and the outer surface.5. The method of claim 4 , wherein forming the at least one drain opening includes forming the drain opening upstream of the at least one bulkhead.6. The method of claim 5 , wherein forming the at least one drain opening upstream of the aft most bulkhead includes arranging the at least one drain opening directly adjacent the at least one bulkhead. This application is a continuation of U.S. application Ser. No. 14/922,659 filed Oct. 26, 2015, which is a continuation of U.S. application Ser. No. 14/065,878 filed Oct. 29, 2013 (now U.S. Pat. No. 9,207,253, Issued on Dec. 8, 2015), which claims priority to U. ...

DYNAMIC PRESSURE PROBE FOR A SENSOR DEVICE AND FLYING OBJECT WITH A SENSOR DEVICE

A dynamic pressure probe for a sensor device can determine the relative speed of an object and a medium surrounding that object, in particular for gathering flight data on a flying object. The dynamic pressure probe includes an outer body with a wall in which an inflow opening is formed and which encloses an inner space, as well as an inner body which is arranged at least partially in the inner space and which encloses a measuring space as a constituent part of the inner space. Medium is able to flow through the inflow opening and is able to be dammed in the measuring space. The inner body is able to be acted upon with a protective fluid, in particular a gas, on a side remote from the measuring space and includes passages through which protective fluid is able to flow into the measuring space. 1. A dynamic pressure probe for a sensor device for determining the relative speed of an object and a medium surrounding said object , wherein the dynamic pressure probe comprises an outer body with a wall in which an inflow opening is formed and which encloses an inner space , as well as an inner body which is arranged at least partially in the inner space and which encloses a measuring space as a constituent part of the inner space , wherein medium is able to flow through the inflow opening and is able to be dammed in the measuring space , and wherein the inner body is able to be acted upon with a protective fluid on a side remote from the measuring space and comprises passages through which protective fluid is able to flow into the measuring space.2. The dynamic pressure probe in accordance with claim 1 , wherein the dynamic pressure probe is of tubular configuration at least in sections claim 1 , with a tubular outer body and a tubular inner body aligned coaxial to the outer body.3. The dynamic pressure probe in accordance with claim 1 , wherein the dynamic pressure probe has a round or polygonal cross section in relation to an inflow direction of the medium through the ...

Pitot tube

A pitot tube includes an outer tube extending from a first tube end to second tube end, the second tube end defining a tip portion of the pitot tube, the tip portion including an inlet opening. A tube sleeve inside of the outer tube at least partially defines a tube passage extending from the first tube end to the second tube end. The tube sleeve includes a sleeve outer surface having a sleeve body portion having a first outer diameter and a sleeve tip portion located at the tip portion of the pitot tube. The sleeve tip portion has a second outer diameter smaller than the first outer diameter. A heating element is located between the outer tube and the tube sleeve at at least the sleeve tip portion.

Air Pressure Probe

An air pressure probe (APP) relates to the field of aviation and is intended to determine aircraft flight parameters or wind tunnel flow parameters. The APP comprises a head part with intake holes located thereon, which are connected by channels to couplers, and a support, attached to the head part from behind. The surface of the head part is provided with flow vortex generators. The generators can be in the form of indentations or protrusions of various shapes on the surface of the air pressure probe, or in the form of ribs formed as a result of the mating of elements of the flat or curved planes that form the surfaces of the head part and the support. The technical result is an increased operational range of measurement and a wider field of practical application. 110-. (canceled)11. An air pressure probe comprising a head part with intake holes located thereon , the intake holes being connected via pneumatic channels with couplers , and a support , attached to the head part from behind , further comprising flow vortex generators located on a surface of the head part to thereby secure supercritical flow-around and eliminate the influence of the Re number.12. The air pressure probe of claim 11 , wherein the flow vortex generators include ribs formed by mating surface elements at an angle ξ≠0 with curvature lying between 0 and ±0.9/H and outline dimensions between 0.01H and 0.4H claim 11 , where H is the minimum outline dimension of the head part.13. The air pressure probe of claim 12 , wherein the head part is shaped as a convex polyhedron with a number of flat faces falling within the range of 10÷1000.14. The air pressure probe of claim 13 , wherein the head part is shaped as an icosahedron.15. The air pressure probe of claim 13 , wherein the head part is shaped as a dodecahedron.16. The air pressure probe of claim 13 , wherein the head part is shaped as a polyhedron with 192 faces.17. The air pressure probe of claim 13 , wherein the intake holes are located on the ...

Aircraft Airflow Sensor Probe and Process of Implementing an Aircraft Sensor Probe

An aircraft airflow sensor probe includes an airflow assembly or a cone assembly configured to sense a direction of local airflow outside an aircraft; a shaft configured to rotatably hold the assembly and allow rotational movement of the assembly; and a motor connected to the shaft and configured to generate a torque to damp the rotational movement of the shaft as well as the assembly. The sensor probe further includes an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the assembly and a sensor configured to sense a position of the assembly and provide the position of the assembly to the angle of attack processor. An aircraft airflow sensor process is disclosed as well. 1. An aircraft airflow sensor probe comprising:an airflow assembly configured to sense a direction of local airflow outside an aircraft;a shaft configured to rotatably hold the airflow assembly and allow rotational movement of the airflow assembly;a motor connected to the shaft and configured to generate a torque to damp the rotational movement of the shaft as well as the airflow assembly;an angle of attack processor configured to control the motor to generate the torque to damp the rotational movement of the shaft as well as the airflow assembly; anda sensor configured to sense a position of the airflow assembly and provide the position of the airflow assembly to the angle of attack processor,wherein the airflow assembly comprises one of the following: a vane assembly configured to sense a direction of local airflow outside an aircraft and a cone assembly configured to sense a direction of local airflow outside an aircraft.2. The aircraft airflow sensor probe according to further comprising:at least one air pressure sensor configured to determine an air pressure received by an air pressure sensor port;wherein the air pressure comprises at least one of the following: a static air pressure, airflow velocity, and a ...

AIR DATA SENSOR FOR AN AIRCRAFT

Air data sensing apparatus comprising: an aircraft panel; a blister arranged on a surface of the aircraft panel, the blister comprising an upstream portion and a downstream portion, the upstream portion being rounded in three dimensions and having a rounded outer edge surface spaced laterally from the aircraft panel; a plurality of apertures in the surface of the aircraft panel, the apertures being adjacent to the upstream portion of the blister, and spaced from the blister; a plurality of conduits, each conduit being in fluid communication with a respective aperture; and one or more pressure sensors arranged to measure a pressure in each of the conduits. 1. Air data sensing apparatus comprising:an aircraft panel;a blister arranged on a surface of the aircraft panel, the blister comprising an upstream portion and a downstream portion, the upstream portion being rounded in three dimensions and having a rounded outer edge surface spaced laterally from the aircraft panel;a plurality of apertures in the surface of the aircraft panel, the apertures being adjacent to the upstream portion of the blister, and being spaced from the blister;a plurality of conduits, each conduit being in fluid communication with a respective aperture; andone or more pressure sensors arranged to measure a pressure in each of the conduits.2. Air data sensing apparatus according to wherein the shape of the upstream portion is that of part of an ellipsoid.3. Air data sensing apparatus according to wherein the shape of the upstream portion is that of part of a sphere.4. Air data sensing apparatus according to claim 1 , wherein the downstream portion of the blister tapers from the forward portion to nothing at a distal end.5. Air data sensing apparatus according to to claim 1 , wherein the apertures are adjacent to the upstream portion of the blister only and not the downstream portion of the blister.6. Air data sensing apparatus according to claim 1 , wherein there at least five apertures.7. Air ...

PROCESS FOR MANUFACTURING A PITOT TUBE HAVING A GRAPHITE INSERT EMBEDDED THEREIN

Disclosed is a process of manufacturing a pitot tube assembly including: obtaining a metal cylindrical tube having a first axial portion that is a first material blank for an assembly inlet portion of the pitot tube assembly and a second axial portion that is a second material blank for a body portion of the pitot tube assembly; nesting the first axial portion of the tube within a cylindrical graphite insert; nesting the cylindrical graphite insert within a cylindrical sheath; constraining axial motion of the insert; performing laser scanning to the assembly inlet portion; and performing additive manufacturing to the pitot tube assembly inlet portion. 1. A process of manufacturing a pitot tube assembly comprising:obtaining a cylindrical tube having a first axial portion that is a first material blank for an assembly inlet portion of the pitot tube assembly and a second axial portion that is a second material blank for a body portion of the pitot tube assembly;nesting the first axial portion of the cylindrical tube within a cylindrical graphite insert;nesting the cylindrical graphite insert within a cylindrical sheath;constraining axial motion of the cylindrical graphite insert;performing laser scanning to the assembly inlet portion; andperforming additive manufacturing to the assembly inlet portion.2. The process of claim 1 , wherein the tube is nickel or a nickel alloy and the insert is pyrolytic or annealed pyrolytic graphite (APG).3. The process of claim 1 , comprising performing hot iso-static processing (HIPping) or heat treating of the assembly after performing laser metal deposition.4. The process of claim 1 , comprising securing the assembly with a rotary chuck when performing additive manufacturing or preforming additive manufacturing with a multi-axis machine.5. The process of claim 1 , wherein nesting the first axial portion of the tube within the insert includes providing a transition fit therebetween.6. The process of claim 5 , wherein nesting the ...

ICE PREVENTION DAM FOR, AND METHOD FOR FORMING, A PITOT TUBE

In an embodiment, an ice-prevention dam for a pitot tube includes a body and a head. The body includes a notch having a substantially planar back, and the head extends from the body and has a substantially planar side that is substantially parallel to the back of the notch. Such a dam can prevent ice accumulation in a pitot tube, and can facilitate proper positioning of the dam. For example, during manufacture of a pitot tube, an assembler inserts the dam into a hole in a side of a pitot-tube body having a front opening such that the head of the dam is located outside of the pitot-tube body and a body of the dam is located inside of the pitot-tube body. Next, the assembler positions the dam by causing the substantially planar side of the dam head to be substantially parallel with the front opening of the pitot-tube body. 1. A dam for a pitot tube , the dam comprising:a body including a notch having a substantially planar back; anda head extending from the body and having a substantially planar side that is substantially parallel to the back of the notch.2. The dam of wherein the body has a substantially cylindrical shape.3. The dam of wherein:the body has a longitudinal axis; andthe back of the notch is substantially parallel to the longitudinal axis.4. The dam of wherein:the body has a longitudinal axis and a diameter in a dimension that is normal to the longitudinal axis; andthe notch has a width that is less than the diameter.5. The dam of wherein:the body has a longitudinal axis and a radius in a dimension that is normal to the longitudinal axis; andthe notch has a width that is greater than the radius.6. A pitot tube claim 1 , comprising:a tube body defining an inlet;at least one hole formed in the tube body; andat least one dam respectively disposed within the at least one hole, each dam having a respective dam body that includes a notch having a substantially planar back that faces, and that is substantially parallel to, the inlet, at least a portion of the ...

Arrangement of dams in air data probe

An air data probe is provided. The air data probe includes a pitot probe having a mounting base or flange, support strut, and tube with a forward facing inlet that is configured to capture a total pressure of the surrounding air, at least three dams placed within the tube of the pitot probe for blocking the ballistic trajectory of water droplets or ice crystals from passing directly through the tube to a downstream pressure sensing element, and a heater element integrated into the tube of the pitot probe on the outside of the dams. The at least three dams are oriented within the tube of the pitot probe in such a way that the dam locations are configured for two or more installations of the air data probe.

CO-LOCATION OF HIGH-MAINTENANCE AIR DATA SYSTEM COMPONENTS INTO ONE LRU

Systems and methods for the co-location of high-maintenance air data system components into one LRU are disclosed. In at least one embodiment, an air data sensing line-replaceable unit (LRU) comprises at least one pressure sensor and at least one probe or port coupled to the at least one pressure sensor. The at least one probe or port conduits air located outside the air data sensing LRU to the at least one pressure sensor. Further, the at least one probe or port and the at least one pressure sensor are connected to each other by a permanent connection. 1. An air data sensing line-replaceable unit (LRU) comprising:at least one pressure sensor; and wherein the at least one probe or port conduits air located outside the air data sensing LRU to the at least one pressure sensor, and', 'wherein the at least one probe or port and the at least one pressure sensor are connected to each other by a permanent connection., 'at least one probe or port coupled to the at least one pressure sensor,'}2. The air data sensing LRU of claim 1 , wherein the at least one probe or port comprises at least one of the following: one or more static ports claim 1 , one or more pitot tubes claim 1 , one or more pitot-static tubes claim 1 , or one or more angle-of-attack vanes.3. The air data sensing LRU of claim 1 , wherein the permanent connection is formed by welding the at least one probe or port to the at least one pressure sensor.4. The air data sensing LRU of claim 1 , wherein the permanent connection is formed by bonding the at least one probe or port to the at least one pressure sensor.5. The air data sensing LRU of claim 1 , wherein the permanent connection is formed by brazing the at least one probe or port to the at least one pressure sensor.6. The air data sensing LRU of claim 1 , wherein the at least one pressure sensor converts the air that the at least one probe or port conduits to the at least one pressure sensor into an electrical signal.7. The air data sensing LRU of claim 6 , ...