ПРИЕМНИК СТАТИЧЕСКОГО И ПОЛНОГО ДАВЛЕНИЙ ПРЕИМУЩЕСТВЕННО ДЛЯ ВЕРТОЛЕТОВ

... 1. Приемник статического и полного давлений преимущественно для вертолетов, содержащий цилиндрическую воспринимающую часть с приемным отверстием, отверстия отбора статического давления, расположенные на компенсационном контуре, трубопровод статического давления, трубопровод полного давления, элементы обогрева приемника и державку, отличающийся тем, что цилиндрическая воспринимающая часть с приемным отверстием имеет угол скоса приемного отверстия к продольной оси приемника, компенсационный контур имеет цилиндрическую или профилированную поверхность, причем одно отверстие отбора статического давления используется и как дренажное, а остальные отверстия выполнены по окружности под углом к вертикальной оси симметрии приемника и под углом к продольной оси приемника.2. Приемник статического и полного давлений преимущественно для вертолетов по п.1, отличающийся тем, что угол скоса цилиндрической воспринимающей части с приемным отверстием к продольной оси приемника изменяется в диапазоне от 40º ...

УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ СКОРОСТИ САМОЛЕТА

... 1. Устройство для измерения скорости самолета, содержащее наконечник с приемником полного давления и камерой статического давления, снабженным отводными трубками, корпус, который соединен с наконечником посредством шарнира и выполнен со сквозным каналом под отводные трубки, отличающееся тем, что, с целью повышения удобства эксплуатации, в него введен трубчатый держатель наконечника, который выполнен с внутренним коническим упором, взаимодействующим с ответным наружным коническим упором, выполненным на корпусе, цилиндрической опорой, охватывающей наконечник с возможностью перемещения вдоль него, и резьбовым пояском, взаимодействующим с нарезным пояском, выполненным на наконечнике со стороны корпуса, а шарнир выполнен с одной степенью свободы в плоскости, проходящей через продольную ось наконечника и корпуса, и расположен между этой осью и трубчатым держателем. 2. Устройство по п.1, отличающееся тем, что оно снабжено фиксатором, включающим подпружиненную защелку, установленную в корпусе за ...

УСТРОЙСТВО ДЛЯ ИЗМЕРЕНИЯ ВОЗДУШНОЙ СКОРОСТИ СВЕРХЛЕГКИХ ЛЕТАТЕЛЬНЫХ АППАРАТОВ

Изобретение относится к измерительной технике и может быть использовано для измерения воздушной скорости сверхлегких летательных аппаратов (СЛА), летный диапазон скоростей которых находится в пределах 10 - 40 м/с. Устройство содержит корпус с проточным каналом и закрепленную внутри корпуса трубку приема воздушного давления. Проточный канал корпуса выполнен состоящим из конфузорной, цилиндрической и диффузорной частей. Трубка приема воздушного давления закреплена в диффузорной части проточного канала таким образом, что приемник статического давления расположен напротив цилиндрической части канала. Приемник полного давления трубки вынесен за торец корпуса на расстояние не менее одного диаметра трубки.

Многофункциональный приемник воздушных давлений

Полезная модель относится к измерительной технике и может быть использована для измерения высотно-скоростных параметров и аэродинамических углов в системах воздушных сигналов летательных аппаратов. Многофункциональный приемник воздушных давлений содержит стойку, в передней части которой расположено осесимметричное тело с тремя группами отверстий для определения полного давления, статического давления и угла атаки, пневмотрассы и электронагревательные элементы, расположенные внутри стойки и осесимметричного тела, влагостойник испарителя и блок осушителя воздуха, соединенные с отверстиями для определения угла атаки, а количество отверстий для определения угла атаки больше двух.

Устройство для измерения и регистрации скорости вертикальных потоков воздуха в атмосфере с горизонтально летящего самолета

Зонд для измерения полного давления

INTEGRIERBARER TRAGFLÄCHENMESSAUFNEHMER FÜR DIE GESAMTTEMPERATUR

Geschwindigkeitsmesser fuer Schiffe

Mittelwerte bildender Pitotmessfühler.

ANEMOMETER POLE FOR MEASURING THE RELATIVE SPEED BETWEEN A FLUID AND A SUPPORT, ESPECIALLY FOR AN AIRCRAFT

Schiffslog mit Pitotrohr

First equipment heating device

Additive manufacturing method for an avionic equipment

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 25 comprising at least one part intended to be arranged at a skin 27 of the aircraft and means for heating that part. The heating means includes a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates. The closed circuit comprises 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 120 for fastening on the skin of the aircraft from which support means 130, for a Pitot tube 140, extend.

Improvements relating to pressure heads for aircraft

... 565,792. Pressure heads for aircraft. AVIMO, Ltd., and STEVENS, H. C. M. April 6, 1943, No. 5491. [Class 69 (i)] A pressure head for measuring the speed of aircraft comprises a body part a of small diameter within which is inserted an electric heater b extending along the whole or greater part of the body part, hollow contacts c, with air flow apertures c being provided at each end of the heater, which may have a uniform heating effect, or a greater heating effect at the front than the rear; a nose d detachably secured to the front of the body part, contains a tubular contact g, with air flow apertures h, which abuts against the front contact c, while at the rear, a hollow spigot-like mounting i is fitted into a socket a<1> integral with, or attached to, the body part and contains, within an insulating sleeve j, a metal tube l in which is a slidable contact k, with air flow apertures n, pressed by a spring m against the rear contact c. A dowel r engages holes in the socket a<1> and mounting ...

Improvements in or relating to pitot-static probes and installations including such probes

... 1,122,302. Air speed indicators. SMITHS INDUSTRIES Ltd. May 20, 1966 [June 4, 1965], No.23854/65. Heading G1R. In a pitot-static probe the pitot outlet pipe 22 and static-air outlet pipe 24 extend one within the other from the main body of the probe and terminate within seals 45, 42 in a housing 30 having static-air pressure outlets 37, 38 and pitot air pressure outlets 35, 36.

Improvements in electrical resistance devices for use in measuring the velocity of flow of fluids

... 395,123. Wire resistances. POOLE, R., 193, Oswald Road, Chorlton-cum- Hardy, Manchester, and ASSOCIATED ELECTRICAL INDUSTRIES, Ltd., Crown House, Aldwych, London. April 27. 1932, No. 12121. [Class 37.] A resistance for measuring the velocity of flow of a fluid by its cooling effect on a heated resistance comprises a grid of wire 4 associated with a series of stream-lined parallel barriers 1 arranged within a framework 2 so as to cause the fluid flo.wing past the wire to flow in a given direction. This arrangement ensures that any returning fluid doubling back upon its path has relatively little cooling effect on the wires. The apparatus shown is arranged for measuring the velocity of a current of air flowing vertically upwards. The bars 1 and the framework 2 are of moulded insulating material such as that known under the Registered Trade Mark " Bakelite " and are stream-lined in the vertical direction. Along the lower edges of the bars 1 is attached the resistance wire 4, which may be of ...

An instrumentation rake

Static vent units

Device for measuring the speed and for determining the direction of air flows (currents, streams)

A device for measuring the speed and for determining the direction of air flows has a housing 2 in which four dynamic (total, stagnation, Pitot)-pressure openings 5 are arranged in a plane and offset by 90 degree relative to one another. Every two mutually opposite dynamic-pressure openings 5 are connected via lines 4 to a pressure transducer in which the differential pressure is converted into an electric signal which is used, together with the signal corresponding to the differential pressure of the two other dynamic-pressure openings 5, to determine the speed and direction of the wind. Provided at each dynamic-pressure opening 5 is a streamlined body 10 which comprises a tube (pipe) piece 12 and a disc 11 situated at the free end thereof. The diameter of the disc 11 corresponds essentially to its spacing from the outer surface of the housing 2 of the device. The diameter of the tube piece 12 is smaller than that of the discs 11. Because of the arrangement of the streamlined body 10, ...

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.

AIR PRESSURE SENSOR

Pitot tube instrument

An apparatus for obtaining pressure measurements in an airstream includes a Pitot tube. The Pitot tube includes at least one total pressure port configured to be positioned in the airstream facing upstream, at least one static pressure port configured to be positioned in the airstream facing downstream, at least one first directional port, and at least one second directional port. The at least one first directional port and the at least one second directional port are positioned on opposite sides of the at least one total pressure port and face obliquely with respect to the direction that the at least one total pressure port faces.

DEVICE FOR MEASURING TOTAL PRESSURE OF A FLOW

Method and apparatus to determine the wind speed and direction experienced by a wind turbine

Method and apparatus to determine the wind speed and direction experienced by a wind turbine

METHOD AND APPARATUS FOR CORRECTING BAROMETRIC PRESSURE FOR WIND VELOCITY AND DIRECTION

STRUT MOUNTED MULTIPLE STATIC TUBE

STRUT MOUNTED MULTIPLE STATIC TUBE A strut mounted multiple static tube providing, as shown, multiple separate static pressure measuring systems and using one probe with separate sets of pressure sensing ports for each system. The probe is designed to have a surface configuration which provides substantially identical static pressure conditions at each set of sensing ports while the axial length of the barrel portion of the sensing probe is maintained at a minimum and the pressure effects from the adjacent structures such as the strut are compensated for. The structure includes a barrel portion of the probe having a surface annular wave pattern with sections of different diameters which causes large, uniform changes in the pressure pattern along the probe to provide areas of both positive and negative pressure levels for aerodynamic compensation. The positions for the ports for the separate systems are selected from a pressure profile of the probe so the ports are located at desired pressure ...

QUAD-DISK STATIC PRESSURE PROBE

A quad disk static pressure probe apparatus (10) including: a hollow stem member (15) having a plurality of static pressure ports (16) disposed on its periphery an apertured collar unit (14) surrounding the stem member (15) and being in open fluid communication with the static pressure ports (16); and, inner (21) and outer (18) pairs of disk members operatively secured to the stem member (15) above and below the location of the static pressure ports (16).

INDUCTIVE HEATING OF AIR DATA PROBES

INTEGRATION OF LOW ICE ADHESION SURFACE COATINGS WITH AIR DATA PROBES

An air data probe includes a body, a mount adjacent to the body, a primary low ice adhesion surface coating on a primary impact region of the air data probe, the primary impact region being positioned for direct impact with water drops, and a secondary low ice adhesion surface coating on a secondary impact region of the air data probe, the secondary impact region being positioned for indirect contact by water drops. The primary low ice adhesion surface coating has a different composition than the secondary low ice adhesion surface coating.

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.

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.

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.

HYBRID MATERIAL PITOT TUBE

A pilot tube includes a substantially cylindrical body portion having an interior defining a flow passage and a tip portion extending along a pilot tube axis from the body portion. The tip portion includes a disk, a tip cover and a high terminal conductive insert disposed between the disk and the tip cover and in thermal contact with both.

Continuously Curved Strut Mounted Sensor

AERODYNAMIC PROBE INTERNAL CONSTRUCTIONS

PCT/US90/06567 A short, strut-mounted, multifunction air data sensing probe (20) providing reduced drag, weight and radial cross section has a modular internal construction providing a multiple passageway pressure assembly (35) to transfer sensed pressure signals from individual sensing ports (25,31,32) on a probe barrel (21) to pressure carrying conduits (57,62,66,73,74) extending into the mounting strut (30) of the probe (20). The modular construction eliminates the need for having interior chambers made by fixing a series of difficult to locate bulkheads on the probe interior, with separate lines running from each of the chambers to provide the pressure signal from each of the ports. The modular construction also permits mounting a deicing heater (95) on internal parts other than the outer probe shell so that the manufacture of the probe (20) is further simplified, and the types of material used for the probe shell (21) can be changed without concern about heater mounting.

Self-sealing plug Pitot tube with positioning device

Rotating mechanism for two-way dynamic pressure measuring sensor

Simple and easy speed sensor of pressure method stirring rivers

The utility model relates to a simple and easy speed sensor of pressure method stirring rivers, hold in the palm velocity measurement tube, computer system and photo resistance system including mount,skin, the mount sets up and is used for fixing in stirring rivers drum top the skin holds in the palm velocity measurement tube, the skin is provided with the photo resistance system on holding in the palm velocity measurement tube, and the photo resistance system is connected with computer system again, wherein, the skin asks velocity measurement tube to manage the part including the U type thatthe variable cross section part test tube of the lower part level setting that connects gradually, uniform section test tube that the middle part is the type of falling L setting and upper right portion reduce the cross -section, but the variable cross section of lower part level setting part test tube is intake to turn round and is constituteed by toper device and the free rotation connected with it ...

Static probes of Pitot for planes of which speed varies between subsonic and supersonic speeds

SURFACE TREATMENT TO THE CHROMIUM OF SUPPORTS CONTAINING NICKEL

DEVICE AND PROCESS OF DETERMINATION OF THE TOTAL AIR TEMPERATURE FOR AIRCRAFT

Tube of Pitot with water channels

Improvements with the static tubes of Pitot automatically protected

Improvements with the tubes of Pitot for aeronautical apparatuses

MULTIFUNCTION PROBE FOR AIRCRAFT

ADDITIVE FABRICATION PROCESS FOR AERONAUTICAL EQUIPMENT

L'invention concerne un procédé de fabrication par addition d'au moins une partie d'un équipement aéronautique tel que notamment une sonde de Pitot, destiné à équiper un aéronef, l'équipement (25) comprenant au moins une partie destinée à être disposée au niveau d'une peau (27) de l'aéronef et des moyens de réchauffage de cette partie, les moyens de réchauffage comportant une boucle thermodynamique comprenant un circuit fermé au moins en partie intégré, dans lequel circule un fluide caloporteur, le circuit fermé comprenant un évaporateur et une zone dans laquelle peut s'opérer une condensation du fluide caloporteur dans l'appendice pour le réchauffer, hors de l'évaporateur, le circuit dans lequel circule le fluide est formé par un canal tubulaire à section vide au moins en partie venu de matière avec l'équipement, au moins la partie de l'équipement disposée à l'extérieur de l'aéronef est réalisée par fabrication additive et comporte une embase (120) de fixation sur la peau de l'aéronef ...

STRUT MOUNTED DUAL STATIC TUBE

DEVICE MANOSENSIBLE OF STATIC PRESSURE TAP AND ANEMOMETRIC CHECHMATE, IN PARTICULAR FOR AIRCRAFT

HEATING A FIRST AIRCRAFT AERONAUTICAL EQUIPMENT

L'invention concerne un aéronef muni d'au moins deux équipements aéronautiques, un premier équipement (25) comprenant une partie destinée à être disposée au niveau d'une peau (27) de l'aéronef et des moyens de réchauffage de la partie, caractérisé en ce que les moyens de réchauffage comprennent une boucle thermodynamique comprenant un circuit fermé dans lequel circule un fluide caloporteur, le circuit fermé comprenant un évaporateur (14) associé à des moyens fonctionnels (80) du deuxième équipement (81) de l'aéronef formant source chaude dégageant de la chaleur lors de leur fonctionnement et une zone dans laquelle peut s'opérer une condensation du fluide caloporteur dans l'appendice pour le réchauffer, et en ce que hors de l'évaporateur (14), le circuit dans lequel circule le fluide est formé par un canal tubulaire à section vide.

Pressure probe for aircraft, comprises vane which is free to rotate about a vertical axis, has a variable rake on the leading edge and includes facilities to measure total and static pressures

L'invention se rapporte à une sonde multifonction pour aéronef. La sonde comporte une palette mobile (1) destinée à s'orienter dans l'axe (8) d'un écoulement d'air entourant la sonde. La palette mobile (1) comprend des premiers moyens (20, 21) de prise de pression pour mesurer la pression totale (Pt) de l'écoulement et des seconds moyens (22, 23) de prise de pression pour mesurer la pression statique (Ps) de l'écoulement. La palette mobile (1) comporte en outre un profil dont la flèche (λ1, λ2) est variable.

A COOLED PRANDTL PROBE ASSEMBLY

... The present invention provides a cooled Prandtl probe assembly is presented. The cooled Prandtl probe assembly comprises a Prandtl probe, which comprises (i) at least one total pressure tube with a total pressure intake hole on its end, wherein the at least one total pressure tube is adopted to provide a total pressure of the fluid flow to be measured, (ii) at least one static pressure tube with a static pressure intake hole on its end, wherein the at least one static pressure tube is adopted to provide a static pressure of the fluid flow to be measured, and (iii) a measuring tool connected to the at least one total pressure tube and the at least one static pressure tube. The measuring tool measures at least total and static pressure of the fluid flow provided by the at least one total pressure tube and the at least one static pressure tube respectively. The total pressure intake hole of the at least one total pressure tube and the static pressure intake hole of the at least one static ...

METHOD AND APPARATUS TO DETERMINE THE WIND SPEED AND DIRECTION EXPERIENCED BY A WIND TURBINE

An apparatus and a method used to determine the speed and direction of the wind experienced by a wind turbine are provided. Said apparatus comprises at least one sensor fixed to the rotor of said wind turbine, an angular sensor to measure the angular position of the rotor of said wind turbine, and a circuit which converts the relationship between the output of said at least one sensor and the output of the angular sensor into the speed and direction of the wind experienced by the wind turbine. According to the invention, the sensing apparatus can measure the wind speed and direction in three dimensions. In addition, mounting the sensors directly to the rotor of the wind turbine results in a very simple and robust installation. Mounting the sensors directly to the rotor also eliminates the turbulence from the rotor and the nacelle of the wind turbine from affecting the sensors.

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 ...

Pitot tube

Methods and systems for determining air data parameters

An air data system (100) is described that includes a cone-shaped probe (10), a plurality of pressure transducers (110,112,114), and a processing device. The cone-shaped probe includes a first pressure port (12) formed in a substantial tip (14) of the probe and extending therethrough, and a plurality of pressure ports (16,18,20,22) formed in a substantially evenly spaced circular pattern about a sloped surface (30) of the probe and extending through the probe. The plurality of pressure transducers are each configured to receive at least one pressure transferred through at least one of the pressure ports and output one or more signals related to the pressures sensed. The processing device (102) is configured to receive signals originating from the transducers, The processing device is further configured to calculate a static pressure, an angle of attack, and an angle of sideslip based on the received signals.

Wind turbine measurement system

Averaging pitot probe

To measure speed of gas flow in direction F along pipe 8 a flowmeter 2 is used comprising a gas flow sensor 4 connected by tubing 50,52 with an averaging pitot probe 6 formed by two tubes 10 and 12 of circular cross-section disposed side by side and closed at their one and the same ends 14 and 16 and mounted in a gas tight manner in a sleeve 18 which fits in aperture 20 in the wall of pipe 8 and is secured in a gas tight manner to the pipe (8). The two tubes 10 and 12 are identical in shape and dimensions and each has four circular holes 22 through its tube wall. All the holes 22 are of the same shape and size, and each has a diameter in the range 0.4mm to 1.00mm. The internal diameter of each tube 10,12 is at least 1.59mm, and the ratio of the cross-sectional area of each tube (10, 12) to the cross-sectional area of each hole 22 is at least 9:1. The positions of the holes 22 in one tube (10, 12) are identical to the positions of the holes in the other tube (10, 12) except that the holes ...

STANDOFF MOUNTING FOR AIR DATA SENSING PROBES ON A HELICOPTER

A standoff arm and probe assembly (20) for a helicopter (10) has a standoff mounting arm (22, 70) that extends outwardly from the helicopter body (18, 72) in a selected direction, preferably forwardly. The standoff arm (22, 70) has an outer end (24) that mounts a low lateral speed sensing probe (26, 88) that is positioned with an axis substantially parallel to the axis of a helicopter rotor (12), and within the downwash region of air movement caused by the rotor (12). The low lateral speed sensing probe (26, 88) has ports (30, 90) that are arranged annularly around the probe (26, 88), and the pressures sensed at selected annular or peripheral locations on the probe (26, 88) are measured to determine low air speeds. Additionally, the standoff arm (22, 70) can mount a plurality of other sensors (44, 50, 52, 56, 58, 60, 76, 78, 82, 94, 96, 98) such as a pilot pressure probe (44, 82) extending forwardly from the arm, a lateral pressure sensing probe (50, 52, 76, 78) along a lateral side of ...

QUAD-DISK STATIC PRESSURE PROBE

A quad disk static pressure probe apparatus (10) including: a hollow stem member (15) having a plurality of static pressure ports (16) disposed on its periphery; an apertured collar unit (14) surrounding the stem member (15) and being in open fluid communication with the static pressure ports (16); and, inner (21) and outer (18) pairs of disk members operatively secured to the stem member (15) above and below the location of the static pressure ports (16).

ПРИЕМНИК ВОЗДУШНОГО ДАВЛЕНИЯ

Изобретение относится к определению параметров полета летательных аппаратов или параметров потока в аэродинамических трубах. Приемник воздушного давления, выполнен в виде двух расположенных соосно тел в виде призм, сечения которых имеют форму равностороннего треугольника с вершинами, смещенными на угол 60o, а на боковых гранях призм выполнены приемные отверстия, соединенные пневмотрассами со штуцерами. Отличительной особенностью данного приемника воздушного давления является то, что в нем боковые грани призм выполнены выпуклыми с радиусом кривизны R, определяемым из соотношения R/r > 1, где r - радиус окружности, проведенной через вершины углов треугольников, расположенных в сечениях призм. Такая форма приемника воздушного давления позволяет с одной стороны минимизировать влияние числа Рейнольдса на измерение давлений, а с другой стороны увеличить чувствительность прибора за счет возрастания производной измеряемых давлений по углу скоса, что приводит к существенному уменьшению инструментальных ...

АЭРОДИНАМИЧЕСКИЙ ДАТЧИК

Использование: определение параметров воздушного потока текучей среды. Сущность изобретения: короткий, устанавливаемый с помощью сжатого элемента многофункциональный аэродинамический датчик имеет модульную конструкцию, образующую многоканальный напорный блок для передачи зафиксированных сигналов давления от индивидуальных фиксирующих отверстий на цилиндрической оболочке датчика в напорные трубопроводы, доходящие до монтажного сжатого элемента датчика. 2 с.п. ф-лы, 15 з.п. ф-лы, 13 ил.

Устройство для измерения расхода газов и жидкостей

Анемометр

Приемник воздушного давления потока дозвуковой скорости

SONDE UND VERFAHREN ZUM MESSEN DER RELATIVGESCHWINDIGKEIT EINES ANSTROEMENDEN MEDIUMS

INTERNE STRUKTUREN AERODYNAMISCHER FÜHLER.

Moving-vane angle of attack probe

A moving-vane AOA probe comprises a vane defined by a leading edge and a trailing edge, an opening 4 located on the leading edge, at least one exhaust opening 6 which may be located on the trailing edge, and a chamber 5 extending through the vane from opening 4 to exhaust 6. Both openings 4 and 6 may be slots extending along their respective edges. The chamber houses a pitot tube 8 for measuring the pressure of the fluid passing through chamber 5. Drain holes 12 and/or foil/ceramic heaters may be used to remove water/ice. An electronics assembly i.e. air-data computer 16 may be located in housing 2a, to take angle of attack and/or pressure readings. Housing 2a may also hold a counterweight system 9 configured to balance the mass distribution of the vane relative to the axis of rotation. A moving-vane AOA probe comprising at least one static pressure system is also provided. Each system comprises a pressure port in the region of a depression (i.e. a groove) on a surface of the vane, and ...

Avionic equipment heating

Differential pressure anemometer

STATIC PRESSURE SENSING APPARATUS

... 1413990 Pressure sensing apparatus DEFENCE SECRETARY OF STATE FOR 12 April 1973 [19 April 1972] 18031/72 Heading G1R In a probe for sensing static pressure in an air stream, having a tubular member provided with an air passage 1 and at least one tapping 7 connecting the air passage 1 with the exterior of the probe downstream of the leading probe edge, a plurality of regularly spaced serration 8 are provided around the outer surface of the probe and extend rearwardly along the probe. The external surface of the probe may have various conical configurations.

Improvements relating to ships' logs

... 893,381. Ships' logs. WALKER & SON Ltd., THOMAS. Jan. 30, 1961 [Feb. 11, 1960], No. 4878/60. Class 69 (1). A pitot tube assembly, including a distance tube 3, extends between the bottom 1 and the inner bottom 2 of a ship, and rigidly secured in position at its lower end 4 and resiliently secured at its upper end by flexible metal bellows. The lower end 4 is fixed at 6 to a sea-valve 7 whose lower flange 11 is bolted at 12 to a pad 13 on the bottom 1. The bellows 15 pass through an oversize hole 24 and are bolted at 21 to a ring on the inner bottom 2. The pitot tube proper is not shown, but it is screwed at 31 to an inner tube 30 which can slide through a hole 32 in the ship's bottom by moving up and down in the tube 30. Sealing rings are fitted to the distance tube 3 at 35, to a collar 41 on the tube 30 at 41, and to a plate 52 through which the tube 30 passes at 37. Pressure fluid can be actuated or exhausted through conduits 43 and 44 to raise and lower the tube 30 inside the tube 3.

Automatically protected pitot static tubes

... 502,060. Heating Pitot-tube apparatus electrically. KOLLSMAN, P. April 11, 1938, Nos. 11016 and 11017. Convention dates, April 9, 1937 and March 12, 1938. [Class 69 (i)] [Also in Groups XI, XXXV, and XXXVII] An electric heater B, Fig. 1, arranged to heat conductively the metallic dynamic and static pressure conduits 2, 5 of the Pitot head of'an aircraft speed-indicator in order to keep them free from ice &c. is protected from overheating by automatic means controlling the current supply to it in dependence upon the rate at which the heat is dissipated. In the form shown in Fig. 1, the Pitot tube consists of a dynamic pressure tube 2 extending within an outer shell A forming the static pressure conduit 5 and provided with static pressure openings 4. A tube 7 extends from the conduit 2 to drain any moisture which' may enter.the latter. The heater B consists of enamel-embedded wire enclosed in a copper shell which is preferably welded or soldered to the shell A. The current supply to the heater ...

WIND VECTOR REGULATION EQUIPMENT

Vorrichtung und Verfahren zur Messung eines Druckes

The invention relates to a device (1) and to a method for measuring a pressure. The device, in particular a Pitot tube, comprises a tube (2) having a first opening (3), and a first pressure measuring unit (4) for determining a pressure acting on the first opening (3). In order to avoid a blocking of the tube (2), and to allow an interruption-free measurement at the same time, according to the invention a delivery unit, in particular a pump, is provided in order to generate a pressure in a medium located in the tube (2), said pressure decreasing toward the first opening (3). The device (1) is designed such that whenever the tube (2) is filled with a medium, upon which a pressure that decreases toward the first opening (3) acts, a pressure acting upon the first opening (3) can be indirectly measured via the medium using the first measuring unit (4).

Vorrichtung und Verfahren zur Messung eines Druckes

The invention relates to a device (1) and to a method for measuring a pressure. The device, in particular a Pitot tube, comprises a tube (2) having a first opening (3), and a first pressure measuring unit (4) for determining a pressure acting on the first opening (3). In order to avoid a blocking of the tube (2), and to allow an interruption-free measurement at the same time, according to the invention a delivery unit, in particular a pump, is provided in order to generate a pressure in a medium located in the tube (2), said pressure decreasing toward the first opening (3). The device (1) is designed such that whenever the tube (2) is filled with a medium, upon which a pressure that decreases toward the first opening (3) acts, a pressure acting upon the first opening (3) can be indirectly measured via the medium using the first measuring unit (4).

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.

PROCEDURE AND DEVICE FOR USING AND SEALING A FLOW METER OF THE TYPE OF PITOT TUBE IN A PIPE.

STATIC STATIC SOUNDING ROD WITH FOUR PLATES.

APPARATUS FOR PROTECTION OF A PROBE INTEGRAL TO AN EXTERIOR WALL OF AN AIRPLANE

L'invention concerne un dispositif (300) de protection d'une sonde (200) solidaire d'une paroi (102) d'un avion. Des moyens (306) amovibles de fixation à la paroi du dispositif de protection sont sensibles à une modification d'une température de la sonde. Par exemple, les moyens de fixation sont en matériau à mémoire de forme. Une élévation de la température permet une déformation des moyens de fixation et une désolidarisation du dispositif de la paroi. Il est également possible de réaliser les moyens de fixation en matériau magnétostrictif ou polarisable, afin de désolidariser le dispositif de protection lorsque les moyens de fixations sons soumis à un champs magnétique. Ainsi, les moyens de fixation peuvent comporter une goupille (307) polarisable se retirant d'un logement (308; ménagé sur un élément traversant (301) lorsqu'elle est soumise au champs magnétique généré par un électroaimant (400).

FAMILY OF AERODYNAMICALLY COMPENSATED MULTIPLE STATIC PRESSURE TUBES

OPTO-MECHANICAL TRANSDUCER FOR THE DETECTION OF VIBRATIONS

La présente invention porte sur un transducteur opto-mécanique comprenant une fibre optique présentant une extrémité distale pointue polie placée en face d'une surface réfléchissante et une extrémité proximale étant raccordée à un coupleur combinant une fibre optique d'éclairage associée à une source lumineuse et une fibre optique de mesure associée à un photo-détecteur. L'élément réfléchissant présente une zone mobile avec une composante axiale, la distance axiale entre l'extrémité distale de la fibre optique et ladite surface réfléchissante au repos est déterminée pour que l'intensité lumineuse réfléchie I0 soit égale à P.Imax où Imax désigne l'intensité lumineuse réfléchie maximale, et P est un paramètre compris entre 0,25 et 0,75.

AIR-PRESSURE SENSOR

The present invention relates to an air-pressure sensor which can be used for determining the parameters of an air flow, of a flow of other gases or of liquids as well as the flight parameters of aircraft. This air-pressure sensor comprises a rod including a plurality of ridges which are each oriented along the longitudinal axis of said rod. Groups of openings are provided between the ridges on the smooth side surfaces of the rod and are connected by pneumatic paths to outlet fittings located outside the flow. The longitudinal ridges are continuous and their number is n > 3. The groups of openings are spaced from the ridges by a distance a 0.1 b where b is the distance between the ridges at any cross-section of the rod. The angle between the side surfaces of the rod at any cross-section thereof is .gamma. < 180~. The sharp ridges can be rounded or blunted by a land, or can even be made in the form of protrusions. The side surfaces of the rod may have a convex, cylindrical or conical shape ...

PROBE FOR MEASURING THE TOTAL PRESSURE OF A FLOW AND METHOD FOR IMPLEMENTING THE PROBE

The invention relates to a probe (10) for measuring the total pressure of a flow and a method for implementing the probe (10). The probe (10) is intended to be fitted in an aircraft. The probe (10) comprises a Pitot tube (14) and means (22) for reheating the probe assembly (10). According to the invention, the probe (10) also comprises means (38) for measuring a local temperature of regions (23, 37) of the Pitot tube (14) likely to accumulate particles conveyed by the flow independently of the means (38) for determining the average temperature of the probe (10). According to the method, if the temperature delivered by the means (38) for measuring a local temperature of regions (23, 37) of the Pitot tube (14) likely to accumulate particles conveyed by the flow is less than the first reference temperature (T0), then an additional reheating of regions (23, 37) of the Pitot tube (14) likely to accumulate particles conveyed by the flow is triggered.

AIR DATA PROBES

An air data probe includes a probe head defining a longitudinal axis between a forward tip and aft base. The probe includes a thermocouple having a sense end in the forward tip to measure the temperature in the forward tip. The probe includes a port opening defined in a side of the probe head and opening at an angle with respect to the longitudinal axis. The probe includes a bulkhead within the probe head. The bulkhead 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.

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

The invention relates to a probe for measuring the total pressure of an airflow, the probe (10) being intended to equip an aircraft and a method of using the probe. The probe (10) comprises a Pitot tube (14), two separate heating wires (31, 32) supplied separately and allowing each one to heat an external part (14, 15) of the probe (10), and means (35) of distribution of a given maximum power to each of the two heating wires (31, 32) as a function of the current temperature of each of the two parts (14, 15). The method consists in giving priority to the reaching of a predefined minimum temperature of a first (14) of the two parts of the probe (10) by allocating to the first part (14) of the probe (10) a predefined share of the given maximum power for as long as the temperature of the first part (14) is below a predefined minimum temperature.

FUSELAGE PITOT-STATIC TUBE

The invention relates to a fuselage Pitot-static tube comprising three groups of orifices for determining the total pressure (2), static pressure (3) and angle of attack (6, 7), and an axisymmetric body (1) and strut (5) for mounting an anti-icing system having, arranged between them, airways (10) and electric heating elements (8). The orifices for determining the angle of attack are arranged on the strut, whose cross section is constructed in the form of a subsonic aerodynamic profile with a rounded-off nose or a tapered nose, and are arranged between the nose of the profile and the position of its maximum thickness.

FUSELAGE PITOT-STATIC TUBE

The invention relates to a fuselage Pitot-static tube comprising three groups of orifices for determining the total pressure (2), static pressure (3) and angle of attack (6, 7), and an axisymmetric body (1) and strut (5) for mounting an anti-icing system having, arranged between them, airways (10) and electric heating elements (8). The orifices for determining the angle of attack are arranged on the strut, whose cross section is constructed in the form of a subsonic aerodynamic profile with a rounded-off nose or a tapered nose, and are arranged between the nose of the profile and the position of its maximum thickness.

Приемник воздушного давления

... 1. Технический результат Упрощение конструкции, уменьшение массы. 2. Суть Устройство содержит три группы отверстий 2, 5, 6, 10 для определения полного давления, статистического давления и угла атаки, осесимметрическое тело 1 и стойку для крепления 4, с расположенными в них пневмотрассами и электронагревательными элементами, отверстия 10, измеряющие статистическое давление, расположены на плите 8 перед стойкой. 3. Область применения Авиационная техника. Пункт: 1 незав. 10 зав. Фиг.: 28 ...

Fuselage Pitot-Static Tube and the Aerodynamic Profile of Its Strut

Pitot-Static Tube

APPARATUS AND METHOD FOR ANTI-ICING OF SPEED MEASUREMENT PROBES

Improved smoke section average flow velocity monitoring device

DISPOSITIF MANOSENSIBLE DE PRISE DE PRESSION STATIQUE ET MAT ANEMOMETRIQUE, NOTAMMENT POUR AERONEF

L'INVENTION CONCERNE LA MESURE DE LA VITESSE DES AERONEFS. ELLE SE RAPPORTE A UN MAT ANEMOMETRIQUE AYANT UN CORPS 10 DONT L'EXTREMITE 14 FORME UN DISPOSITIF DE PRISE DE PRESSION STATIQUE. SELON L'INVENTION, CE DISPOSITIF COMPORTE AU MOINS UN ORIFICE 22 FORME DANS UNE SURFACE DE REVOLUTION AUTOUR D'UN AXE A, AU MOINS DANS UN SECTEUR CIRCULAIRE 28 DONT L'ETENDUE CORRESPOND AU MOINS A LA PLAGE DE VARIATIONS ANGULAIRES DU VECTEUR VITESSE. APPLICATION A LA MESURE DE LA VITESSE DES AERONEFS.

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 ...

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.

BALLAST WATER TREATMENT MONITORING SYSTEM

A method and system for taking a sample of ballast water. The method includes withdrawing a sample of ballast water via a tube inserted in a ballast water pipe, wherein the tube includes a sample inlet, and isokinetic flow is achieved via a pump that controls the flow of the sample ballast water through the tube inlet by comparing a flow of the ballast water pipe with a flow of the sample ballast water through the tube; and controlling the flow of water through the sample tube inlet when a flow of the ballast water pipe is sensed to be different; withdrawing a portion of the sample ballast water for testing; and returning remaining sample ballast water to the ballast water pipe. 1. A method for taking a sample of ballast water , comprising:withdrawing a sample of ballast water via a tube inserted in a ballast water pipe, wherein the tube includes a sample inlet, and isokinetic sampling is achieved via a pump that controls the flow rate of the sample ballast water through the tube inlet by comparing a fluid velocity of the ballast water pipe with a fluid velocity of the sample ballast water through the tube;controlling the flow of water through the sample tube inlet when a flow velocity of the ballast water pipe is sensed to be different than a velocity of the ballast water in the pipe;withdrawing a portion of the sample ballast water for testing; andreturning remaining sample ballast water to the ballast water pipe.2. The method of claim 1 , wherein the sample ballast water is withdrawn and returned via a pitot tube assembly comprising a housing and a wand inside the housing claim 1 , wherein sample ballast water is withdrawn through the wand claim 1 , and sample ballast water is returned via the housing.3. The method of claim 2 , further comprising extending the wand from within the housing to reach a sampling location inside the ballast water pipe.4. The method of claim 2 , wherein the wand seals against the housing claim 2 , and sample ballast water is withdrawn ...

DEVICE FOR MAINTAINING AND ANALYZING AN AERODYNAMIC PROBE

A device for maintaining and analyzing an aerodynamic probe of stagnation pressure type intended to be installed in an aircraft comprises a channel with a first end that is intended to penetrate into the probe, and means for creating in the channel an air depression relative to the ambient pressure and means for recovering any particles sucked into the channel. 1. A device for maintaining and analyzing an aerodynamic probe of stagnation pressure type for installation in an aircraft , the device comprising: a channel with a first end that is intended to penetrate into the probe , means for creating in the channel an air depression relative to the ambient pressure and means for recovering any particles sucked into the channel.2. The device as claimed in claim 1 , wherein the means for creating a depression comprise an ejector intended to be coupled to a pressurized gas source and ejecting the gas in proximity to a second end of the channel in order to drive the air present in the channel.3. The device as claimed in claim 1 , wherein the recovery means comprise a closed vessel positioned in the line of the channel.4. The device as claimed in claim 3 , wherein the vessel comprises at least one transparent wall.5. The device as claimed in claim 3 , wherein the vessel comprises a removable wall.6. The device as claimed in claim 1 , further comprising means for measuring and displaying the depression prevailing in the channel.7. The device as claimed in claim 1 , wherein the channel claim 1 , at its first end claim 1 , is formed from a flexible material.8. The device as claimed in claim 2 , the recovery means comprising a closed vessel positioned in the line of the channel.9. The device as claimed in claim 4 , the vessel comprising a removable wall.10. The device as claimed in claim 2 , comprising means for measuring and displaying the depression prevailing in the channel.11. The device as claimed in claim 2 , the channel claim 2 , at its first end claim 2 , being formed ...

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 ...

SIDESLIP GUIDANCE FOR ONE ENGINE INOPERATIVE CONDITION

The present disclosure describes systems and methods associated with providing sideslip guidance for an aircraft. A sideslip offset based on aileron position is used to adjust an initial target sideslip, which is further modified using the actual sideslip of the aircraft. 1. A method for providing sideslip guidance for an aircraft , the method comprising:determining an initial target sideslip based on current operating conditions of the aircraft;determining a sideslip offset based on an actual position of at least one aileron of the aircraft and a neutral position of the at least one aileron;adjusting the initial target sideslip using the sideslip offset to generate an adjusted target sideslip;obtaining an actual sideslip of the aircraft; andproviding a target sideslip as a difference between the adjusted target sideslip and the actual sideslip.2. The method of claim 1 , wherein determining the initial target sideslip comprises using at least one of an airspeed of the aircraft and a flap configuration of the aircraft as the current operating conditions.3. The method of claim 1 , wherein determining the initial target sideslip comprises using an engine operating status for each engine of the aircraft as the current operating conditions.4. The method of claim 1 , further comprising determining the actual position of the at least one aileron as an average of an actual position of a first aileron and an actual position of a second aileron.5. The method of claim 1 , wherein obtaining the actual sideslip of the aircraft comprises estimating the actual sideslip of the aircraft.6. The method of claim 5 , wherein estimating the actual sideslip comprises:determining an initial sideslip estimate using aircraft operating parameters; andadjusting the initial sideslip estimate by a gain factor.7. The method of claim 1 , further comprising:detecting an engine failure of at least one engine of the aircraft; andwhen the engine failure is detected, determining an operating mode of ...

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 ...

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 ...

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 ...

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 ...

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 ...

PITOT-STATIC ANEMOMETRIC TEST ADAPTER

An adapter for isolating the at least one pressure port of a pitot-static tube from ambient conditions. The adapter can be used to perform aircraft anemometric testing and provides a replaceable, leak-proof seal for communicating pressures from the aircraft pitot-static system to testing equipment. 1. A pitot-static test adapter comprising:a mating body with a plurality of grooves and a seal configured and adapted for isolating at least one port of a pitot-static pressure sensing device from ambient pressure conditions;said seal comprising an elongated body having a plurality of protrusions configured and adapted for engaging and retaining the plurality of grooves.2. The pitot-static test adapter of claim 1 , wherein the protrusion extends the length of the seal.3. The pitot-static test adapter of claim 1 , wherein the seal defines a communicating hole for communicating pressure from the pitot-static pressure sensing device to the pitot-static test adapter.4. The pitot-static test adapter of claim 3 , wherein the seal further defines a hemispherical protrusion surrounding the communicating hole to further enhance isolation from ambient pressure conditions.5. A pitot-static test adapter comprising:a mating body and a seal configured and adapted for isolating at least one port of a pitot-static pressure sensing device from ambient pressure conditions; andone groove adapted to cooperate with one protrusion, one of the groove and the protrusion formed by a surface of the mating body, the other of the groove and the protrusion defined by a surface of the seal, wherein the mating body and the seal are connected to one another without the need for adhesive when the groove is mated with the protrusion.6. The pitot-static test adapter of claim 5 , wherein the one of the groove and the protrusion defined by a surface of the seal extends the length of the seal.7. The pitot-static test adapter of claim 5 , wherein the seal defines a communicating hole for communicating pressure ...

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 ...

SINGLE BEAM/DETECTOR OPTICAL REMOTE CROSS- FLOW SENSOR

System and method for remotely sensing the cross-flow orientation of a fluid (including a gaseous fluid) over an extended range. A Fourier transform of beam wander of a single beam can be used to determine the orientation of the flow field. Many applications depend upon accurate flow orientation data to provide correct information such as, for example, citing of turbines on wind farms and atmospheric/ocean weather prediction. 1. A method for determining flow orientation in a turbulent fluid comprising:projecting a light source through the turbulent fluid onto a position sensitive detector (PSD);monitoring, by a first special purpose computer, beam wander on the PSD over a pre-selected time period;calculating, by a second special purpose computer, Fourier transforms of the beam wander along different directions of the PSD, the Fourier transforms being related to Fourier amplitudes and Fourier frequencies; anddetermining, by a third special purpose computer, the flow orientation as a selected of the different directions at which the Fourier amplitudes reach a maximum at the highest of the Fourier frequencies.2. The method as in wherein the turbulent fluid is an ocean.3. The method as in wherein the turbulent fluid is a planetary atmosphere.4. The method as in wherein the light source is continuous.5. The method as in wherein the light source is pulsing.6. The method as in wherein the light source is a laser.7. The method as in wherein the light source is a point source.8. The method as in wherein the light source is a plain wave.9. A computer method for surveying wind for a wind farm plan comprising: projecting a light source through the wind onto a position sensitive detector (PSD);', 'monitoring beam wander on the PSD over a pre-selected time period;', 'calculating Fourier transforms of the beam wander along different directions of the PSD, the Fourier transforms being related to Fourier amplitudes and Fourier frequencies; and', 'determining the flow orientation as ...

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: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; anddisposing at least one electrical coil including one or more coil wraps along the flow passage of the pitot tube.2. The method of claim 1 , wherein the radially tapered outer surface has a concave curve.3. The method of claim 1 , wherein disposing 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: positioning at least one bulkhead along the flow passage to limit travel of particles ingested into the pitot tube.5. The method of claim 4 , further comprising: arranging at least one of the one or more coil wraps along the flow path between the inlet opening and the at least one bulkhead.6. The method of claim 4 , further comprising: arranging at least one of the one or more coil wraps along the flow path downstream of the at least one bulkhead.7. The method of claim 6 , wherein arranging the at least one of the one or more coil wraps includes positioning a plurality of coils to establish a variable watt density along the flow path.8. The method of claim 4 , further comprising: forming at least one drain opening in the substantially cylindrical body portion fluidically connecting the flow path and the outer surface.9. The method of claim 8 , wherein forming the at ...

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.

PITOT TUBE VELOCIMETER SYSTEM

An apparatus and method for sensing position according to flow velocity includes at least two pitot tubes each defining a central axis is along mutually orthogonal axes. Each of at least two pressure sensors is positioned in fluid communication with a corresponding one of the at least two pitot tubes. A controller receives outputs from the at least two pressure sensors and analyzes to determine at least one of an angular and translational velocity according to the outputs. A distance traveled is then determined according to the at least one of an angular and translational velocity. Corresponding methods of use and calibration are also disclosed. 1. An apparatus for determining position according to flow velocity of a fluid , the apparatus comprising:at least two pitot tubes each defining a central axis, including at least one pitot tube oriented with the central axis thereof parallel to a first direction, at least one pitot tube oriented having the central axis thereof having an extent along a second direction orthogonal to the first direction; andat least two pressure sensors each positioned in fluid communication with one of the at least two pitot tubes2. The method of claim 1 , further comprising: receive outputs from the at least two pressure sensors,', 'determine a velocity according to the outputs thereof, and', 'determine a distance traveled based on the velocity., 'a controller operably coupled to the at least two pressure sensors, the controller being programmed to'}3. The apparatus of claim 1 , wherein the at least two pitot tubes are each positioned within a shaped surface and have corresponding distal ends in fluid communication with space exterior to the shaped surface.4. The apparatus of claim 3 , wherein the shaped surface defines at least one vent.5. The apparatus of claim 4 , wherein the at least two pressure sensors are differential pressure sensors each positioned to measure a difference between a pressure within the shaped surface and a pressure ...

AERODYNAMIC MEASUREMENT PROBE FOR AIRCRAFT

An aerodynamic measurement probe intended to equip an aircraft. The probe comprises a tube intended to face substantially into a flow of air along the aircraft, the tube being open at a first of its ends. The probe further emits an electromagnetic wave directed towards a free zone situated in the extension of the tube on the side of the open end, the electromagnetic wave making it possible to reheat the water likely to be located in the free zone. 1. An aerodynamic measurement probe intended to equip an aircraft , the probe comprising:a tube intended to face substantially into a flow of air along the aircraft, the tube comprising a first and a second ends, the tube being open at the first ends, anda transmitter emitting an electromagnetic wave directed towards a free zone situated in the extension of the tube on the side of the open end, the electromagnetic wave making it possible to reheat water likely to be located in the free zone, the electromagnetic wave being directed towards the free zone by the inside of the tube.2. The probe according to claim 1 , further comprising temperature measurement means.3. The probe according to claim 1 , further comprising pressure measurement means.4. The probe according to claim 1 , wherein the electromagnetic wave is a laser beam.5. The probe according to claim 4 , wherein the emitter comprises a laser diode emitting the laser beam and a focuser focusing the laser beam.6. The probe according to claim 5 , wherein the diode is positioned inside the tube.7. The probe according to wherein claims 4 , the tube is blocked at the second end claims 4 , the focuser comprising a concave mirror positioned in the tube and fixed at the second end.8. The probe according to claim 4 , wherein the tube is partially blocked at the second end claim 4 , the focuser forming a body centred on an axis of the tube claim 4 , several streams of air being able to circulate in the tube angularly about the focuser claim 4 , an internal shape of the tube in ...

Metering Device

According to the invention a device for precise metering of a fluid volumetric flow of low flow rates down to zero volumetric flow of a liquid component in a mixer feed line for mixing plastics is provided, the device having a fluid supply tank that is in fluid line communication with the mixer feed line via a pump and through a volumetric flow meter, is characterized in that a fluid return line, which leads back into the tank through a second volumetric flow meter and which branches off from one of the fluid lines between the tank and the mixer feed line downstream of the first volumetric flow meter through a distributor apparatus that has one input and two outputs, namely one into the return line and one into the mixer feed line, and that distributes an input volumetric flow into the two outputs, and specifically in an adjustable fluid rate ratio. 2321226. The device according to claim 1 , further comprising a signal processing apparatus that calculates a difference signal () from signals of the two volumetric flow meters ( claim 1 , ).318321226. The device according to or claim 1 , further comprising a control apparatus claim 1 , which controls or regulates the flow-rate ratio at the distributor apparatus () claim 1 , depending on a difference signal () from signals of the two volumetric flow meters ( claim 1 , ).418. The device according to or claim 1 , wherein the distributor apparatus () has a distributor ball valve and/or a slide valve and/or a pilot valve.5184042444242. The device according to or claim 1 , wherein the distributor apparatus () has a line branching () claim 1 , which leads to two metering ball valves () each having an adjustable output flow rate claim 1 , and a coupling apparatus () claim 1 , at which the flow rate ratio can be adjusted claim 1 , in that the coupling apparatus reduces the output flow-rate at one of the two metering ball valves () claim 1 , by the same amount by which it increases the output flow rate at the other of the two ...

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 ...

CUSTOMIZABLE AVERAGING PITOT TUBE PROBE AND PROCESS VARIABLE TRANSMITTER

A customizable length averaging pitot tube (APT) probe for insertion into a confined conduit, such as a process pipe, is disclosed. The APT probe includes a probe portion, configured to be inserted into the confined conduit, which includes longitudinally extending upstream, downstream and middle surfaces to form first and second fluid carrying plenums within the APT probe portion. A plurality of longitudinally arranged openings are disposed along the length of the upstream surface with each opening in fluid communication with the first fluid carrying plenum. A plurality of longitudinally arranged openings are disposed along the length of the downstream surface with each opening in fluid communication with the second fluid carrying plenum. A cap is affixed to an end of the APT probe portion to isolate the first and second fluid carrying plenums at the end of the APT probe portion. An elongated body is coupled to the APT probe portion and provides fluid passageways fluidically coupled to the first and second plenums for coupling process pressures from the first and second plenums to a pressure sensor. 1. A method of customizing an averaging pitot tube (APT) probe for insertion into a particular confined conduit , the method comprising:providing an APT probe portion having a plurality of cutting regions which define adjustable lengths of the APT probe portion, the APT probe portion comprising a longitudinally extending upstream surface and a longitudinally extending downstream surface which form first and second fluid carrying plenums within the APT probe portion, the APT probe portion further comprising a plurality of longitudinally arranged openings in the upstream surface disposed along a length of the upstream surface with each opening in fluid communication with the first fluid carrying plenum, and a plurality of longitudinally arranged openings in the downstream surface disposed along a length of the downstream surface with each opening in fluid communication ...

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.

DAMAGE DETECTION FOR ROTARY ANGLE MEASUREMENT SENSORS

An angle of attack sensor includes a rotatable vane extending away and support from a mounting plate, a housing extending way from an opposite side of the mounting plate, and a sensor coupled to the vane. The angle of attack sensor communicates with an electronics module enclosed within the housing or mounted remotely with respect to the angle of attack sensor. The electronics module includes a processor, computer-readable memory, and a communication device. The computer-readable memory is encoded with instructions that, when executed by the processor, cause the electronics module to perform steps of a damage detection method. 1. An angle of attack sensor comprising:a mounting plate;a vane supported from the mounting plate and extending from a first side of the mounting plate, wherein the vane is rotatable about a vane axis;a housing extending from a second side of the mounting plate in a direction opposite to the vane;a sensor coupled to the vane; and at least one processor;', 'a communication device; and', receive, from the sensor, a signal indicative of one or more of a kinematic parameter of the vane and an electrical parameter of the angle of attack sensor;', 'compare the signal to a first damage criterion; and', 'output, using the communication device, a first fault signal to a consuming system of an aircraft that is indicative of a damage event based on a comparison of the signal to the first damage criterion., 'computer-readable memory, encoded with instructions that, when executed by the at least one processor, cause the electronics module to], 'an electronics module mounted within the housing, the electronics module comprising2. The angle of attack sensor of claim 1 , wherein the sensor is an accelerometer claim 1 , and the signal is indicative of one of a linear acceleration of the vane and a rotational acceleration of the vane.3. The angle of the attack sensor of claim 2 , wherein the first damage criterion includes a first acceleration limit ...

Sensor Block, Pipe, and Production Method

The embodiments of the present invention relates to a sensor block for measuring fluid flow or pressure in a tube. The sensor block comprises a sensor and a housing. The housing has a resilient clamp part which is shaped such that it can be plugged onto a tube along the radial direction and is part of the tube in the plugged state. The invention also relates to a tube, which is produced by means of MID technology. The tube comprises conductor paths and a sensor, which is firmly connected to the tube. The tube further comprises two elongated grooves for releasable attachment of a sensor block. The embodiments of the present invention further relates to a production method, in which both a sensor block and a tube are manufactured with an identical mask set, injection molding tool or control program component. 1. (canceled)2. (canceled)3. (canceled)4. (canceled)5. (canceled)6. (canceled)7. (canceled)8. (canceled)9. (canceled)10. (canceled)11. (canceled)12. (canceled)13. (canceled)14. (canceled)15. (canceled)16. A sensor block for measuring fluid flow or pressure in a tube , the sensor block comprising:a sensor; anda housing with a resilient clamp part for the sensor block to be removably mounted on the tube;wherein the resilient clamp part is shaped such that the resilient clamp part can be plugged onto the tube along the radial direction and the resilient clamp part radially covers part of a wall of the tube.17. The sensor block of claim 16 , wherein the resilient clamp part has a longitudinal projection claim 16 , which extends parallel to a longitudinal axis of the tube when the sensor block is mounted on the tube.18. The sensor block of claim 16 , wherein the sensor is a differential pressure sensor and the sensor block has two openings facing the tube; each opening is pneumatically connected to a pneumatic connection of the differential pressure sensor.19. The sensor block of claim 16 , wherein the sensor is a differential pressure sensor;wherein the housing ...

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 ...

AERODYNAMIC MEASUREMENT PROBE WITH EVACUATION OF PENETRATED LIQUID BY GRAVITY

An aerodynamic measurement probe intended to measure a local angle of attack of an airstream flowing along the fuselage of an aircraft, comprises a support and a shaft that is able to rotate about a longitudinal axis with respect to the support. The support and the shaft are configured to form between one another a plurality of successive chicanes about the longitudinal axis. Each chicane makes it possible to transport liquid that has penetrated into the chicane: along a first path, under the effect of gravity, towards an evacuation circuit associated with the chicane and formed in the support, and along a second path, and counter to the effect of gravity, towards a successive chicane or towards the shaft. The evacuation circuit of each of the chicanes makes it possible to evacuate liquid out of the support under the effect of gravity moving away from the shaft. 1. An aerodynamic measurement probe intended to measure a local angle of attack of an airstream flowing along the fuselage of an aircraft , comprising a support and a shaft that is able to rotate about a longitudinal axis with respect to the support , along a first path, under the effect of gravity, towards an evacuation circuit associated with the chicane and formed in the support, and', 'along a second path, and counter to the effect of gravity, towards a successive chicane or towards the shaft;, 'the support and the shaft being configured to form between one another a plurality of successive chicanes about the longitudinal axis; each chicane making it possible to transport liquid that has penetrated into the chicanethe evacuation circuit of each of the chicanes making it possible to evacuate liquid out of the support under the effect of gravity moving away from the shaft.2. The probe according to claim 1 , wherein the support comprises a capturing chamber claim 1 , associated with a chicane claim 1 , towards which liquid that has penetrated into the chicane is driven under the effect of gravity; the ...

Process measurement probe bottoming indicator

Systems and methods are disclosed for indicating bottoming contact between an inner wall of a fluid carrying conduit and a distal tip process measurement probe. A process device, such as a fluid flow meter, has a process measurement probe configured for insertion into the fluid carrying conduit. An insertion mechanism is coupled to the process measurement probe and configured to apply force to insert the process measurement probe into the fluid carrying conduit. A bottoming indicator is configured to provide an indication of proper bottoming of the distal tip of the process measurement probe against the inner wall of the fluid carrying conduit as a function of an insertion related force or pressure.

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 ...

FLOW MEASUREMENT PROBE

A flow measurement probe includes an elongate probe having an averaging pitot tube with a plurality of upstream and downstream openings arranged along a length of the elongate probe, and a thermal flow measurement sensor coupled to the elongate probe. A method of measuring fluid flow rate in a process includes calculating a flow rate of the fluid using differential pressure in upstream and downstream openings of an averaging pitot tube in an elongate probe when the differential pressure is at least a defined measurement threshold, and calculating the flow rate of the fluid with a thermal mass flow sensor coupled to the flow measurement probe when the differential pressure is less than the defined measurement threshold. 1. A flow measurement probe , comprising:an elongate probe comprising an averaging pitot tube element having a plurality of upstream and downstream openings arranged along a length of the elongate probe; anda thermal flow measurement sensor coupled to the elongate probe.2. The flow measurement probe of claim 1 , wherein the thermal flow measurement sensor is isolated from the upstream and downstream openings.3. The flow measurement probe of claim 1 , wherein the thermal flow measurement sensor comprises two thermal mass flow sensors in a single chamber.4. The flow measurement probe of claim 3 , wherein the upstream and downstream openings have directional tube drilling from upstream and downstream sides of a flow of fluid past the averaging pitot tube.5. The flow measurement probe of claim 1 , wherein the thermal flow measurement sensor comprises an array of thermal mass flow sensors disposed in the elongate tube.6. The flow measurement probe of claim 1 , wherein the averaging pitot tube element comprises distinct sections connected via tubing for pressure communication.7. The flow measurement probe of claim 1 , wherein the thermal flow measurement sensor is disposed substantially at a center of the elongate probe along a height of the elongate probe. ...

ADJUSTABLE POSITION PITOT PROBE MOUNT

The present invention includes an adjustable Pitot tube and method for using the same for operating or flight testing an aircraft comprising: a Pitot probe; a streamline tube connected to the Pitot probe; a mount on the aircraft connected to the streamline tube, wherein the streamline tube can at least one of rotate about an axis of the mount, or the streamline tube can move the Pitot probe closer to, or away from, a skin of the aircraft. 1. An adjustable Pitot tube for an aircraft comprising:a Pitot probe;a streamline tube connected to the Pitot probe;a mount on the aircraft connected to the streamline tube, wherein the streamline tube can: rotate about an axis of the mount, or the streamline tube can move the Pitot probe closer to, or away from, a skin of the aircraft.2. The Pitot tube of claim 1 , wherein the Pitot probe is a simple Pitot tube claim 1 , a static source claim 1 , or a Pitot-static tube.3. The Pitot tube of claim 1 , wherein the mount comprises a plurality of openings that permit rotation of the mount along a longitudinal axis of the streamline tube.4. The Pitot tube of claim 1 , wherein the mount comprises a generally spherical mount that permits movement of the streamline tube in at least two-dimensions.5. The Pitot tube of claim 1 , wherein the streamline tube is connected to an actuator that is capable of linearly translating the streamline tube along a longitudinal axis of the streamline tube.6. The Pitot tube of claim 1 , wherein the mount comprises a generally spherical mount that is connected to one or more actuators claim 1 , wherein each of the one or more actuators provides rotational of the spherical mount in at least one dimension.7. The Pitot tube of claim 1 , wherein the Pitot tube further comprises a heater or a coating that prevents ice formation.8. The Pitot tube of claim 1 , wherein the position of the Pitot tube in at least two dimensions is controlled by a computer that is connected to one or more actuators that rotate the ...

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.

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.

SYSTEM FOR MEASURING SIX DEGREES OF FREEDOM

A system that measures six degrees-of-freedom of a remote target, the system including a dimensional measuring device having a camera, the remote target including a retroreflector, at least three light markers, and a pitch-yaw sensor, the six degrees-of-freedom determined based at least in part on measured 3D coordinates of the retroreflector by the dimensional measuring device, on a captured image of the at least three light markers by the camera, and on readings of the pitch-yaw sensor. 1. A system comprising:a six-DOF assembly having a first retroreflector and at least three light markers;a coordinate measuring device including a light source, a distance meter, a first motor, a second motor, a first angle measuring device, a second angle measuring device, a first camera and a second camera, the coordinate measuring device operable to direct a first light from the light source to the first retroreflector, the distance meter operable to measure a first distance to the first retroreflector, the first angle measuring device operable to measure a first angle to the first retroreflector, the second angle measuring device operable to measure a second angle to the first retroreflector, the first camera having a first lens and a first photosensitive array, the second camera having a second lens and a second photosensitive array, a focal length of the second lens being at least twice a focal length of the first lens, the first camera operable to form a first image of the at least three light markers, the second camera operable to form a second image of the at least three light markers; anda processor operable to determine six degrees-of-freedom of the six-DOF assembly based at least in part on the measured first distance, the measured first angle, the measured second angle, and at least one of the captured first image and the captured second image.2. The system of claim 1 , wherein the second camera further comprises a second retroreflector placed between the second lens ...

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 ...

DIFFERENTIAL PRESSURE SENSOR, AND FILTRATION DEVICE USED THEREWITH

A spool, including a substantially cylindrical flange portion and a substantially cylindrical front end portion which is thinner than the flange portion and whose center axis is substantially coincident with the center axis of the flange portion, is provided in a manner capable of slidingly moving in a cavity formed in a casing. The flange portion is inserted in a first cavity which has a center axis substantially coincident with the center axis of the casing and which has an inner diameter that is substantially the same as the diameter of the flange portion in length. The front end portion is inserted in a second cavity which is formed with its center axis being substantially coincident with the center axis of the casing, and which has an inner diameter greater than the diameter of the front end portion and less than the inner diameter of the first cavity in length. The rotation limiting portion, which has a rod-like shape thinner than the front end portion and which is provided along the front end portion in a manner contacting the side surface of the front end portion, is inserted in a groove portion formed on the side face of the second cavity. When the flange portion slidingly moves along the first cavity, the rotation limiting portion slidingly moves along the groove portion. 1. A differential pressure sensor comprising:a spool including a flange portion having a substantially cylindrical shape, and a front end portion having a substantially cylindrical shape, a center axis of the front end section being substantially coincident with a center axis of the flange portion, and the front end portion being thinner than the flange portion;a rotation limiting portion having a rod shape thinner than the front end portion, the limiting portion being positioned along the front end portion in a manner contacting a side surface of the front end portion;a casing having a substantially cylindrical shape and including a cavity formed therein, the spool and the rotation ...

Pitot tube designs for compressible and incompressible fluid flow with viscosity and turbulence

This invention presents a Pitot tube design and methodology for determining the flow characteristics of fluids in subsonic and supersonic flow, including the effects of viscosity and turbulence. A new methodology, the Two-Fluid Theory, is developed which treats a real fluid as being composed of two ideal fluids: an inviscid fluid and a Poiseuille fluid. The resulting expression for flow velocity is applicable to a real fluid of any viscosity and to pipes of any L/D ratios, including entrance effects. 1. this invention provides for two Pitot tube designs: one for incompressible , subsonic fluid flow; the other for compressible , supersonic fluid flow; that the designs are comprised of hollow tubes of length 10 cm and internal diameter 0.5 cm , opened at one end to the flow field; connected to pressure measuring devices at the opposite ends of the devices to measure total pressures; surrounded by annuli of 0.25 cm differential radii , sealed at both ends and connected to pressure measuring device to measure static pressures; small bore holes are positioned around the circumferences of the annuli and 1 cm from the flow entrances in accordance with a new theory , the Two-Fluid Theory , developed for this work , to ensure that the viscous component of the flow is fully established; that the device used for supersonic flow is insulated to fulfill adiabatic conditions , its annulus abbreviated to minimize heat loss; and temperature measuring devices can be added to ensure that adiabatic conditions are met , which are not required for the device used for incompressible fluid flow since isothermal conditions are satisfactory , rendering Pitot tubes for such applications much simpler to fabricate , operate and maintain.21. the devices of claim () , made of stainless steel , nickel alloy , titanium or other metal or material suitable for the flow field conditions , are supported by rigid frames to the surfaces of aircraft , walls of pipes , or other structures within a flow ...

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 ...

Aircraft Nonlinear Dynamic Instability Warning System

A system and method for predicting aircraft nonlinear instability includes the steps of: (1) a pre-built aircraft state parameters for all possible flight conditions, (2) real time measuring flight parameters to determine aircraft state, (3) calculating the inertial coupling frequencies and periods as well as the nonlinear instability threshold based on the nonlinear instability theory recently developed by the inventor, (4) providing a first warning signal if the threshold is approached, (5) providing a second warning signal if the threshold has been exceeded. 2. The method of claim 1 , wherein the pre-obtained aircraft state parameter and coefficient data are obtained in advance by measurements and analyses during test flights of an aircraft.3. The method of claim 1 , wherein the pre-obtained aircraft state parameter and coefficient data are obtained in advance by empirical formulas and aerodynamic derivatives based on wind tunnel tests.4. The method of claim 1 , wherein the minimum threshold βis in the range of (0.0018 claim 1 , 0.09) radian claim 1 , i.e. (0.1° claim 1 , 5°) and depending on aircraft type and size.5. The method of claim 1 , wherein the safety factor λ is in the range of (0.5 claim 1 , 0.99) and depending on individual aircraft type and size.7. The method of claim 6 , wherein the pre-obtained aircraft state parameter and coefficient data are obtained in advance by measurements and analyses during test flights of an aircraft.8. The method of claim 6 , wherein the pre-obtained aircraft state parameter and coefficient data are obtained in advance by empirical formulas and aerodynamic derivatives based on wind tunnel tests.9. The method of claim 6 , wherein the minimum threshold βis in the range of (0.0018 claim 6 , 0.18) radian claim 6 , i.e. (01.° claim 6 , 10°) and depending on individual aircraft type and size.10. The method of claim 6 , wherein the safety factor A is in the range of (0.5 claim 6 , 0.99) and depending on individual aircraft type ...

Apparatus for measurement of ducted air

Apparatus and methods for measurement of airflow in a duct are described. The apparatus combines a Pitot tube, sensing apparatus, control apparatus, a display, control switches and carry apparatus arranged into a unitary structure.

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.

METHOD FOR INTERNAL COMBUSTION ENGINE EXHAUST FLOW MEASUREMENT CALIBRATION AND OPERATION

A calibration method for a flow measuring device used with a vehicle exhaust analysis system includes the flow measuring device being connected with the vehicle exhaust system wherein exhaust gases are directed through the flow measuring device. A portable flow calibration device is connected in a manner that exhaust gases of the vehicle exhaust system are directed through the portable flow calibration device. The vehicle is operated so that exhaust gas flows through the flow measuring device and the flow calibration device. The flow measuring device is calibrated with the portable flow calibration device. The flow measuring device includes a Pitot tube assembly in a flow tube wherein gas flowing through the flow tube passes the Pitot tube assembly. The Pitot tube assembly includes a sensing tube and at least one pressure sensing port connected with the sensing tube. The sensing tube includes a plurality of sensing openings that are positioned at different portions of gas flowing through the flow tube. 1. A calibration method for a flow measuring device used with a vehicle exhaust analysis system , said method comprising:said flow measuring device being connected with the vehicle exhaust system wherein exhaust gases are directed through said flow measuring device;connecting a portable flow calibration device wherein exhaust gases of the vehicle exhaust system are directed through the portable flow calibration device;operating the vehicle wherein exhaust gas flows through said flow measuring device and said flow calibration device;calibrating the flow measuring device with the portable flow calibration device.2. A flow measuring device comprising:a Pitot tube assembly in a flow tube wherein gas flowing through said flow tube passes said pitot tube assembly; andsaid Pitot tube assembly comprising a sensing tube and at least one pressure sensing port connected with said sensing tube, said sensing tube comprising a plurality of sensing openings that are positioned at ...

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.

RELATIVE WIND DISPLAY AND LANDING AID

A system for displaying information obtained along the direction of flight of an aircraft is provided. The system includes a vane assembly pivotally mounted to the aircraft having a sensor mounted thereto. The vane comprises a pointing axis configured to continuously align with the direction of the flight path of the aircraft. A display device is operatively connected to the output of the sensor for providing a display along the actual flight path of the aircraft. 1. A method of conveying flight path information of an aircraft comprising:capturing a visual indication of a flight path of the aircraft using an optical sensor associated with a vane mounted to an exterior of the aircraft; andtransmitting a signal indicative of the captured visual indication of the flight path.2. The method of claim 1 , further comprising the steps of:receiving the transmitted signal; anddisplaying the visual indication of the flight path of the aircraft.3. The method of claim 2 , wherein the step of displaying the visual indication of the flight path includes displaying the visual indication of the flight path on a video monitor.4. The method of claim 1 , wherein the step of transmitting the signal indicative of the captured visual indication of the flight path includes generating a wireless transmission signal.5. The method of claim 1 , wherein the vane is mounted such that a pointing axis thereof is aligned with the direction of the flight path of the aircraft.6. The method of claim 6 , wherein a sensing axis of the optical sensor is aligned with the pointing axis of the vane.7. A sensor assembly for conveying flight path information comprising:a vane configured to be pivotally mounted to an exterior of an aircraft, the vane comprising a pointing axis for aligning with the direction of the flight path of the aircraft; andan optical sensor associated with the vane, the optical sensor having a sensing axis aligned with the pointing axis of the vane;wherein the optical sensor is ...

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 ...

Methop for determining airplane flight-path angle with the use of airspeed and the global positi0ning system (gps)

The angle of attack (AOA) of an airplane is calculated as the difference of the flight-path angle and the pitch angle. The pitch angle is available from an attitude monitoring device (e.g., pitch gyro), but the flight-path angle is not available from the basic instruments common in general aviation. This method determines the flight-path angle mathematically, and in particular, using inputs from indicated airspeed and GPS. The sine (trig function) of the flight-path angle is the value determined by dividing the vertical velocity, provided by onboard GPS, by the velocity along the flight path (e.g., indicated airspeed). The sine value is converted to the value of flight-path angle by referring to a sine lookup table.

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.

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 ...

Method And System For Estimating The Flaps Position Of An Aircraft

An estimation system includes a module for measuring a current angle of attack and current flight parameters of the aircraft, a module for estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft, a module for estimating an angle of attack for a zero lift from the current angle of attack, from the current lift coefficient and from a slope of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack, a module for estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift and a module for sending the current position of the flaps to a user device. 1. A method for estimating the position of flaps of an aircraft , comprising:a measurement step, implemented by a measuring module, including measuring a current angle of attack of the aircraft and current flight parameters of the aircraft;a first estimation step, implemented by a first estimating module, including estimating a current lift coefficient of the aircraft from the current flight parameters and from a mass of the aircraft;{'sub': 0', 'zα, 'a second estimation step, implemented by a second estimating module, including estimating an angle of attack (α) for a zero lift from the current angle of attack, from the current lift coefficient estimated in the first estimation step and from a slope (C) of an affine part of at least one theoretical curve describing a lift coefficient of the aircraft as a function of an angle of attack;'}a third estimation step, implemented by a third estimating module, including estimating the current position of the flaps of the aircraft from the angle of attack for a zero lift, estimated in the second estimation step; anda sending step, implemented by a sending module, including sending the current position of the flaps to a user device.2. The method according to claim 1 , wherein the measurement step comprises:a ...

FLOWMETER PRIMARY ELEMENT WITH SENSORS

A process variable transmitter is configured as a flowmeter for measuring flow of a process fluid through a conduit. The transmitter includes a pitot tube extending into the conduit which creates a differential pressure in the process fluid due to flow of the process fluid. An upstream process variable sensor is mounted on the pitot tube and coupled to the flow of process fluid to sense an upstream process variable of the process fluid. A downstream process variable sensor is mounted on the pitot tube downstream of the upstream process variable sensor and coupled to the flow of process fluid to sense a downstream process variable of the process fluid. Measurement circuitry determines the flow of the process fluid based upon the upstream process variable and the downstream process variable. 1. A flowmeter for measuring flow of a process fluid through a conduit , comprising:a pitot tube extending into the conduit which creates a differential pressure in the process fluid due to flow of the process fluid;an upstream process variable sensor mounted on the pitot tube and exposed to a pressure generated by the flow of process fluid configured to sense an upstream process variable of the process fluid;a downstream process variable sensor mounted downstream of the upstream process variable sensor mounted on the pitot tube and exposed to a pressure generated by the flow of process fluid configured to sense a downstream process variable of the process fluid; andmeasurement circuitry configured to determine the flow of the process fluid based upon the upstream process variable and the downstream process variable.2. The flowmeter of wherein the upstream and downstream process variable sensors comprise pressure sensors.3. The flowmeter of including a differential pressure sensor configured to sense a differential pressure created by the pitot tube.4. The flowmeter of wherein the measurement circuitry provides an output based upon a difference between the measured differential ...

PITOT TUBE TRAVERSE ASSEMBLY

A pressure measurement system for measuring pressure in a conduit has a bluff body extending into the conduit. The bluff body has an upstream opening and a downstream opening. An upstream pitot tube is slidably engaged within the bluff body and has an open end positioned in the upstream opening. A downstream pitot tube is slidably engaged within the bluff body and has an open end positioned in the downstream opening. A differential pressure sensor is fluidly coupled to the upstream pitot tube and the downstream pitot tube to measure a pressure difference between the upstream pitot tube and the downstream pitot tube. 1. A pressure measurement system for measuring pressure in a conduit , comprising:a bluff body extending into the conduit and having an upstream opening and a downstream opening;an upstream pitot tube slidably engaged within the bluff body and having an open end positioned in the upstream opening;a downstream pitot tube slidably engaged within the bluff body and having an open end positioned in the downstream opening;a differential pressure sensor fluidly coupled to the upstream pitot tube and the downstream pitot tube to measure a pressure difference between the upstream pitot tube and the downstream pitot tube.2. The pressure measurement system of wherein the differential pressure sensor measures a first pressure difference when the upstream pitot tube and the downstream pitot tube are in a first position within the bluff body and wherein the differential pressure sensor measures a second pressure difference when the upstream pitot tube and the downstream pitot tube are in a second position.3. The pressure measurement system of wherein the upstream opening and the downstream opening are both slots.4. The pressure measurement system of wherein at least one of the upstream pitot tube and the downstream pitot tube further comprises exterior markings that indicate the position of at least one of the upstream pitot tube and the downstream pitot tube within ...

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.

VARIABLE LINE SIZE AVERAGING PITOT TUBE

Systems, apparatus and methods are disclosed for coupling an averaging picot tube (APT) primary element to a process pipe. A mounting assembly mounts the APT primary element to the process pipe such that a length of the APT primary element extending into the process pipe is adjustable to accommodate different sized process pipe diameters. The mounting assembly includes a weld coupling coupled to the process pipe over an opening in the process pipe and having the APT primary element extending therethrough into the process pipe. An extension pipe nipple is connected to the weld coupling and has the APT primary element extending therethrough such that a transition between a neck section and a sensor section of the APT primary element is positioned inside the extension pipe nipple. A union component, a ferrule, and a cap keep the APT primary element in the mounted position and form a process seal. 1. A process variable monitoring system for measuring a process variable indicative of a flow rate of a process fluid in a range of different sized process pipes , the system comprising:a process variable transmitter;a pressure sensor in the process variable transmitter;an averaging pitot tube (APT) primary element having a distal region including one or more slots, the APT primary element being extendable into the process pipe to couple process pressures of the process fluid to the pressure sensor such that the pressure sensor provides as an output pressure measurement indicative of the flow rate of process fluid in the process pipe, wherein the distal region including the one or more slots is sized such that for larger diameter process pipes the one or more slots span a smaller percentage of the pipe diameter than for smaller diameter pipes; anda mounting assembly configured to mount the APT primary element to the process pipe and provide a process seal such that a length of the APT primary element extending into the process pipe is adjustable for different sized process ...

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.

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.

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. A pitot device for use in an airflow , comprising:a pitot housing forming a cavity having a housing external orifice characterized by a housing external-orifice height;an air-permeable fabric extending across a section of the cavity and defining an internal chamber; anda pressure sensor configured to sense information regarding the pressure within the internal chamber;wherein the distance within the cavity between the air-permeable fabric and the housing external orifice is less than 2.4 times the housing external-orifice height.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 claim 2 , wherein the autopilot is configured to provide flight control information based on the airspeed ...

Pneumatic Filter

A tuned sensor system is disclosed. The tuned sensor system may receive an unsteady pressure from an external environment via a pressure inlet port. The pressure may have a first component that is substantially static and a second component that varies at a relatively high frequency. The pressure inlet port may conduct the unsteady pressure to a tuned path. The tuned path may filter the unsteady pressure, blocking the second component and communicating the first component, such as for use by a pressure sensor. The tuned sensor system may be compact and may include one or more turn in the tuned path so that the distance between the pressure inlet port and the sensor is less than the length of the tuned path. The tuned path may be entirely within the supporting structure of the tuned sensor system, easing installation, removal, and maintenance of the compact and modular system. 1. A modular tuned sensor system comprising:a main body having a tuned path in fluidic communication with a pressure inlet port;an enclosing member having a substantially planar structure defining a portion of the tuned path of the main body and substantially sealing the tuned path from leaking; andthe pressure inlet port having an aperture disposed in the enclosing member; anda sensor terminus having an aperture defined through the main body and in fluidic communication with the tuned path.2. The modular tuned sensor system according to claim 1 , wherein the tuned path comprises a channel disposed in the main body and receiving an unsteady pressure from the pressure inlet port claim 1 , andwherein the pressure inlet port is in fluidic communication with an external environment.3. The modular tuned sensor system according to claim 2 ,wherein the unsteady pressure comprises a first component with a substantially static pressure and a second component with a high frequency variable pressure, andwherein the tuned path blocks the second component and transmits the first component from the pressure ...

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 ...

EXHAUST GAS FLOW RATE MEASURING UNIT AND EXHAUST GAS ANALYZING APPARATUS

The present invention is an exhaust gas flow rate measuring unit that eliminates the disturbance of the flow velocity distribution of exhaust gas flowing through an attachment pipe to accurately measure an exhaust gas flow rate, and is mounted in a vehicle to measure the flow rate of exhaust gas emitted from an exhaust pipe of the vehicle. In addition, the exhaust gas flow rate measuring unit includes the attachment pipe that is connected to the exhaust pipe and forms a flow path through which the exhaust gas flows, a flowmeter that is provided in the flow path and measures the flow rate of the exhaust gas flowing through the flow path, and a straightening mechanism that is provided on the upstream side of the flowmeter in the flow path. 1. An exhaust gas flow rate measuring unit that is mounted in a vehicle and measures a flow rate of exhaust gas emitted from an exhaust pipe of the vehicle , the exhaust gas flow rate measuring unit comprising:an attachment pipe that is connected to the exhaust pipe and forms a flow path through which the exhaust gas flows;a flowmeter that is provided in the flow path and measures the flow rate of the exhaust gas flowing through the flow path; anda straightening mechanism that is provided on an upstream side of the flowmeter in the flow path.2. The exhaust gas flow rate measuring unit according to claim 1 , whereinthe attachment pipe includes a straight pipe part, andthe flowmeter and the straightening mechanism are provided in the straight pipe part.3. The exhaust gas flow rate measuring unit according to claim 2 , whereinthe attachment pipe includes a curved pipe part or a junction part on an upstream side of the straight pipe part.4. The exhaust gas flow rate measuring unit according to claim 1 , used for an on-road running test of the vehicle.5. The exhaust gas flow rate measuring unit according to claim 1 , whereinthe flowmeter is a Pitot tube flowmeter.6. The exhaust gas flow rate measuring unit according to claim 1 , ...

FLYING OBJECT POSITION MEASURING APPARATUS, FLYING OBJECT POSITION MEASURING METHOD, AND NON-TRANSITORY STORAGE MEDIUM

A flying object position measuring apparatus includes an optical sensor, a storage, an orientation calculator, and a position calculator. The optical sensor obtains an image of a flying object. The flying object performs flight along a ballistic trajectory. The storage stores, in advance, basic trajectory information regarding a basic trajectory of the flying object. The basic trajectory information includes position information of a start point at which the flying object starts the flight. The orientation calculator calculates an orientation of the flying object as viewed from the optical sensor on the basis of the image obtained by the optical sensor. The position calculator calculates, as a position of the flying object, an intersection of a plane of rotation with the orientation of the flying object. The plane of rotation is a plane based on a rotation of the basic trajectory around a vertical axis that travels through the start point. 1. A flying object position measuring apparatus comprising:an optical sensor configured to obtain an image of a flying object, the flying object configured to perform flight along a ballistic trajectory;a storage that stores, in advance, basic trajectory information regarding a basic trajectory of the flying object, the basic trajectory information including position information of a start point at which the flying object starts the flight;an orientation calculator configured to calculate an orientation of the flying object as viewed from the optical sensor on a basis of the image obtained by the optical sensor; anda position calculator configured to calculate, as a position of the flying object, an intersection of a plane of rotation with the orientation of the flying object, the plane of rotation being a plane based on a rotation of the basic trajectory around a vertical axis, the vertical axis traveling through the start point.2. The flying object position measuring apparatus according to claim 1 , wherein claim 1 , when two ...

BALLAST WATER TREATMENT MONITORING SYSTEM

A system for withdrawing samples of fluids comprises a pitot tube assembly, a flow sensor to measure a flow rate of the sample, and a pump connected to the pitot tube assembly to withdraw a sample, wherein the system is configured to match a sample flow velocity to the flow velocity sensed by a flow sensor on a pitot wand. The pitot tube assembly comprises a housing with a sample outlet and a return sample inlet, an extendable/retractable pitot wand within the housing, wherein the pitot wand includes a passage extending the length thereof to transfer a sample from a pitot tube end to a sealed compartment in the housing connected to the sample outlet; wherein the return sample inlet is connected to a passage in the housing leading to an outlet from the housing, and a flow sensor on an end of the pitot wand. 1. A system for withdrawing samples of water and other fluids , comprising: a housing with a sample outlet and a return sample inlet;', 'an extendable/retractable pitot wand within the housing, wherein the pitot wand includes a passage extending the length thereof to transfer a sample from a pitot tube end to a sealed compartment in the housing connected to the sample outlet; wherein', 'the return sample inlet is connected to a passage in the housing leading to an outlet from the housing;', 'a flow sensor on an end of the pitot wand;, 'a pitot tube assembly, comprisinga flow sensor configured to measure a flow rate of the sample; anda pump connected to the pitot tube assembly to withdraw a sample from the pitot wand, wherein the system is configured to match a sample flow velocity to the flow velocity sensed by the flow sensor on the pitot wand.2. The system of claim 1 , further comprising a pitot tube placed perpendicular to the pitot wand on the end thereof.3. The system of claim 1 , further comprising a processor to control a pump speed to control the sample flow rate.4. The system of claim 1 , further comprising a processor and one or more control valves to ...

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.

MONITORING DEVICE WITH MODULAR ASSEMBLY

A monitoring device includes a cavity assembly with a plurality of cavities. Openings of the plurality of cavities are distributed about a flow-facing surface of the cavity assembly. A gas pressure sensor is disposed within each of the cavities, and is configured to measure an absolute pressure of a gas flow which flows past the monitoring device. Gas pressure measurements from the pressure sensors may be used to determine a flow speed and a flow direction of the gas flow. More specifically, a mapping may be used to map the logarithm of the difference between the maximum and minimum pressures to a flow speed. Further, a lookup table may be used to map a pattern of pressure measurements to a flow direction. 1. A monitoring device , comprising:a cavity assembly with a plurality of cavities;a plurality of sensors; anda sensor support that supports the plurality of sensors,wherein the cavity assembly has a first interface that is formed by a sensor-facing surface with a first plurality of openings,wherein each one of the first plurality of openings is fluidly connected with one of the plurality of cavities,wherein the sensor support has a second interface that is formed by a top surface of the sensor support and the plurality of sensors,wherein the first interface is geometrically complementary to the second interface, andwherein the second interface is geometrically complementary to the first interface.2. The monitoring device of claim 1 , wherein the sensor-facing surface is a planar surface.3. The monitoring device of claim 1 , wherein the top surface of the sensor support is a planar surface.4. The monitoring device of claim 1 , wherein the plurality of sensors is disposed on the top surface of the sensor support.5. The monitoring device of claim 1 , wherein the plurality of sensors is disposed in a single plane.6. The monitoring device of claim 1 , wherein each one of the first plurality of openings from the first interface is configured to receive one of the ...

FEATURES TO PREVENT ICE ACCUMULATION ON HEATED FACEPLATE

A wall for a heated faceplate includes a base and tines protruding from the base and spaced from each another. The tines are configured to accumulate ice in a manner which promotes shedding of small ice formations to prevent large accumulations of ice father aft on the faceplate. 1. A wall for a heated faceplate comprising:a base; andtines protruding from the base and spaced from each another, wherein the tines are configured to accumulate ice.2. The wall of claim 1 , further including grooves positioned between the tines.3. The wall of claim 1 , wherein the tines are substantially parallel to oncoming airflow.4. The wall of claim 1 , wherein the tines are configured to shed the accumulated ice.5. The wall of claim 1 , wherein the tines are configured to accumulate ice in unstable shapes.6. The wall of claim 1 , wherein the wall is configured to be attached to an upstream portion of the heated faceplate.7. The wall of claim 1 , wherein the wall is unitary with an upstream portion of the heated faceplate.8. The wall of claim 1 , wherein the wall is a horse-shoe shape.9. The wall of claim 1 , wherein the wall is curved.10. The wall of claim 1 , wherein the wall is straight.11. The wall of claim 1 , wherein the tines overhang the base in an upstream direction.12. The wall of claim 1 , wherein the tines have rounded edges.13. A faceplate comprising:an upstream portion;a downstream portion adjacent the upstream portion; and a base connected to the exterior surface of the faceplate at the upstream portion of the faceplate; and', 'tines protruding from the base, wherein the tines are substantially parallel to oncoming airflow., 'a wall at the upstream portion of the faceplate; the wall including14. The faceplate of claim 13 , wherein the faceplate is a faceplate for an angle of attack sensor.15. The faceplate of claim 13 , wherein the faceplate is a faceplate for a flush static plate.16. The faceplate of claim 13 , wherein the wall further includes grooves positioned ...

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 , ...

METHOD AND DEVICE FOR MEASURING THE ANGLE OF ATTACK AND THE SIDESLIP OF AN AIRCRAFT

According to the present invention, use is made of a probe provided with a central sensor, with off-centred sensors and lateral sensors, and said probe is articulated on the aircraft around two orthogonal axes. 1. Method for measuring the angle of attack of the longitudinal axis of an aircraft with respect to the relative wind , in which method a probe is used which is provided , at the front end thereof , with a central directional sensor which is arranged at the intersection of the horizontal and vertical midplanes of said probe , and with at least two eccentric midplane directional sensors which are in parallel with said central directional sensor and are arranged at an equal distance therefrom on either side of said horizontal midplane of said probe , the method comprising:pivotally connecting said probe to said aircraft about a first pivot axis which is in parallel with said horizontal midplane of said probe and is orthogonal to said longitudinal axis of the aircraft;rotating said probe about said first pivot axis in order to make said probe assume the particular inclined position in which the measurements provided by said eccentric midplane directional sensors are equal; andmeasuring the particular angle of inclination which is produced, in this particular inclined position, between said horizontal midplane of the probe and the longitudinal axis (L-L) of the aircraft,wherein said probe is provided, at the front end thereof and in addition to said central directional sensor and said eccentric midplane directional sensors, with at least two lateral directional sensors which are in parallel with said central directional sensor and are arranged at an equal distance therefrom on either side of said vertical midplane of said probe, and wherein, in order to measure the sideslip of the aircraft, the method comprises:pivotally connecting said probe to said aircraft about a second pivot axis which is in parallel with said longitudinal axis of the aircraft;rotating said ...