WO2004113929A1 - In-situ control system, characterisation device and method for control of an angle of attack probe - Google Patents

In-situ control system, characterisation device and method for control of an angle of attack probe Download PDF

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Publication number
WO2004113929A1
WO2004113929A1 PCT/EP2004/051125 EP2004051125W WO2004113929A1 WO 2004113929 A1 WO2004113929 A1 WO 2004113929A1 EP 2004051125 W EP2004051125 W EP 2004051125W WO 2004113929 A1 WO2004113929 A1 WO 2004113929A1
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WO
WIPO (PCT)
Prior art keywords
angle
probe
flag
enveloping structure
relative
Prior art date
Application number
PCT/EP2004/051125
Other languages
French (fr)
Inventor
Philippe Roberge
Dominique Thomas
Original Assignee
Thales
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Thales filed Critical Thales
Priority to EP04741809A priority Critical patent/EP1636596A1/en
Publication of WO2004113929A1 publication Critical patent/WO2004113929A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments
    • B64D43/02—Arrangements or adaptations of instruments for indicating aircraft speed or stalling conditions
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P13/00—Indicating or recording presence, absence, or direction, of movement
    • G01P13/02—Indicating direction only, e.g. by weather vane
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P13/00—Indicating or recording presence, absence, or direction, of movement
    • G01P13/02—Indicating direction only, e.g. by weather vane
    • G01P13/025—Indicating direction only, e.g. by weather vane indicating air data, i.e. flight variables of an aircraft, e.g. angle of attack, side slip, shear, yaw
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01P—MEASURING LINEAR OR ANGULAR SPEED, ACCELERATION, DECELERATION, OR SHOCK; INDICATING PRESENCE, ABSENCE, OR DIRECTION, OF MOVEMENT
    • G01P21/00—Testing or calibrating of apparatus or devices covered by the preceding groups
    • G01P21/02—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers
    • G01P21/025—Testing or calibrating of apparatus or devices covered by the preceding groups of speedometers for measuring speed of fluids; for measuring speed of bodies relative to fluids

Definitions

  • the invention relates to an on-site control device, a characterization device and a method for controlling a mobile incidence probe, for example mounted on the skin of an aircraft.
  • a mobile incidence probe for any mobile device making it possible to measure the incidence of air relative to the skin of the aircraft, such as for example a mobile multifunction probe comprising, in addition to determining the incidence, pressure taps for example to determine the total pressure and the static pressure of the air surrounding the aircraft.
  • An incidence sensor is a device for measuring the orientation of the wind.
  • the invention finds more particularly its application in the aeronautical industry, where the adjustment of an incidence probe is of vital importance. In fact, the value of the measurement of the orientation of the apparent wind of an aircraft makes it possible to obtain, after calculation, the value of the incidence and lift parameters.
  • An incidence sensor is an organ, part of which is located outside the aircraft. This external part is subject to climatic variations, in particular to temperature variations. In addition, it can be damaged by impacts with external bodies, such as birds, grains of sand or particles of ice. More generally, it can be worn by external forces which can be applied. The conditions outside an aircraft are very harsh. The part of the incidence sensor directly sensitive to wind is fragile. Forces applied to this device in flight are very strong. These forces can further modify the setting of the wind sensitive part with respect to the orientation sensors to which it is connected. For economic reasons, when the incidence probe needs to be replaced, only a limited part of it is replaced. An incidence probe thus comprises a wind vane which is movable in the wind, a sensor support and a probe body.
  • the most precise adjustment method requires adjusting the wind vane using a wind tunnel. Indeed, the wind tunnel creates a perfectly known orientation wind. A complete incidence sensor is then directly adjusted according to the orientation of the wind supplied by the wind tunnel. Under these conditions, a complete incidence probe placed on the aircraft is perfectly adjusted. The adjustment is carried out by fixing the wind vane in a known position relative to the probe body, and by mechanically adjusting the position of the sensor support relative to this probe body, so that a signal delivered by the sensors in the known position of the weather vane is worth an expected value.
  • Aerodynamic zero is observed in the wind tunnel. It corresponds to an orientation of the wind vane in the wind axis of the wind tunnel, and to a corresponding position of the sensor support, which in this case gives an expected measurement signal (generally a zero signal).
  • the relative positions of the wind vane with respect to the sensor support are finally identified. In practice this location is obtained by locating the wind vane relative to the probe body, and also locating the sensor support relative to the probe body. Aerodynamic zero is identified for example by a hole, made in the factory, on the wind vane.
  • the adjustment principle in the prior art, is to fix the hole representing the aerodynamic zero in a known position relative to the probe body, and to place the orientation sensor, relative to this fixed assembly, in a position such that the measurement signal delivered is the expected measurement signal (generally the zero signal).
  • the aerodynamic zero determination operation carried out in a wind tunnel is called characterization of the incidence probe.
  • FIG. 1 placed at the end of this description, schematically illustrates the general structure of an incidence probe 10.
  • the incidence probe 10 comprises a probe body 11 constituted by a housing, generally cylindrical, closed on its upper part by a plate 12, advantageously circular.
  • a wind vane 13 comprises a base 14, of small thickness and movable around an axis ⁇ s, which is also called probe axis.
  • the wind vane 13 also includes a flag 15 surmounting the base 14. The flag 15 is intended to orient itself in the wind surrounding the incidence probe 10.
  • the shape and profile of the section of this flag 15 are determined by the final application of the probe, that is to say essentially the type of aircraft for which it is intended, the degree of precision of the angle measurements. to obtain and a certain number of physical parameters describing the environmental conditions to which the incidence probe is subjected: maximum speed reached by the aircraft, therefore also air flowing along the walls of the cabin, variations maximum temperatures, etc. these considerations go beyond the precise scope of the invention. Indeed, the positioning device object of the invention, and this is one of the advantages of it, remains compatible with all types of flag probes of the known art and does not require any modification, either structural or functional. .
  • the housing contains in particular a rotation angle sensor of the wind vane 13, and more precisely of the flag 15, around the axis ⁇ s relative to the probe body 11.
  • the latter may call for a measurement based on use a potentiometer whose axis is driven by the rotation of the flag 15, of a sensor of the so-called “resolver” type or of any other sensor of the known art suitable for this field of application.
  • the amplitude of the rotation of the vane 13 around the axis ⁇ s is converted into electrical signals, transmitted by links 16 to a signal processing device (not shown) located inside the aircraft, generally in the cockpit, to be finally displayed on an on-board instrument in an appropriate form, according to the parameters measured.
  • the probe body 11 is arranged in an orifice (not shown) provided for this purpose in the cabin of the aircraft and covered with a cover (not shown) so that what is called the "skin" of the 'aircraft, referenced PA, is flush with the upper surface of the base 14 of the wind vane 13. It is indeed necessary that, with the exception of the protrusion formed by the flag 15, no roughness remains which would disturb the flow of air streams outside the PA skin.
  • the incidence probe 10 comprises means for positioning relative to the skin PA of the aircraft.
  • the positioning means comprise for example two lugs 17 and 18 intended to penetrate into corresponding holes made in the skin PA. Through lugs 17 and 18 passes a straight line ⁇ v concurrent with the axis ⁇ s.
  • the airlines want us to be able to test the correct operation and certify the accuracy of the measurement signals supplied by the incidence probes, if possible. without having to remove them, that is to say disassemble them, extract them from their housing, then reassemble them after testing, which would result in long and costly operations.
  • the precision of the measurements required is very high: typically a few tenths of degrees, and that on the other hand, the environmental conditions to which the impact probes are subjected are extremes. If it is necessary to remove the incidence probe, it is desirable to avoid the use of a blower to test or adjust the incidence probe using as much as possible a site bench.
  • the site rigging bench is used at the foot of the aircraft, that is to say after dismantling the aircraft's incidence probe.
  • a factory setting bench for an incidence probe is described. with a weather vane.
  • This bench uses a point mechanical reference against which the mobile flag of the probe rests.
  • the factory setting bench allows the characterization of the incidence probe. More precisely, the factory setting bench makes it possible to determine a difference between the angular orientation of the mobile flag between a first position where it is in abutment against the point mechanical reference and a second position where it is oriented freely relative to a wind. known direction obtained by wind tunnel.
  • a device for angular in situ positioning of an incidence probe comprising a wind vane.
  • This device comprises an enveloping structure intended to receive the mobile flag of the wind vane.
  • the in situ positioning device is used when the incidence probe is mounted on the skin PA of the aircraft.
  • the in situ positioning device makes it possible to control the linearity of the orientation sensor and makes it possible to obtain an accuracy of the order of a degree in the zero adjustment of the sensor. Better precision cannot be obtained because the mechanical reference of the in situ positioning device is different from the mechanical reference of the site setting bench or the factory setting bench.
  • the invention makes it possible to solve this problem by using a single mechanical reference for the three operations described above, namely the characterization in the factory, the control of the probe on site, at the foot of the aircraft and the angular adjustment of the probe. mounted on the aircraft.
  • the subject of the invention is a device for on-site control of an incidence probe, the probe comprising a probe body, a flag movable in rotation about an axis relative to the probe body, characterized in what it further comprises an enveloping structure intended to receive the flag, the flag being able to be immobilized temporarily with respect to the enveloping structure, and means for measuring an angle of the enveloping structure with respect to the probe body .
  • the subject of the invention is also a method of on-site control of an incidence probe, the probe comprising a probe body, a flag which can move in rotation about an axis with respect to the probe body and a sensor for angle of rotation of the flag relative to the probe body around the axis, characterized in that the device further comprises an enveloping structure intended to receive the flag, the flag being able to be immobilized temporarily relative to the enveloping structure, and means for measuring an angle of the enveloping structure relative to the probe body, and in that the method consists in: - immobilizing the probe body relative to a support of the device,
  • the subject of the invention is also a device for characterizing an incidence probe, the probe comprising a flag which is mobile in rotation about an axis, characterized in that the device comprises an enveloping structure intended to receive the flag, and in that the enveloping structure forms a mechanical reference in determining a characterization angle of the probe.
  • FIG. 1 shows an exemplary embodiment of an incidence probe for aircraft of the type comprising a wind vane movable around an axis; Figure 1 has been described above to present the invention;
  • FIG. 2 shows a characterization device or on-site control device for an incidence probe comprising an inclinometer oriented perpendicular to the axis of rotation of the wind vane;
  • FIG. 3 shows the device of Figure 2 in which the inclinometer is oriented parallel to the axis of rotation of the vane.
  • Figure 2 are shown the common elements of a characterization device and an on-site control device of an incidence probe.
  • the characterization device is used in the wind tunnel and includes means for positioning in the wind tunnel. These means are not shown in FIG. 2.
  • the on-site control device is used at the foot of the aircraft. More specifically, when an incidence probe must be controlled, it is removed from the aircraft and then temporarily placed on the on-site control device located near the aircraft. The on-site control device allows the control and adjustment of the angle of attack sensor without requiring the use of a blower.
  • the device shown in Figure 2 comprises a support 20 having the shape of a square.
  • the support 20 has a high rigidity so as not to deform during the various operations necessary for checking the probe.
  • the support 20 comprises a first horizontal wing 21 and a second vertical wing 22.
  • the device may include adjustment screws 23 and 24 as well as a spirit level 25 in order to adjust, during the mounting of the incidence probe on the support 20, the verticality of the straight line ⁇ v defined using the figure 1.
  • the second wing 22 comprises means for immobilizing the probe body 11 on the wing 22 so that the probe axis ⁇ s is in a horizontal position.
  • These means comprise for example a circular orifice pierced in the wing 22 and similar to that produced in the skin PA of the aircraft as well as means for fixing the probe body 11 on the wing 22.
  • the means for immobilizing the body probe 11 on the wing 22 also have holes intended to receive the pins 17 and 18. These holes are similar to those made in the skin PA of the aircraft for positioning the incidence probe when the latter is mounted on the aircraft.
  • the device further comprises an enveloping structure 26 intended to receive the flag 15 of the incidence probe 10.
  • the enveloping structure 26 comprises for example two half-shells 27 and 28 between which the flag 15 is temporarily immobilized. other ⁇
  • the device comprises means for measuring an angle of the enveloping structure 26 relative to the probe body 11.
  • the angle of the enveloping structure 26 relative to the probe body 11 is an angle of rotation of the flag 15 around its axis of rotation ⁇ s.
  • the measuring means may comprise an index 30 secured to the enveloping structure 26 and a graduated angular sector 31 secured to the support 20.
  • the index 30 moves in rotation around the axis ⁇ s with the enveloping structure 26 and consequently makes it possible to display the angular position of the flag 15 around its axis of rotation ⁇ s.
  • the index 30 moves in front of the graduated angular sector 31 which can be produced directly on the wing 22.
  • the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 comprise an inclinometer 29 integral with the enveloping structure 26.
  • the inclinometer 29 can replace the index 30 and the graduated sector 31, integral with the enveloping structure 26.
  • the inclinometer 29 is oriented so as to measure an angle of rotation of the flag 15 around its axis of rotation ⁇ s .
  • the device comprises means for immobilizing the enveloping structure 26 relative to the support 20.
  • These means can use the index 30 which is locked in position relative to the graduated sector 31.
  • These immobilizing means make it possible to immobilize the enveloping structure 26 relative to the support 20 after having oriented the flag 15 so that the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 indicates a characterization angle of the probe, and before adjusting the angle of rotation sensor so that it indicates a null value.
  • the angle of the enveloping structure 26 relative to the probe body 11 is an angle of rotation of the flag 15 measured in a plane containing the axis ⁇ s.
  • an inclinometer integral with the enveloping structure 26, is oriented so as to measure the angle of the enveloping structure 26 relative to the probe body 11 in a plane o containing the axis of rotation ⁇ s.
  • the inclinometer oriented in this way, bears the reference 35.
  • This orientation of the inclinometer 35 makes it possible to measure the angle between the axis of rotation ⁇ s and the plane of symmetry of the flag 15.
  • the inclinometer 35 allows to check if the flag 15 has been twisted when using the incidence sensor compared to its original position.
  • the fact of using the enveloping structure 26 as a mechanical reference in the angle measurement carried out by the device makes it possible, by placing the inclinometer 35 as shown in FIG. 2, to verify a possible deformation of the flag 15 relative to the '' base 14.
  • An aircraft incidence probe characterization device, 0 is similar to an on-site control device for the same incidence probe 10.
  • the characterization device comprises an enveloping structure intended to receive the flag and the structure enveloping forms a mechanical reference in determining the angles of characterization of the probe. 5 It is possible to use the same inclinometer to perform the angle measurement perpendicular to the axis ⁇ s and the angle measurement in a plane containing the axis ⁇ s. Nevertheless, commercial inclinometers have a relatively low purchase cost. To avoid modifying the orientation of a single inclinometer, it is advantageous to mount, integral with the enveloping structure 26, two inclinometers 29 and 35, the first 29 with the orientation shown in FIG. 1 and the second 35 with the orientation shown in Figure 2.
  • the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 comprise two inclinometers 29 and 35 integral with the enveloping structure 26.
  • the first inclinometer 29 makes it possible to measure an angle of rotation of the flag 15 around its axis of rotation ⁇ s and the second inclinometer 35 makes it possible to measure an angle of rotation of the flag 15 measured in a plane containing the axis ⁇ s.
  • Their respective position relative to the enveloping structure 26 is then fixed, which simplifies the use of the control device.
  • the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 then comprise one or two inclinometers 36 and 32 secured to the support 20.
  • the angle of rotation of the flag 15 around its axis of rotation s is obtained by difference between the measurement carried out by the first inclinometer 29 secured to the enveloping structure 26 and the first inclinometer 31 secured to the support 20.
  • the angle of rotation of the flag 15 measured in a plane containing the axis ⁇ s is obtained by difference between the measurement carried out by the second inclinometer 35 secured to the enveloping structure 26 and the second inclinometer 32 secured to the support 20.

Abstract

The invention relates to an in-situ control system, a characterisation device and a method for control of a moving angle of attack probe, for example, mounted on the skin of an aircraft. The probe comprises a moving vane (15), rotating about an axis (Δs) with relation to a probe body (11). The in-situ control device and the characterisation device comprise an enveloping structure (26), for housing the vane (15). The enveloping structure (26) forms the same mechanical reference for the two devices in the determination of the angle of rotation about the axis (Δs). The method uses the in-situ control device to control the probe as a function of the characterisation angle thereof.

Description

Dispositif de contrôle sur site, dispositif de caractérisation et procédé de contrôle d'une sonde d'incidence On-site control device, characterization device and method for controlling an incidence probe
L'invention se rapporte à un dispositif de contrôle sur site, à un dispositif de caractérisation et à un procédé de contrôle d'une sonde d'incidence mobile par exemple montée sur la peau d'un aéronef. On pourra généraliser le terme « sonde d'incidence » pour tout organe mobile permettant de mesurer l'incidence de l'air par rapport à la peau de l'aéronef, comme par exemple une sonde multifonction mobile comportant, outre la détermination de l'incidence, des prises de pression permettant par exemple de déterminer la pression totale et la pression statique de l'air entourant l'aéronef. Une sonde d'incidence est un dispositif de mesure de l'orientation du vent. L'invention trouve plus particulièrement son application dans l'industrie aéronautique, où le réglage d'une sonde d'incidence a une importance vitale. En effet, la valeur de la mesure de l'orientation du vent apparent d'un aéronef permet d'obtenir, après calcul, la valeur des paramètres d'incidence et de portance. Ces deux paramètres doivent être connus de manière fiable car ils permettent d'assurer des conditions optimales de vol, mais surtout ce sont des paramètres critiques pour la sécurité du vol. Les dispositifs et le procédé de l'invention peuvent néanmoins être utilisés dans d'autres domaines, en particulier en météorologie. Des girouettes installées sur les stations météorologiques s'apparentent aux sondes d'incidence et doivent également être régulièrement réglées, voire changées.The invention relates to an on-site control device, a characterization device and a method for controlling a mobile incidence probe, for example mounted on the skin of an aircraft. We can generalize the term "incidence probe" for any mobile device making it possible to measure the incidence of air relative to the skin of the aircraft, such as for example a mobile multifunction probe comprising, in addition to determining the incidence, pressure taps for example to determine the total pressure and the static pressure of the air surrounding the aircraft. An incidence sensor is a device for measuring the orientation of the wind. The invention finds more particularly its application in the aeronautical industry, where the adjustment of an incidence probe is of vital importance. In fact, the value of the measurement of the orientation of the apparent wind of an aircraft makes it possible to obtain, after calculation, the value of the incidence and lift parameters. These two parameters must be known reliably because they ensure optimal flight conditions, but above all they are critical parameters for flight safety. The devices and method of the invention can nevertheless be used in other fields, in particular in meteorology. Weather vanes installed on weather stations are similar to incidence sensors and must also be regularly adjusted or even changed.
Une sonde d'incidence est un organe, dont une partie est située à l'extérieur de l'aéronef. Cette partie externe est soumise à des variations climatiques, notamment à des variations de température. De plus, elle peut être abîmée par des chocs avec des corps externes, tels que des oiseaux, des grains de sable ou des particules de glace. Plus généralement, elle peut être usée par des forces externes qui peuvent fui être appliquées. Les conditions extérieures à un aéronef sont très rudes. La partie de la sonde d'incidence directement sensible au vent est fragile. Des forces appliquées sur ce dispositif en phase de vol sont très fortes. Ces forces peuvent en outre modifier le réglage de la partie sensible au vent par rapport à des capteurs d'orientation auxquels elle est reliée. Pour des raisons économiques, lorsque la sonde d'incidence doit être remplacée, seule une partie limitée de celle ci est remplacée. Une sonde d'incidence comporte ainsi une girouette mobile au vent, un support de capteurs et un corps de sonde. Quelques fois, seul la girouette est changée. La fixation d'une nouvelle girouette, sur un support de capteurs et sur un corps de sonde déjà en place, ou la fixation d'une nouvelle girouette et d'un support de capteur sur un corps de sonde déjà en place doit alors être entreprise. Il y a dans ce cas une nécessité de réglage sur site des capteurs d'orientation par rapport au corps de sonde, en fonction de la nouvelle sonde d'incidence ainsi constituée.An incidence sensor is an organ, part of which is located outside the aircraft. This external part is subject to climatic variations, in particular to temperature variations. In addition, it can be damaged by impacts with external bodies, such as birds, grains of sand or particles of ice. More generally, it can be worn by external forces which can be applied. The conditions outside an aircraft are very harsh. The part of the incidence sensor directly sensitive to wind is fragile. Forces applied to this device in flight are very strong. These forces can further modify the setting of the wind sensitive part with respect to the orientation sensors to which it is connected. For economic reasons, when the incidence probe needs to be replaced, only a limited part of it is replaced. An incidence probe thus comprises a wind vane which is movable in the wind, a sensor support and a probe body. Sometimes, only the weather vane is changed. The fixing of a new wind vane, on a sensor support and on a probe body already in place, or the fixing of a new wind vane and a sensor support on a probe body already in place must then be undertaken . In this case, there is a need for on-site adjustment of the orientation sensors relative to the probe body, according to the new incidence probe thus formed.
Par ailleurs, les compagnies aériennes imposent une vérification fréquente des réglages des sondes d'incidence. Ces vérifications peuvent parfois aboutir à l'observation de dérives, et donc conduire à un nouveau réglage de la sonde d'incidence II apparaît donc nécessaire de mettre en œuvre une méthode de réglage de la sonde d'incidence fiable et bon marché.In addition, airlines require frequent verification of the settings of the incidence sensors. These verifications can sometimes lead to the observation of drifts, and therefore lead to a new adjustment of the incidence probe. It therefore appears necessary to implement a method of adjustment of the reliable and inexpensive incidence probe.
La méthode de réglage la plus précise nécessite de régler la girouette au moyen d'un passage en soufflerie. En effet, la soufflerie permet de créer un vent d'orientation parfaitement connue. Une sonde d'incidence complète est alors directement réglée en fonction de l'orientation du vent fourni par la soufflerie. Dans ces conditions une sonde d'incidence complète placée sur l'aéronef est parfaitement réglée. Le réglage est réalisé en fixant la girouette dans une position connue par rapport au corps de sonde, et en réglant mécaniquement la position du support de capteurs par rapport à ce corps de sonde, pour qu'un signal délivré par les capteurs dans la position connue de la girouette vaille une valeur attendue.The most precise adjustment method requires adjusting the wind vane using a wind tunnel. Indeed, the wind tunnel creates a perfectly known orientation wind. A complete incidence sensor is then directly adjusted according to the orientation of the wind supplied by the wind tunnel. Under these conditions, a complete incidence probe placed on the aircraft is perfectly adjusted. The adjustment is carried out by fixing the wind vane in a known position relative to the probe body, and by mechanically adjusting the position of the sensor support relative to this probe body, so that a signal delivered by the sensors in the known position of the weather vane is worth an expected value.
Dans l'état de la technique, le placement de la girouette dans une position connue par rapport au corps de sonde nécessite l'existence et l'identification matérielle sur la girouette, d'un repérage correspondant à un zéro aérodynamique. Le zéro aérodynamique est observé en soufflerie. Il correspond à une orientation de la girouette dans l'axe du vent de la soufflerie, et à une position correspondante du support de capteurs, qui dans ce cas donne un signal de mesure attendu (en général un signal nul). Pour ce zéro aérodynamique, on repère en définitive les positions relatives de la girouette par rapport au support de capteurs. Dans la pratique ce repérage est obtenu en repérant la girouette par rapport au corps de sonde, et en repérant également le support de capteurs par rapport au corps de sonde. Le zéro aérodynamique est identifié par exemple par un trou, réalisé en usine, sur la girouette. Le principe de réglage, dans l'état de la technique est de figer le trou représentant le zéro aérodynamique dans une position connue par rapport au corps de sonde, et de placer le capteur d'orientation, par rapport à cet ensemble figé, dans une position telle que le signal de mesure délivré soit le signal de mesure attendu (en général le signal nul). L'opération de détermination du zéro aérodynamique réalisée en soufflerie est appelée caractérisation de la sonde d'incidence.In the prior art, the placement of the wind vane in a known position relative to the probe body requires the existence and the physical identification on the wind vane, of a marking corresponding to an aerodynamic zero. Aerodynamic zero is observed in the wind tunnel. It corresponds to an orientation of the wind vane in the wind axis of the wind tunnel, and to a corresponding position of the sensor support, which in this case gives an expected measurement signal (generally a zero signal). For this aerodynamic zero, the relative positions of the wind vane with respect to the sensor support are finally identified. In practice this location is obtained by locating the wind vane relative to the probe body, and also locating the sensor support relative to the probe body. Aerodynamic zero is identified for example by a hole, made in the factory, on the wind vane. The adjustment principle, in the prior art, is to fix the hole representing the aerodynamic zero in a known position relative to the probe body, and to place the orientation sensor, relative to this fixed assembly, in a position such that the measurement signal delivered is the expected measurement signal (generally the zero signal). The aerodynamic zero determination operation carried out in a wind tunnel is called characterization of the incidence probe.
La figure 1 , placée en fin de la présente description, illustre schématiquement la structure générale d'une sonde d'incidence 10.FIG. 1, placed at the end of this description, schematically illustrates the general structure of an incidence probe 10.
La sonde d'incidence 10 comprend un corps de sonde 11 constitué par un boîtier, généralement cylindrique, fermé sur sa partie supérieure par une plaque 12, avantageusement circulaire. Une girouette 13 comprend une embase 14, de faible épaisseur et mobile autour d'un axe Δs, que l'on appelle également axe de sonde. La girouette 13 comprend aussi un drapeau 15 surmontant l'embase 14. Le drapeau 15 est destiné à s'orienter dans le vent entourant la sonde d'incidence 10.The incidence probe 10 comprises a probe body 11 constituted by a housing, generally cylindrical, closed on its upper part by a plate 12, advantageously circular. A wind vane 13 comprises a base 14, of small thickness and movable around an axis Δs, which is also called probe axis. The wind vane 13 also includes a flag 15 surmounting the base 14. The flag 15 is intended to orient itself in the wind surrounding the incidence probe 10.
La forme et le profil de la section de ce drapeau 15 sont déterminés par l'application finale de la sonde, c'est-à-dire essentiellement le type d'aéronef auquel elle est destinée, le degré de précision des mesures d'angle à obtenir et un certain nombre de paramètres physiques décrivant les conditions d'environnement auxquelles est soumise la sonde d'incidence : vitesse maximale atteinte par l'aéronef, donc également de l'air s'écoulant le long des parois de la carlingue, variations maximales de températures, etc. ces considérations sortent du cadre précis de l'invention. En effet, le dispositif de positionnement objet de l'invention, et c'est un des avantages de celui-ci, reste compatible avec tous types de sondes à drapeau de l'art connu et ne nécessite aucune modification, ni structurelles, ni fonctionnelles.The shape and profile of the section of this flag 15 are determined by the final application of the probe, that is to say essentially the type of aircraft for which it is intended, the degree of precision of the angle measurements. to obtain and a certain number of physical parameters describing the environmental conditions to which the incidence probe is subjected: maximum speed reached by the aircraft, therefore also air flowing along the walls of the cabin, variations maximum temperatures, etc. these considerations go beyond the precise scope of the invention. Indeed, the positioning device object of the invention, and this is one of the advantages of it, remains compatible with all types of flag probes of the known art and does not require any modification, either structural or functional. .
Le boîtier renferme notamment un capteur d'angle de rotation de la girouette 13, et plus précisément du drapeau 15, autour de l'axe Δs par rapport au corps de sonde 11. Ce dernier peut faire appel à une mesure basée sur l'utilisation d'un potentiomètre dont l'axe est entraîné par la rotation du drapeau 15, d'un capteur du type dit "resolver" ou de tout autre capteur de l'art connu approprié à ce domaine d'application. L'amplitude de la rotation de la girouette 13 autour de l'axe Δs est convertie en signaux électriques, transmis par des liaisons 16 à un appareil de traitement de signal (non représenté) situé à l'intérieur de l'aéronef, généralement dans le cockpit, pour y être finalement affichés sur un instrument de bord sous une forme appropriée, selon les paramètres mesurés.The housing contains in particular a rotation angle sensor of the wind vane 13, and more precisely of the flag 15, around the axis Δs relative to the probe body 11. The latter may call for a measurement based on use a potentiometer whose axis is driven by the rotation of the flag 15, of a sensor of the so-called "resolver" type or of any other sensor of the known art suitable for this field of application. The amplitude of the rotation of the vane 13 around the axis Δs is converted into electrical signals, transmitted by links 16 to a signal processing device (not shown) located inside the aircraft, generally in the cockpit, to be finally displayed on an on-board instrument in an appropriate form, according to the parameters measured.
Le corps de sonde 11 est disposé dans un orifice (non représenté) prévu à cet effet dans la carlingue de l'aéronef et recouvert d'un cache (non représenté) de manière à ce que ce qui est appelé la "peau" de l'aéronef, référencée PA, affleure à la surface supérieure de l'embase 14 de la girouette 13. Il est en effet nécessaire que, à l'exception de l'excroissance formée par le drapeau 15, ne subsiste aucune aspérité qui perturberait l'écoulement des filets d'air à l'extérieur de la peau PA. La sonde d'incidence 10 comprend des moyens de positionnement par rapport à la peau PA de l'aéronef. Les moyens de positionnement comportent par exemple deux ergots 17 et 18 destinés à pénétrer dans des trous correspondants ménagés dans la peau PA. Par les ergots 17 et 18 passe une droite Δv concourante de l'axe Δs. On comprend aisément que, lors des opérations périodiques d'entretien et de vérification de routine, les compagnies aériennes souhaitent que l'on puisse tester le bon fonctionnement et certifier l'exactitude des signaux de mesure fournis par les sondes d'incidence, si possible sans avoir à les déposer, c'est-à-dire les démonter, les extraire de leur logement, puis les remonter après test, ce qui se traduirait par des opérations longues et coûteuses. En outre, il doit être rappelé, d'une part, que la précision des mesures requise est très grande : typiquement quelques dixièmes de degrés, et que d'autre part, les conditions d'environnement auxquelles sont soumises les sondes d'incidences sont extrêmes. En cas de nécessité de dépose de la sonde d'incidence, il est souhaitable d'éviter le recours à une soufflerie pour tester ou régler la sonde d'incidence en utilisant autant que possible un banc de calage de site. Le banc de calage de site est utilisé au pied de l'aéronef, c'est à dire après démontage de la sonde d'incidence de l'aéronef.The probe body 11 is arranged in an orifice (not shown) provided for this purpose in the cabin of the aircraft and covered with a cover (not shown) so that what is called the "skin" of the 'aircraft, referenced PA, is flush with the upper surface of the base 14 of the wind vane 13. It is indeed necessary that, with the exception of the protrusion formed by the flag 15, no roughness remains which would disturb the flow of air streams outside the PA skin. The incidence probe 10 comprises means for positioning relative to the skin PA of the aircraft. The positioning means comprise for example two lugs 17 and 18 intended to penetrate into corresponding holes made in the skin PA. Through lugs 17 and 18 passes a straight line Δv concurrent with the axis Δs. It is easy to understand that during periodic maintenance and routine verification operations, the airlines want us to be able to test the correct operation and certify the accuracy of the measurement signals supplied by the incidence probes, if possible. without having to remove them, that is to say disassemble them, extract them from their housing, then reassemble them after testing, which would result in long and costly operations. In addition, it should be recalled, on the one hand, that the precision of the measurements required is very high: typically a few tenths of degrees, and that on the other hand, the environmental conditions to which the impact probes are subjected are extremes. If it is necessary to remove the incidence probe, it is desirable to avoid the use of a blower to test or adjust the incidence probe using as much as possible a site bench. The site rigging bench is used at the foot of the aircraft, that is to say after dismantling the aircraft's incidence probe.
Dans la demande de brevet déposée sous le numéro FR 98 16353, on décrit un banc de calage usine d'une sonde d'incidence comportant une girouette. Ce banc utilise une référence mécanique ponctuelle contre laquelle s'appuie le drapeau mobile de la sonde. Le banc de calage usine permet de réaliser la caractérisation de la sonde d'incidence. Plus précisément, le banc de calage usine permet de déterminer un écart entre d'orientation angulaire du drapeau mobile entre une première position où il est en appui contre la référence mécanique ponctuelle et une seconde position où il s'oriente librement par rapport à un vent de direction connu obtenu par soufflerie.In the patent application filed under the number FR 98 16353, a factory setting bench for an incidence probe is described. with a weather vane. This bench uses a point mechanical reference against which the mobile flag of the probe rests. The factory setting bench allows the characterization of the incidence probe. More precisely, the factory setting bench makes it possible to determine a difference between the angular orientation of the mobile flag between a first position where it is in abutment against the point mechanical reference and a second position where it is oriented freely relative to a wind. known direction obtained by wind tunnel.
La demande de brevet déposée sous le numéro FR 98 16353 décrit également un banc de calage de site identique au banc de calage usine et permettant de régler la position du capteur d'orientation de la girouette en fonction de l'écart angulaire défini lors de la caractérisation.The patent application filed under the number FR 98 16353 also describes a site setting bench identical to the factory setting bench and making it possible to adjust the position of the orientation sensor of the wind vane as a function of the angular deviation defined during the characterization.
Par ailleurs, dans la demande de brevet déposée sous le numéro FR 99 16773, on décrit un dispositif de positionnement in situ angulaire d'une sonde d'incidence comportant une girouette. Ce dispositif comporte une structure enveloppante destinée à recevoir le drapeau mobile de la girouette. Le dispositif de positionnement in situ est utilisé lorsque la sonde d'incidence est montée sur la peau PA de l'aéronef. Le dispositif de positionnement in situ permet de contrôler la linéarité du capteur d'orientation et permet d'obtenir une précision de l'ordre du degré dans le réglage du zéro du capteur. Une meilleure précision ne peut être obtenue car la référence mécanique du dispositif de positionnement in situ est différente de la référence mécanique du banc de calage de site ou du banc de calage usine.Furthermore, in the patent application filed under the number FR 99 16773, there is described a device for angular in situ positioning of an incidence probe comprising a wind vane. This device comprises an enveloping structure intended to receive the mobile flag of the wind vane. The in situ positioning device is used when the incidence probe is mounted on the skin PA of the aircraft. The in situ positioning device makes it possible to control the linearity of the orientation sensor and makes it possible to obtain an accuracy of the order of a degree in the zero adjustment of the sensor. Better precision cannot be obtained because the mechanical reference of the in situ positioning device is different from the mechanical reference of the site setting bench or the factory setting bench.
L'invention permet de résoudre ce problème en utilisant une seule référence mécanique pour les trois opérations décrites plus haut, à savoir la caractérisation en usine, le contrôle de la sonde sur site, au pied de l'aéronef et le réglage angulaire de la sonde montée sur l'aéronef.The invention makes it possible to solve this problem by using a single mechanical reference for the three operations described above, namely the characterization in the factory, the control of the probe on site, at the foot of the aircraft and the angular adjustment of the probe. mounted on the aircraft.
A cet effet l'invention a pour objet un dispositif de contrôle sur site d'une sonde d'incidence, la sonde comportant un corps de sonde, un drapeau mobile en rotation autour d'un axe par rapport au corps de sonde, caractérisé en ce qu'il comporte en outre une structure enveloppante destinée à recevoir le drapeau, le drapeau pouvant être immobilisé de façon temporaire par rapport à la structure enveloppante, et des moyens de mesure d'un angle de la structure enveloppante par rapport au corps de sonde . L'invention a également pour objet un procédé de contrôle sur site d'une sonde d'incidence, la sonde comportant un corps de sonde, un drapeau mobile en rotation autour d'un axe par rapport au corps de sonde et un capteur d'angle de rotation du drapeau par rapport au corps de sonde autour de l'axe, caractérisé en ce que le dispositif comporte en outre une structure enveloppante destinée à recevoir le drapeau, le drapeau pouvant être immobilisé de façon temporaire par rapport à la structure enveloppante, et des moyens de mesure d'un angle de la structure enveloppante par rapport au corps de sonde, et en ce que le procédé consiste à : - immobiliser le corps de sonde par rapport à un support du dispositif,To this end, the subject of the invention is a device for on-site control of an incidence probe, the probe comprising a probe body, a flag movable in rotation about an axis relative to the probe body, characterized in what it further comprises an enveloping structure intended to receive the flag, the flag being able to be immobilized temporarily with respect to the enveloping structure, and means for measuring an angle of the enveloping structure with respect to the probe body . The subject of the invention is also a method of on-site control of an incidence probe, the probe comprising a probe body, a flag which can move in rotation about an axis with respect to the probe body and a sensor for angle of rotation of the flag relative to the probe body around the axis, characterized in that the device further comprises an enveloping structure intended to receive the flag, the flag being able to be immobilized temporarily relative to the enveloping structure, and means for measuring an angle of the enveloping structure relative to the probe body, and in that the method consists in: - immobilizing the probe body relative to a support of the device,
- immobiliser le drapeau dans la structure enveloppante,- immobilize the flag in the enveloping structure,
- orienter le drapeau de façon à ce que (es moyens de mesure d'un angle de la structure enveloppante par rapport au corps de sonde indique un angle de caractérisation de la sonde,- orient the flag so that (the means for measuring an angle of the enveloping structure with respect to the probe body indicates an angle for characterizing the probe,
- régler le capteur d'angle de rotation pour qu'il indique une valeur nulle.- set the angle of rotation sensor so that it indicates a zero value.
L'invention a encore pour objet un dispositif de caractérisation d'une sonde d'incidence, la sonde comportant un drapeau mobile en rotation autour d'un axe, caractérisé en ce que le dispositif comporte une structure enveloppante destinée à recevoir le drapeau, et en ce que la structure enveloppante forme une référence mécanique dans la détermination d'un angle de caractérisation de la sonde.The subject of the invention is also a device for characterizing an incidence probe, the probe comprising a flag which is mobile in rotation about an axis, characterized in that the device comprises an enveloping structure intended to receive the flag, and in that the enveloping structure forms a mechanical reference in determining a characterization angle of the probe.
L'invention sera mieux comprise et d'autres avantages apparaîtront à la lecture de la description détaillée d'un mode de réalisation donné à titre d'exemple et illustré par le dessin joint dans lequel :The invention will be better understood and other advantages will appear on reading the detailed description of an embodiment given by way of example and illustrated by the attached drawing in which:
- la figure 1 représente un exemple de réalisation d'une sonde d'incidence pour aéronef du type comportant une girouette mobile autour d'un axe ; la figure 1 a été décrite précédemment pour présenter l'invention ;- Figure 1 shows an exemplary embodiment of an incidence probe for aircraft of the type comprising a wind vane movable around an axis; Figure 1 has been described above to present the invention;
- la figure 2 représente un dispositif de caractérisation ou dispositif de contrôle sur site d'une sonde d'incidence comportant un inclinomètre orienté perpendiculairement à l'axe de rotation de la girouette ;- Figure 2 shows a characterization device or on-site control device for an incidence probe comprising an inclinometer oriented perpendicular to the axis of rotation of the wind vane;
- la figure 3 représente le dispositif de la figure 2 dans lequel Pinclinomètre est orienté parallèlement à l'axe de rotation de la girouette. Pour une meilleure compréhension, les mêmes éléments porteront les mêmes repères dans les différentes figures.- Figure 3 shows the device of Figure 2 in which the inclinometer is oriented parallel to the axis of rotation of the vane. For a better understanding, the same elements will bear the same references in the different figures.
Sur la figure 2 sont représentés les éléments communs d'un dispositif de caractérisation et d'un dispositif de contrôle sur site d'une sonde d'incidence. Le dispositif de caractérisation est utilisé en soufflerie et comporte des moyens pour se positionner dans la soufflerie. Ces moyens ne sont pas représentés sur fa figure 2. Le dispositif de contrôle sur site est utilisé au pied de l'aéronef. Plus précisément, lorsqu'une sonde d'incidence doit être contrôlée, elle est démontée de l'aéronef puis placée temporairement sur le dispositif de contrôle sur site situé à proximité de l'aéronef. Le dispositif de contrôle sur site permet le contrôle et le réglage de la sonde d'incidence sans nécessiter le recours à une soufflerie.In Figure 2 are shown the common elements of a characterization device and an on-site control device of an incidence probe. The characterization device is used in the wind tunnel and includes means for positioning in the wind tunnel. These means are not shown in FIG. 2. The on-site control device is used at the foot of the aircraft. More specifically, when an incidence probe must be controlled, it is removed from the aircraft and then temporarily placed on the on-site control device located near the aircraft. The on-site control device allows the control and adjustment of the angle of attack sensor without requiring the use of a blower.
Le dispositif représenté figure 2 comporte un support 20 ayant la forme d'une équerre. Le support 20 a une rigidité importante pour ne pas se déformer lors des différentes opérations nécessaires au contrôle de la sonde. Le support 20 comporte une première aile 21 horizontale et une seconde aile 22 verticale. Le dispositif peut comporter des vis de réglage 23 et 24 ainsi qu'un niveau à bulle 25 afin de régler, lors du montage de la sonde d'incidence sur le support 20, la verticalité de la droite Δv définie à l'aide de la figure 1.The device shown in Figure 2 comprises a support 20 having the shape of a square. The support 20 has a high rigidity so as not to deform during the various operations necessary for checking the probe. The support 20 comprises a first horizontal wing 21 and a second vertical wing 22. The device may include adjustment screws 23 and 24 as well as a spirit level 25 in order to adjust, during the mounting of the incidence probe on the support 20, the verticality of the straight line Δv defined using the figure 1.
La seconde aile 22 comprend des moyens pour immobiliser le corps de sonde 11 sur l'aile 22 de façon à ce que l'axe de sonde Δs soit dans une position horizontale. Ces moyens comportent par exemple un orifice circulaire percé dans l'aile 22 et semblable à celui réalisé dans la peau PA de l'aéronef ainsi que des moyens de fixation du corps de sonde 11 sur l'aile 22. Les moyens pour immobiliser le corps de sonde 11 sur l'aile 22 comportent en outre des trous destinés à recevoir les ergots 17 et 18. Ces trous sont semblables à ceux réalisés dans la peau PA de l'aéronef pour positionner la sonde d'incidence lorsque celle ci est montée sur l'aéronef.The second wing 22 comprises means for immobilizing the probe body 11 on the wing 22 so that the probe axis Δ s is in a horizontal position. These means comprise for example a circular orifice pierced in the wing 22 and similar to that produced in the skin PA of the aircraft as well as means for fixing the probe body 11 on the wing 22. The means for immobilizing the body probe 11 on the wing 22 also have holes intended to receive the pins 17 and 18. These holes are similar to those made in the skin PA of the aircraft for positioning the incidence probe when the latter is mounted on the aircraft.
Le dispositif comporte en outre une structure enveloppante 26 destinée à recevoir le drapeau 15 de la sonde d'incidence 10. La structure enveloppante 26 comporte par exemple deux demi-coquilles 27 et 28 entre lesquelles le drapeau 15 est immobilisé de façon temporaire. D'autres δThe device further comprises an enveloping structure 26 intended to receive the flag 15 of the incidence probe 10. The enveloping structure 26 comprises for example two half-shells 27 and 28 between which the flag 15 is temporarily immobilized. other δ
exemples de réalisation d'une structure enveloppante sont décrits dans la demande de brevet déposée sous le numéro FR 99 16773.exemplary embodiments of an enveloping structure are described in the patent application filed under the number FR 99 16773.
Le dispositif comporte des moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11. Sur la figure 2, l'angle de la structure enveloppante 26 par rapport au corps de sonde 11 est un angle de rotation du drapeau 15 autour de son axe de rotation Δs.The device comprises means for measuring an angle of the enveloping structure 26 relative to the probe body 11. In FIG. 2, the angle of the enveloping structure 26 relative to the probe body 11 is an angle of rotation of the flag 15 around its axis of rotation Δs.
Les moyens de mesure peuvent comporter un index 30 solidaire de la structure enveloppante 26 et un secteur angulaire gradué 31 solidaire du support 20. L'index 30 se déplace en rotation autour de l'axe Δs avec la structure enveloppante 26 et permet par conséquent de visualiser la position angulaire du drapeau 15 autour de son axe de rotation Δs. L'index 30 se déplace devant le secteur angulaire gradué 31 qui peut être réalisé directement sur l'aile 22.The measuring means may comprise an index 30 secured to the enveloping structure 26 and a graduated angular sector 31 secured to the support 20. The index 30 moves in rotation around the axis Δs with the enveloping structure 26 and consequently makes it possible to display the angular position of the flag 15 around its axis of rotation Δs. The index 30 moves in front of the graduated angular sector 31 which can be produced directly on the wing 22.
Avantageusement, les moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11 comportent un inclinomètre 29 solidaire de ia structure enveloppante 26. L'inclinomètre 29, peut remplacer l'index 30 et le secteur gradué 31, solidaire de la structure enveloppante 26. Sur la figure 2, l'inclinomètre 29 est orienté de façon à mesurer un angle de rotation du drapeau 15 autour de son axe de rotation Δs.Advantageously, the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 comprise an inclinometer 29 integral with the enveloping structure 26. The inclinometer 29 can replace the index 30 and the graduated sector 31, integral with the enveloping structure 26. In FIG. 2, the inclinometer 29 is oriented so as to measure an angle of rotation of the flag 15 around its axis of rotation Δ s .
Lors du contrôle sur site d'une sonde d'incidence 10 on procède de la façon suivante :During the on-site inspection of an incidence probe 10, the procedure is as follows:
- immobiliser le corps de sonde 11 par rapport à un support 20 du dispositif, - immobiliser le drapeau 15 dans la structure enveloppante 26,immobilize the probe body 11 relative to a support 20 of the device, immobilize the flag 15 in the enveloping structure 26,
- orienter le drapeau 15 de façon à ce que les moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11 indique un angle de caractérisation de la sonde,orient the flag 15 so that the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 indicates a characterization angle of the probe,
- régler le capteur d'angle de rotation pour qu'il indique une valeur nulle.- set the angle of rotation sensor so that it indicates a zero value.
Avantageusement, le dispositif comporte des moyens d'immobilisation de la structure enveloppante 26 par rapport au support 20.Advantageously, the device comprises means for immobilizing the enveloping structure 26 relative to the support 20.
Ces moyens peuvent utiliser l'index 30 que l'on verrouille en position par rapport au secteur gradué 31. Ces moyens d'immobilisation permettent d'immobiliser la structure enveloppante 26 par rapport au support 20 après avoir orienté le drapeau 15 de façon à ce que les moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11 indique un angle de caractérisation de fa sonde, et avant de régler le capteur d'angle de rotation pour qu'il indique une valeur nulle. 5 Sur la figure 3, l'angle de la structure enveloppante 26 par rapport au corps de sonde 11 est un angle de rotation du drapeau 15 mesuré dans un pian contenant l'axe Δs. Plus précisément, un inclinomètre, solidaire de la structure enveloppante 26, est orienté de façon à mesurer l'angle de la structure enveloppante 26 par rapport au corps de sonde 11 dans un plan o contenant l'axe de rotation Δs. L'inclinomètre, orienté de cette façon, porte le repère 35. Cette orientation de l'inclinomètre 35 permet de mesurer l'angle entre l'axe de rotation Δs et le plan de symétrie du drapeau 15. Autrement dit l'inclinomètre 35 permet de vérifier si le drapeau 15 a été tordu lors de l'utilisation de la sonde d'incidence par rapport à sa position d'origine. Le fait 5 d'utiliser la structure enveloppante 26 comme référence mécanique dans la mesure d'angle réalisée par le dispositif permet, en plaçant l'inclinomètre 35 comme représenté sur la figure 2, de vérifier une éventuelle déformation du drapeau 15 par rapport à l'embase 14.These means can use the index 30 which is locked in position relative to the graduated sector 31. These immobilizing means make it possible to immobilize the enveloping structure 26 relative to the support 20 after having oriented the flag 15 so that the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 indicates a characterization angle of the probe, and before adjusting the angle of rotation sensor so that it indicates a null value. In FIG. 3, the angle of the enveloping structure 26 relative to the probe body 11 is an angle of rotation of the flag 15 measured in a plane containing the axis Δs. More specifically, an inclinometer, integral with the enveloping structure 26, is oriented so as to measure the angle of the enveloping structure 26 relative to the probe body 11 in a plane o containing the axis of rotation Δs. The inclinometer, oriented in this way, bears the reference 35. This orientation of the inclinometer 35 makes it possible to measure the angle between the axis of rotation Δs and the plane of symmetry of the flag 15. In other words the inclinometer 35 allows to check if the flag 15 has been twisted when using the incidence sensor compared to its original position. The fact of using the enveloping structure 26 as a mechanical reference in the angle measurement carried out by the device makes it possible, by placing the inclinometer 35 as shown in FIG. 2, to verify a possible deformation of the flag 15 relative to the '' base 14.
Un dispositif de caractérisation d'une sonde d'incidence d'aéronef, 0 est semblable à un dispositif de contrôle sur site de la même sonde d'incidence 10. Le dispositif de caractérisation comporte une structure enveloppante destinée à recevoir le drapeau et la structure enveloppante forme une référence mécanique dans la détermination des angles de caractérisation de la sonde. 5 II est possible d'utiliser le même inclinomètre pour effectuer la mesure d'angle perpendiculairement à l'axe Δs et la mesure d'angle dans un plan contenant l'axe Δs. Néanmoins, les inclinomètres du commerce ont un coût d'achat relativement faible. Pour éviter de modifier l'orientation d'un seul inclinomètre, il est avantageux de monter, solidaire de la structure 0 enveloppante 26, deux inclinomètres 29 et 35, le premier 29 avec l'orientation représenté sur ia figure 1 et le second 35 avec l'orientation représenté sur la figure 2.An aircraft incidence probe characterization device, 0 is similar to an on-site control device for the same incidence probe 10. The characterization device comprises an enveloping structure intended to receive the flag and the structure enveloping forms a mechanical reference in determining the angles of characterization of the probe. 5 It is possible to use the same inclinometer to perform the angle measurement perpendicular to the axis Δ s and the angle measurement in a plane containing the axis Δs. Nevertheless, commercial inclinometers have a relatively low purchase cost. To avoid modifying the orientation of a single inclinometer, it is advantageous to mount, integral with the enveloping structure 26, two inclinometers 29 and 35, the first 29 with the orientation shown in FIG. 1 and the second 35 with the orientation shown in Figure 2.
Autrement dit, les moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11 comportent deux 5 inclinomètres 29 et 35 solidaires de la structure enveloppante 26. Le premier inclinomètre 29 permet de mesurer un angle de rotation du drapeau 15 autour de son axe de rotation Δs et le second inclinomètre 35 permet de mesurer un angle de rotation du drapeau 15 mesuré dans un plan contenant l'axe Δs. Leur position respective par rapport à la structure enveloppante 26 est alors fixe ce qui simplifie l'utilisation du dispositif de contrôle.In other words, the means for measuring an angle of the enveloping structure 26 relative to the probe body 11 comprise two inclinometers 29 and 35 integral with the enveloping structure 26. The first inclinometer 29 makes it possible to measure an angle of rotation of the flag 15 around its axis of rotation Δs and the second inclinometer 35 makes it possible to measure an angle of rotation of the flag 15 measured in a plane containing the axis Δs. Their respective position relative to the enveloping structure 26 is then fixed, which simplifies the use of the control device.
Lorsqu'on envisage d'utiliser le dispositif de contrôle à bord d'un porte-avions pour régler les sondes d'incidences d'aéronefs qui y sont embarqués, le support 20 est susceptible de bouger au rythme du porte- avions et le ou les inclinomètres 29 et 35 ne donneront pas de mesures stables. Pour palier ce problème, on dispose avantageusement sur le dispositif un ou deux inclinomètres supplémentaires. Les moyens de mesure d'un angle de la structure enveloppante 26 par rapport au corps de sonde 11 comportent alors un ou deux inclinomètres 36 et 32 solidaires du support 20. L'angle de rotation du drapeau 15 autour de son axe de rotation s est obtenu par différence entre la mesure réalisée par le premier inclinomètre 29 solidaire de la structure enveloppante 26 et le premier inclinomètre 31 solidaire du support 20. L'angle de rotation du drapeau 15 mesuré dans un plan contenant l'axe Δs est obtenu par différence entre la mesure réalisée par le second inclinomètre 35 solidaire de la structure enveloppante 26 et le second inclinomètre 32 solidaire du support 20.When considering using the control device on board an aircraft carrier to adjust the aircraft incidence probes on board, the support 20 is liable to move at the rate of the aircraft carrier and the inclinometers 29 and 35 will not give stable measurements. To overcome this problem, there are advantageously one or two additional inclinometers on the device. The means for measuring an angle of the enveloping structure 26 relative to the probe body 11 then comprise one or two inclinometers 36 and 32 secured to the support 20. The angle of rotation of the flag 15 around its axis of rotation s is obtained by difference between the measurement carried out by the first inclinometer 29 secured to the enveloping structure 26 and the first inclinometer 31 secured to the support 20. The angle of rotation of the flag 15 measured in a plane containing the axis Δs is obtained by difference between the measurement carried out by the second inclinometer 35 secured to the enveloping structure 26 and the second inclinometer 32 secured to the support 20.
Le fait d'utiliser quatre inclinomètres sur le dispositif permet d'éviter le réglage des vis 23 et 24 même lorsque le dispositif est utilisé sur la terre ferme. The fact of using four inclinometers on the device makes it possible to avoid adjusting the screws 23 and 24 even when the device is used on dry land.

Claims

REVENDICATIONS
1. Dispositif de contrôle sur site d'une sonde d'incidence (10), la sonde comportant un corps de sonde (11), un drapeau mobile (15) en rotation autour d'un axe (Δs) par rapport au corps de sonde (11), caractérisé en ce qu'il comporte en outre une structure enveloppante (26) destinée à 5 recevoir le drapeau (15), le drapeau (15) pouvant être immobilisé de façon temporaire par rapport à la structure enveloppante (26), et des moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11).1. An on-site control device for an incidence probe (10), the probe comprising a probe body (11), a mobile flag (15) rotating around an axis (Δs) relative to the body of probe (11), characterized in that it further comprises an enveloping structure (26) intended to receive the flag (15), the flag (15) being able to be immobilized temporarily relative to the enveloping structure (26) , and means for measuring an angle of the enveloping structure (26) relative to the probe body (11).
o 2. Dispositif selon la revendication 1 , caractérisé en ce que l'angle de la structure enveloppante (26) par rapport au corps de sonde (11 ) est un angle de rotation du drapeau (15) autour de son axe de rotation (Δs).o 2. Device according to claim 1, characterized in that the angle of the enveloping structure (26) relative to the probe body (11) is an angle of rotation of the flag (15) about its axis of rotation (Δ s ).
3. Dispositif selon la revendication 1, caractérisé en ce que l'angle 5 de la structure enveloppante (26) par rapport au corps de sonde (11) est un angle de rotation du drapeau (15) mesuré dans un plan contenant l'axe (Δs).3. Device according to claim 1, characterized in that the angle 5 of the enveloping structure (26) relative to the probe body (11) is an angle of rotation of the flag (15) measured in a plane containing the axis (.DELTA.S).
4. Dispositif selon l'une des revendications précédentes, caractérisé en ce que les moyens de mesure d'un angle de ia structure 0 enveloppante (26) par rapport au corps de sonde (11) comportent un index (30) solidaire de la structure enveloppante (26) et un secteur angulaire gradué (31) solidaire d'un support (20) du dispositif.4. Device according to one of the preceding claims, characterized in that the means for measuring an angle of the enveloping structure 0 (26) relative to the probe body (11) comprise an index (30) integral with the structure enveloping (26) and a graduated angular sector (31) integral with a support (20) of the device.
5. Dispositif selon l'une des revendications précédentes, 5 caractérisé en ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11) comportent un inclinomètre (29, 30) solidaire de la structure enveloppante (26).5. Device according to one of the preceding claims, 5 characterized in that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) comprise an inclinometer (29, 30) integral with the enveloping structure (26).
6. Dispositif selon l'une des revendications précédentes, 0 caractérisé en ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11) comportent un inclinomètre (31 , 32) solidaire du support (20). 6. Device according to one of the preceding claims, 0 characterized in that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) comprise an inclinometer (31, 32) integral with the support (20).
7. Dispositif selon l'une quelconque des revendications 5 ou 6, caractérisé en ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11) comportent deux inclinomètres (29, 30) solidaires de la structure enveloppante (26), en ce que 5 le premier inclinomètre (29) permet de mesurer un angle de rotation du drapeau (15) autour de son axe de rotation (Δs) et en ce que le second inclinomètre (30) permet de mesurer un angle de rotation du drapeau (15) mesuré dans un plan contenant l'axe (Δs).7. Device according to any one of claims 5 or 6, characterized in that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) comprise two inclinometers (29, 30) integral with the enveloping structure (26), in that the first inclinometer (29) makes it possible to measure an angle of rotation of the flag (15) around its axis of rotation (Δs) and in that the second inclinometer (30) allows to measure an angle of rotation of the flag (15) measured in a plane containing the axis (Δs).
o 8. Dispositif selon les revendications 6 et 7, caractérisé en ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11) comportent deux inclinomètres (31 , 32) solidaires du support (20), en ce que l'angle de rotation du drapeau (15) autour de son axe de rotation (Δs) est obtenu par différence entre la mesure 5 réalisée par le premier inclinomètre (29) solidaire de la structure enveloppante (26) et le premier inclinomètre (36) solidaire du support (20) et en ce que l'angle de rotation du drapeau (15) mesuré dans un plan contenant l'axe (Δs) est obtenu par différence entre la mesure réalisée par le second inclinomètre (35) solidaire de la structure enveloppante (26) et le second 0 inclinomètre (32) solidaire du support (20).o 8. Device according to claims 6 and 7, characterized in that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) comprise two inclinometers (31, 32) integral with the support (20), in that the angle of rotation of the flag (15) around its axis of rotation (Δs) is obtained by difference between measurement 5 carried out by the first inclinometer (29) integral with the enveloping structure (26) and the first inclinometer (36) integral with the support (20) and in that the angle of rotation of the flag (15) measured in a plane containing the axis (Δs) is obtained by difference between the measurement carried out by the second inclinometer (35) secured to the enveloping structure (26) and the second inclinometer 0 (32) secured to the support (20).
9. Procédé de contrôle sur site d'une sonde d'incidence (10), la sonde comportant un corps de sonde (11), un drapeau (15) mobile en rotation autour d'un axe (Δs) par rapport à un corps de sonde (11) et un 5 capteur d'angle de rotation du drapeau (15) par rapport au corps de sonde (11) autour de l'axe (Δs), caractérisé en ce que le dispositif comporte en outre une structure enveloppante (26) destinée à recevoir le drapeau (15), le drapeau (15) pouvant être immobilisé de façon temporaire par rapport à la structure enveloppante (26), et des moyens de mesure d'un angle de la 0 structure enveloppante (26) par rapport au corps de sonde (11), et en ce que le procédé consiste à :9. Method for on-site control of an incidence probe (10), the probe comprising a probe body (11), a flag (15) movable in rotation about an axis (Δs) relative to a body probe (11) and a sensor for the angle of rotation of the flag (15) relative to the probe body (11) about the axis (Δs), characterized in that the device also comprises an enveloping structure ( 26) intended to receive the flag (15), the flag (15) being able to be immobilized temporarily with respect to the enveloping structure (26), and means for measuring an angle of the enveloping structure (26) by relative to the probe body (11), and in that the method consists in:
- immobiliser le corps de sonde (11) par rapport à un support (20) du dispositif,- immobilize the probe body (11) relative to a support (20) of the device,
- immobiliser le drapeau (15) dans la structure enveloppante (26), - orienter le drapeau (15) de façon à ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11 ) indique un angle de caractérisation de la sonde,- immobilize the flag (15) in the enveloping structure (26), - orient the flag (15) so that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) indicates an angle of characterization of the probe,
- régler le capteur d'angle de rotation pour qu'il indique une valeur 5 nulle.- set the angle of rotation sensor so that it indicates a zero value of 5.
10. Procédé selon la revendication 9, caractérisé en ce qu'après avoir orienté le drapeau (15) de façon à ce que les moyens de mesure d'un angle de la structure enveloppante (26) par rapport au corps de sonde (11) o indique un angle de caractérisation de la sonde, et avant de régler le capteur d'angle de rotation pour qu'il indique une valeur nulle, le procédé consiste à immobiliser la structure enveloppante (26) par rapport au support (20).10. Method according to claim 9, characterized in that after having oriented the flag (15) so that the means for measuring an angle of the enveloping structure (26) relative to the probe body (11) o indicates a characterization angle of the probe, and before adjusting the rotation angle sensor so that it indicates a zero value, the method consists in immobilizing the enveloping structure (26) relative to the support (20).
11. Dispositif de caractérisation d'une sonde d'incidence, la sonde 5 comportant un drapeau mobile (15) en rotation autour d'un axe (Δs), caractérisé en ce que le dispositif comporte une structure enveloppante (26) destinée à recevoir le drapeau (15), et en ce que la structure enveloppante (26) forme une référence mécanique dans la détermination d'un angle de caractérisation de la sonde. 0 11. Device for characterizing an incidence probe, the probe 5 comprising a mobile flag (15) rotating around an axis (Δs), characterized in that the device comprises an enveloping structure (26) intended to receive the flag (15), and in that the enveloping structure (26) forms a mechanical reference in determining a characterization angle of the probe. 0
PCT/EP2004/051125 2003-06-24 2004-06-16 In-situ control system, characterisation device and method for control of an angle of attack probe WO2004113929A1 (en)

Priority Applications (1)

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EP04741809A EP1636596A1 (en) 2003-06-24 2004-06-16 In-situ control system, characterisation device and method for control of an angle of attack probe

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FR0307625A FR2856799B1 (en) 2003-06-24 2003-06-24 SITE CONTROL DEVICE, CHARACTERIZATION DEVICE AND METHOD OF CONTROLLING IMPACT PROBE
FR0307625 2003-06-24

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013144157A1 (en) * 2012-03-28 2013-10-03 Dassault Aviation Method for determining a credibility state of measurements from an incidence sensor of an aircraft, and corresponding system
CN103698557A (en) * 2012-09-27 2014-04-02 北京同步科技有限公司 Device and method for improving the accuracy of angular velocity sensors

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3097042B1 (en) * 2019-06-06 2021-05-28 Thales Sa INCIDENCE SENSOR CLOVER CHECK

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4909077A (en) * 1989-07-14 1990-03-20 Safe Flight Instrument Company Settable indexing device for aircraft angle of attack indicator meter
FR2787886A1 (en) * 1998-12-23 2000-06-30 Sextant Avionique METHOD AND DEVICE FOR ADJUSTING A WEATHER AND ADJUSTABLE WEATHER BY THIS METHOD
FR2803387A1 (en) * 1999-12-30 2001-07-06 Thomson Csf Sextant DEVICE FOR ANGULAR POSITIONING OF AN INCIDENCE PROBE ON A WALL, OF THE TYPE INCLUDING A MOBILE CLOVER AROUND AN AXIS, ESPECIALLY ON AN AIRCRAFT WALL

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4909077A (en) * 1989-07-14 1990-03-20 Safe Flight Instrument Company Settable indexing device for aircraft angle of attack indicator meter
FR2787886A1 (en) * 1998-12-23 2000-06-30 Sextant Avionique METHOD AND DEVICE FOR ADJUSTING A WEATHER AND ADJUSTABLE WEATHER BY THIS METHOD
FR2803387A1 (en) * 1999-12-30 2001-07-06 Thomson Csf Sextant DEVICE FOR ANGULAR POSITIONING OF AN INCIDENCE PROBE ON A WALL, OF THE TYPE INCLUDING A MOBILE CLOVER AROUND AN AXIS, ESPECIALLY ON AN AIRCRAFT WALL

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013144157A1 (en) * 2012-03-28 2013-10-03 Dassault Aviation Method for determining a credibility state of measurements from an incidence sensor of an aircraft, and corresponding system
FR2988851A1 (en) * 2012-03-28 2013-10-04 Dassault Aviat METHOD FOR DETERMINING A CREDIBILITY STATE OF MEASUREMENTS OF AN AIRCRAFT INCIDENT SENSOR AND CORRESPONDING SYSTEM
US9933451B2 (en) 2012-03-28 2018-04-03 Dassault Aviation Method for determining a state of credibility of measurements of an incidence sensor of an aircraft and corresponding system
CN103698557A (en) * 2012-09-27 2014-04-02 北京同步科技有限公司 Device and method for improving the accuracy of angular velocity sensors

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EP1636596A1 (en) 2006-03-22
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