CN104034301A - Microminiature type angle-of-attack sensor - Google Patents
Microminiature type angle-of-attack sensor Download PDFInfo
- Publication number
- CN104034301A CN104034301A CN201410256403.2A CN201410256403A CN104034301A CN 104034301 A CN104034301 A CN 104034301A CN 201410256403 A CN201410256403 A CN 201410256403A CN 104034301 A CN104034301 A CN 104034301A
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- Prior art keywords
- angle
- weathercock
- microminiature
- attack
- weather
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Classifications
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
Abstract
The invention provides a microminiature type angle-of-attack sensor. The microminiature type angle-of-attack sensor comprises an installing seat, an integrated force-arm type weather vane, a bearing, a balancing weight and an angle-of-attack acquiring device, wherein the installing seat is provided with an internal containing space; the integrated force-arm type weather vane comprises a weather-vane shaft, a weather-vane force arm extending obliquely from one end of the weather-vane shaft, and a weather-vane wing surface supported by the weather-vane force arm; the weather-vane force arm and the weather-vane wing surface are exposed at the outer part of the installing seat and rotate along with airflow to drive the weather-vane shaft to rotate together; the bearing is arranged in the internal containing space and is used for supporting the weather-vane shaft penetrating through the bearing; the balancing weight is arranged at the other end of the weather-vane shaft and is positioned under the bearing in the internal containing space; and the angle-of-attack acquiring device is arranged at the bottom part of the internal containing space and is connected with the weather-vane shaft. The microminiature type angle-of-attack sensor provided by the invention has the advantages of compact structure, clean pneumatic appearance, small interference for a flow field, easiness in miniaturization, low friction force and high measuring accuracy.
Description
Technical field
The present invention relates to sensor technical field, relate more specifically to a kind of microminiature angle of attack sensor, it is for measuring the local airflow direction of wind tunnel experiment model surface, or for the atmosphere data collection of unmanned plane.
Background technology
Angle of attack sensor, claims again incidence vane, and it is arranged on aircraft fuselage side conventionally for measuring flying angle.Existing angle of attack sensor is mainly divided into two large classes: pressure reduction make zero formula angle of attack sensor and weather vane type angle of attack sensor.Because make zero formula angle of attack sensor complex structure, assembly precision requirement of pressure reduction is high, substantially all by weather vane type angle of attack sensor, replaced at present.Weather vane type angle of attack sensor mainly comprises the parts such as weathercock (being airfoil fan), weathercock axle, angle measurement unit and housing, and the angle of attack that is generally used for true aircraft and unmanned plane is measured.
In traditional design, for the factors such as volume of structural maintenance, angle measurement unit, weather vane type angle of attack sensor is often difficult to realize miniaturization; In the aerodynamic configuration of weathercock, comprising its joint being connected with weathercock axle and securing member etc. affects the part of self aerodynamic configuration clean level, and this field house that needs are accurately caught to flow field characteristic is very unfavorable, is therefore difficult to use in compared with in the wind tunnel experiment of small scale model; Traditional angle measurement unit comprises potentiometer type and mechanical type, there is moment of friction or the gap that is difficult to accurately control in these devices, the precision that the angle of attack is measured is very unfavorable, and the wearing and tearing that long-term use causes will have a strong impact on reliability and the precision of angle of attack sensor; Traditional weathercock aerodynamic configuration is sweepback aerofoil, though processing mode is comparatively simple, its sensitivity under the condition of low dynamic pressure incoming flow is not enough.
Summary of the invention
In order to overcome the above-mentioned deficiency of prior art, the invention provides a kind of microminiature angle of attack sensor of low friction.
According to an aspect of the present invention, provide a kind of microminiature angle of attack sensor, it comprises:
Mount pad, it has inner accommodation space;
The arm-type weathercock of integrated force, it comprises the weathercock axle being received in described inner accommodation space, the weathercock arm of force that is tilted to extend by weathercock axle one end and the weathercock aerofoil being supported by the weathercock arm of force, thereby the described weathercock arm of force is exposed to described mount pad outside for rotating and drive weathercock axle to rotate with air-flow with weathercock aerofoil;
Bearing, it is fixed in described inner accommodation space for supporting the described weathercock axle through it;
Balancing weight, it is installed in the other end of described weathercock axle, described balancing weight in described inner accommodation space, be positioned at described bearing below;
Angle of attack acquisition device, it is installed in the bottom of described inner accommodation space and is connected with described weathercock axle.
Of the present invention aspect this, owing to adopting the arm-type weathercock of integrated force, make whole angle of attack sensor compact conformation, be convenient to miniaturization, make weathercock aerodynamic configuration cleaner, stream field disturbs little, has greatly improved the sensitivity to low dynamic pressure incoming flow simultaneously, can experience the subtle change of the aerodynamic moment that small change in angle of attack brings, so measurement result is truer; And the existence of the weathercock arm of force is convenient to make weathercock aerofoil to work in beyond boundary-layer, and be convenient to improve the aerodynamic moment that weathercock aerofoil produces, be suitable for providing enough sensitivity in the less wind tunnel experiment of dynamic pressure; Separately, the cooperation of weathercock axle and bearing can effectively guarantee low frictional fit, further improves the ability that angle of attack sensor accurately catches flow field characteristic.
Preferably, described angle of attack acquisition device comprises magnet and Hall element, wherein said magnet is fixed to the bottom of described balancing weight, thereby described Hall element is installed in the bottom of described inner accommodation space and is positioned in isolated mode the changes of magnetic field generation voltage signal that described magnet below is used for experiencing described magnet.
The built-in balancing weight magnet mount pad of holding concurrently makes rotary part (comprising the arm-type weathercock of integrated force, balancing weight and magnet) the apparent wind parameter of angle of attack sensor realize weight balancing, realized truly servo-actuated with incoming flow, got rid of the impact of the gravity of rotary part on measurement result, make rotary part compact conformation, aerodynamic configuration is clean simultaneously; In addition, by magnet with the wind the rotation of parameter produce changes of magnetic field, thereby and by contactless Hall element, experience this changes of magnetic field and produce voltage signal, realized the measurement of aircraft angle of attack.
Further preferably, described angle of attack acquisition device also comprises the installing plate of the bottom that is installed in described inner accommodation space, and described Hall element is installed on described installing plate by glueing joint or welding.By installing plate, provide reference plane, can make Hall element and magnetic field axis quadrature, be convenient to accurate measurement.
Further preferably, described Hall element is contactless CMOS Hall element.By the setting of this Hall element, can realize extremely low friction force, and can, when guaranteeing degree of precision, realize the microminaturization of sensor, and cost be lower.
The gap further preferably, between described Hall element and described magnet with 0.5～1.5mm.This clearance distance is more conducive to the changes of magnetic field of Hall element sensing magnet.
Further preferably, described balancing weight has bottom groove, and described magnet is flush-mounted in described bottom groove by wringing fit or splicing.By this kind of setting, avoided the use of securing member and other syndetons, make the mechanical hook-up of whole angle of attack sensor and the combination of electronic installation compact, promoted the realization of microminaturization.
Further preferably, described balancing weight is arranged so that the arm-type weathercock of described integrated force, balancing weight and magnet realizes weight balancing with respect to described weathercock axle.
Further preferably, the heavily end of described balancing weight is positioned to relatively described weathercock axle and described weathercock aerofoil is 180 ° of layouts.Layout is more conducive to realize the arm-type weathercock of integrated force, balancing weight and magnet with respect to the weight balancing of described weathercock axle like this.
Further preferably, described balancing weight is made by brass or silver alloy.Thereby the large miniaturization little, that be convenient to angle of attack sensor that takes up room of density on the one hand of these materials, thereby not magnetisable avoiding exerts an influence and then affects measurement result changes of magnetic field on the other hand.
Preferably, the ball bearing that described bearing is oil lubrication.The low frictional fit that this can guarantee between weathercock axle and bearing more, further improves the ability that angle of attack sensor accurately catches flow field characteristic.
Further preferably, the section shape of described weathercock aerofoil is wedge shape or double-wedge.This kind of section manufacturing process is relatively simple, and is applicable to subsonic speed, transonic speed and supersonic flow field simultaneously.
Further preferably, the angle of the sagittal plane of the relatively described weathercock axle of the described weathercock arm of force is within the scope of 15～30 °.This contribute to make weathercock aerofoil can the boundary-layer in ring flange place plane outside, make weathercock there is the longer rotation arm of force, aerodynamic moment is unlikely to cause to the excessive moment of flexure of weathercock arm of force root simultaneously, affects weathercock arm of force intensity.
Preferably, described mount pad comprises housing and the ring flange being spirally connected with housing one end, the described inner accommodation space of the common formation of the inner chamber of described housing and the inner chamber of described ring flange, wherein, described bearing is arranged in the inner chamber of described ring flange, and described balancing weight is arranged in the inner chamber of described housing.Both link together housing by fine thread.. wherein, housing can be used for other inner parts of protection, and whole angle of attack sensor can be by being fixed on ring flange on the wall that needs to install.
Further preferably, described housing and ring flange are formed by duralumin, hard alumin ium alloy or stainless steel car system.By this, arrange, make processing cost lower, metal shell and ring flange can also form the shielding of electromagnetic field to external world.
Further preferably, the top of described weathercock axle has the shaft shoulder, the top surface adjacency of the basal surface of the described shaft shoulder and described bearing.Weathercock axle top be shaped as shaft shoulder shape, can be used for location and compress bearing, improve the size of weathercock arm of force root to increase intensity simultaneously.
By reference to described embodiment below, these and other aspects of the present invention will clearly be set forth.
Accompanying drawing explanation
Structure of the present invention and mode of operation and further object and advantage are better understood the description by below in conjunction with accompanying drawing, and wherein, identical reference marker identifies identical element:
Fig. 1 is according to the schematic cross sectional views of the microminiature angle of attack sensor of a specific embodiment of the present invention;
Fig. 2 is the schematic perspective view of the arm-type weathercock of integrated force of microminiature angle of attack sensor in Fig. 1;
Fig. 3 is the section shape schematic diagram of the weathercock aerofoil of the arm-type weathercock of integrated force in Fig. 2;
Fig. 4 is a section shape schematic diagram that change is routine of the weathercock aerofoil of the arm-type weathercock of integrated force in Fig. 2.
Embodiment
As requested, will disclose the specific embodiment of the present invention here.Yet, should be understood that, disclosed embodiment is only exemplary of the present invention here, it can be presented as various forms.Therefore, here the detail disclosing is not considered to restrictive, and be only as the basis of claim and as for instructing those skilled in the art differently to apply representational basis of the present invention in any appropriate mode of reality, comprise employing disclosed various features in conjunction with the feature that may clearly not disclose here here.
It should be noted that in this article, for explaining the structure of various piece and the direction indication of action of disclosed embodiment, such as top surface, basal surface, top, bottom etc., is not absolute, but relative.When the various piece of disclosed embodiment is positioned at position shown in figure, these expressions are suitable.If the position of the embodiment that discloses or reference system change, these expressions also will change according to the change of the position of disclosed embodiment or reference system.
Fig. 1 schematically shows the microminiature angle of attack sensor according to a specific embodiment of the present invention, and it comprises housing 1, ring flange 2, the arm-type weathercock 3 of integrated force, bearing 4, balancing weight 5, magnet 6, Hall element 7, installing plate 8.Housing 1 is for example spirally connected by fine thread at the main part of its top ends and ring flange 2, thereby common formation has the mount pad of inner accommodation space 9, and wherein, the inner chamber of the inner chamber of housing 1 and ring flange 2 forms this inside accommodation space 9 jointly.Bearing 4 is arranged in the inner chamber of ring flange 2, and balancing weight 5 is arranged in the inner chamber of housing 1.Be to be understood that; the setting of housing 1 can be used for other inner parts of protection; and the whole angle of attack sensor that ring flange 2 can make is fixed on the wall that needs to install, for example, by means of sunk screw (not shown), through countersunk head screw hole 21 on ring flange 2, be screwed on the wall that needs to install.In the present embodiment, housing 1 and ring flange 2 can be formed by duralumin, hard alumin ium alloy or stainless steel car system.
As shown in Figure 1, and in conjunction with Fig. 2 to Fig. 4, the arm-type weathercock 3 of integrated force comprises weathercock axle 31, the weathercock arm of force 32 (claiming again oblique fulcrum bar) that is tilted to extend by weathercock axle one end and the weathercock aerofoil 33 being supported by the weathercock arm of force, the weathercock arm of force 32 and weathercock aerofoil 33 are exposed to the mount pad outside of housing 1 and ring flange 2 formations, thereby drive weathercock axle 31 to rotate for rotating with air-flow.The flat shape of weathercock aerofoil 33 (shape of seeing from weathercock aerofoil full-size direction) is preferably the rectangle that depth-width ratio equals 2, section shape is preferably wedge shape and (sees Fig. 3, wedge shape drift angle is set to 15 ° in the present embodiment) or double-wedge (see Fig. 4, in other embodiment, wedge shape drift angle is set to 20 °), section relative thickness (being aerofoil thickness and the ratio of width) is no more than 30%.Separately, the angle of the sagittal plane of the weathercock arm of force 32 apparent wind parameters 31 is preferably arranged in the scope of 15～30 °.The top of weathercock axle 31 preferably has the shaft shoulder 310, the top surface adjacency of the basal surface of the shaft shoulder and bearing 4, thereby this top surface that can compress bearing 4 contributes to the location of weathercock axle 31, meanwhile, the shaft shoulder 310 can improve the size of root of the weathercock arm of force 32 to increase its intensity.The arm-type weathercock of integrated force preferably adopts stainless steel manufacture, for example, can adopt car system and line cutting processing.It should be noted that, the sagittal plane of above mentioned weathercock axle 31 is the plane at the shaft shoulder 310 places.
As shown in Figure 1, bearing 4 is installed in inner accommodation space 9, is specifically installed in the inner chamber of ring flange 2, for supporting the weathercock axle 31 through it.Bearing 4 preferably adopts the light rank ball bearing of miniature spy, and the light rank ball bearing of this miniature spy adopts the low oil lubrication of viscosity.The transition fit of the preferably little gap value of fit system between weathercock axle 31 and bearing 4, thereby can effectively avoid the distortion of assembling the light rank bearing of miniature spy causing to produce additional friction moment, further improve the ability that angle of attack sensor accurately catches flow field characteristic.
Again as shown in Figure 1, balancing weight 5 is installed in the other end of weathercock axle 31, and in inner accommodation space 9, be positioned at bearing 4 below.Angle of attack acquisition device is installed in the bottom of inner accommodation space 9 and is connected with weathercock axle 31.In the present embodiment, magnet 6, Hall element 7, installing plate 8 form angle of attack acquisition device, wherein magnet 6 is fixed in the bottom groove 51 forming on balancing weight 5, for example by wringing fit or splicing, be flush-mounted in this bottom groove 51, wherein balancing weight 5 has played the dual-use function of counterweight and magnet mount pad.Thereby Hall element 7 is installed in the bottom of inner accommodation space 9 and produces voltage signal with the changes of magnetic field that the below that isolated mode is positioned at magnet 6 is used for experiencing described magnet.Should be understood that, when the angle of attack sensor of application present embodiment, Hall element 7 can for example by means of transmission line, process with outside signal and display device is electrically connected to, so that the aircraft angle of attack of the voltage signal that indication produces corresponding to it.
Hall element 7 is preferably installed on installing plate 8 by glueing joint or welding, and installing plate 8 is installed in the bottom of inner accommodation space 9.Installing plate 8 can adopt epoxy resin board, thereby for example by its edge, embeds the inner side of housing 1 by means of step 11 location of the shell 1 upper formation in body inner side, and the axis of installing plate 8 preferred surface and weathercock axle 31 is perpendicular.Should be appreciated that installing plate 8 nonessential, Hall element 7 also can be directly supported by the inner bottom surface of housing 1.Preferably, Hall element 7 is miniature 360 ° of contactless CMOS Hall elements, and the Hall element of this type can be experienced 360 ° of magnetic field angles and change.Contactless CMOS Hall element, has the gap of 0.5～1.5mm between itself and magnet 6, preferred gap is 1mm.This clearance distance is more conducive to the changes of magnetic field of Hall element sensing magnet.In the present embodiment, magnet 6 preferably adopts SmCo magnet, nd-fe-b magnet or ferrite lattice.
Separately, preferably, balancing weight 5 is arranged so that the arm-type weathercock 3 of integrated force, balancing weight 5 and magnet 6 realizes weight balancing with respect to weathercock axle 31, wherein, the heavily end preferred orientation of balancing weight 5 becomes with respect to weathercock axle 31 and weathercock aerofoil 33 to be 180 ° of layouts, and layout is more conducive to realize the arm-type weathercock of integrated force, balancing weight and magnet with respect to the weight balancing of described weathercock axle like this.Balancing weight 5 is also preferably made by brass or silver alloy, thereby because the large miniaturization little, that be convenient to angle of attack sensor that takes up room of density on the one hand of these materials, thereby not magnetisable avoiding exerts an influence and then affects measurement result changes of magnetic field on the other hand.In the present embodiment, balancing weight 5 adopts tubular shape, be enclosed within on weathercock axle 31, then by for example high-carbon steel holding screw (not shown), through the screw hole 52 on balancing weight 5, be fixed on weathercock axle 31, thereby also play the axial location effect to integrated weathercock 3; Balancing weight 5 tops are provided with the shaft shoulder 53, for locating and compress bearing.In the present embodiment, as shown in Figure 1, in assembling process, bearing 4 packs in turn from the endoporus bottom of ring flange 2, and ring flange endoporus top car has step 22 to come the outer ring of alignment bearing 4, at the other end of bearing 4, just by the shaft shoulder 53, carrys out alignment bearing inner ring; Weathercock axle 3 is located by the shaft shoulder 310 (seeing Fig. 2) at the shaft shoulder 53 and self top again.
In addition, although the angle of attack acquisition device of introducing is in the present embodiment by magnet 6, Hall element 7 and installing plate 8 form, but should be understood that, angle of attack acquisition device can also be used other implementation, for example can adopt the wind direction that comprises dumb card code and wind direction change-over circuit conventional in prior art to obtain parts, when adopting this structure, dumb card code is connected with weathercock axle 31, by the rotation of weathercock axle, drive the bearing mark portion of dumb card code to rotate, identify orientation, wind direction change-over circuit and dumb card code are by receiving and dispatching infrared electro element as transmitting-receiving infrared photocell, described orientation is converted to electric signal.
Technology contents of the present invention and technical characterstic have disclosed as above; yet be appreciated that; under creative ideas of the present invention; those skilled in the art can make various changes and improve said structure and shape; comprise here and to disclose separately or the combination of claimed technical characterictic, comprise significantly other combination of these features.These distortion and/or combination all fall in technical field involved in the present invention, and fall into the protection domain of the claims in the present invention.It should be noted that by convention, in claim, use discrete component to be intended to comprise one or more such elements.In addition, any reference marker in claims should be configured to limit the scope of the invention.
Claims (15)
1. a microminiature angle of attack sensor, is characterized in that comprising:
Mount pad, it has inner accommodation space;
The arm-type weathercock of integrated force, it comprises the weathercock axle being received in described inner accommodation space, the weathercock arm of force that is tilted to extend by weathercock axle one end and the weathercock aerofoil being supported by the weathercock arm of force, thereby the described weathercock arm of force is exposed to described mount pad outside for rotating and drive weathercock axle to rotate with air-flow with weathercock aerofoil;
Bearing, it is installed in described inner accommodation space for supporting the described weathercock axle through it;
Balancing weight, it is fixed on the other end of described weathercock axle, described balancing weight in described inner accommodation space, be positioned at described bearing below;
Angle of attack acquisition device, it is installed in the bottom of described inner accommodation space and is connected with described weathercock axle.
2. microminiature angle of attack sensor according to claim 1, it is characterized in that, described angle of attack acquisition device comprises magnet and Hall element, wherein said magnet is fixed to the bottom of described balancing weight, thereby described Hall element is installed in the bottom of described inner accommodation space and is positioned in isolated mode the changes of magnetic field generation voltage signal that described magnet below is used for experiencing described magnet.
3. microminiature angle of attack sensor according to claim 2, is characterized in that, described angle of attack acquisition device also comprises the installing plate of the bottom that is installed in described inner accommodation space, and described Hall element is installed on described installing plate by glueing joint or welding.
4. microminiature angle of attack sensor according to claim 2, is characterized in that, described Hall element is contactless CMOS Hall element.
5. microminiature angle of attack sensor according to claim 2, is characterized in that, has the gap of 0.5～1.5mm between described Hall element and described magnet.
6. microminiature angle of attack sensor according to claim 2, is characterized in that, described balancing weight has bottom groove, and described magnet is flush-mounted in described bottom groove by wringing fit or splicing.
7. microminiature angle of attack sensor according to claim 2, is characterized in that, described balancing weight is arranged so that the arm-type weathercock of described integrated force, balancing weight and magnet realizes weight balancing with respect to described weathercock axle.
8. microminiature angle of attack sensor according to claim 7, is characterized in that, the heavily end of described balancing weight is positioned to relatively described weathercock axle and described weathercock aerofoil is 180 ° of layouts.
9. microminiature angle of attack sensor according to claim 2, is characterized in that, described balancing weight is made by brass or silver alloy.
10. microminiature angle of attack sensor according to claim 1, is characterized in that, the ball bearing that described bearing is oil lubrication.
11. microminiature angle of attack sensors according to claim 1, is characterized in that, the section shape of described weathercock aerofoil is wedge shape or double-wedge.
12. microminiature angle of attack sensors according to claim 1, is characterized in that, the angle of the sagittal plane of the relatively described weathercock axle of the described weathercock arm of force is within the scope of 15～30 °.
13. microminiature angle of attack sensors according to claim 1, it is characterized in that, described mount pad comprises housing and the ring flange being spirally connected with housing one end, the described inner accommodation space of the common formation of the inner chamber of described housing and the inner chamber of described ring flange, wherein, described bearing is arranged in the inner chamber of described ring flange, and described balancing weight is arranged in the inner chamber of described housing.
14. microminiature angle of attack sensors according to claim 13, is characterized in that, described housing and ring flange are formed by duralumin, hard alumin ium alloy or stainless steel car system.
15. microminiature angle of attack sensors according to claim 13, is characterized in that, the top of described weathercock axle has the shaft shoulder, the top surface adjacency of the basal surface of the described shaft shoulder and described bearing.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410256403.2A CN104034301B (en) | 2014-06-10 | 2014-06-10 | Microminiature type angle-of-attack sensor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410256403.2A CN104034301B (en) | 2014-06-10 | 2014-06-10 | Microminiature type angle-of-attack sensor |
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| CN104034301A true CN104034301A (en) | 2014-09-10 |
| CN104034301B CN104034301B (en) | 2017-04-26 |
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| CN106289709A (en) * | 2016-11-04 | 2017-01-04 | 中国航天空气动力技术研究院 | Realize the wind-tunnel side window test mechanism of the big angle of attack |
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| CN106289709A (en) * | 2016-11-04 | 2017-01-04 | 中国航天空气动力技术研究院 | Realize the wind-tunnel side window test mechanism of the big angle of attack |
| US11181545B2 (en) | 2017-08-17 | 2021-11-23 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
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| CN110500203A (en) * | 2019-09-20 | 2019-11-26 | 西安航天动力测控技术研究所 | A kind of solid rocket ramjet high speed free jet angle of attack measuring system based on weathercock |
| US11649057B2 (en) | 2019-12-13 | 2023-05-16 | Rosemount Aerospace Inc. | Static plate heating arrangement |
| US20220381801A1 (en) * | 2021-05-27 | 2022-12-01 | Airbus Operations S.A.S. | Device for Measuring the Orientation of a Fluid Flow Relative to an Aerodynamic Surface, in Particular of an Aircraft, Using a Magnetic Sensor |
| WO2023281013A1 (en) * | 2021-07-07 | 2023-01-12 | Thales | Angle-of-attack sensor, in particular for an aircraft |
| CN114353739A (en) * | 2021-12-10 | 2022-04-15 | 武汉航空仪表有限责任公司 | Miniaturized multifunctional probe sensor |
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