Airplane angle of attack excitation device

Abstract

An aircraft angle-of-attack (AOA) excitation device is disclosed, capable of remotely adjusting the rotation angle of an aircraft angle-of-attack weather vane. The device includes: a weather vane clamp for holding and fixing the weather vane; a fixing part for fixing the weather vane clamp to the excitation device; a drive part fixedly connected to the weather vane clamp and for driving the weather vane clamp to rotate; and a control part communicatively connected to the drive part, receiving remote operation signals from a real-time simulation model, and controlling the drive part to rotate to a desired angle. Through this aircraft OAA excitation device, the aircraft's angle of attack can be rotated to a specific angle via real-time simulation model data.

Description

Technical Field

[0001] This utility model relates to an aircraft angle of attack excitation device, and more specifically, to an aircraft angle of attack excitation device that can automatically change the aircraft angle of attack during ground testing, belonging to the field of civil aircraft ground testing. Background Technology

[0002] Angle-of-attack excitation (AOA) tests are important tests used to evaluate the angle-of-attack (AOA) function of an aircraft's air data system and its interconnected response with other systems. By observing the responses of the air data system, main flight control system, and other interconnected systems at different angles of attack, the tests provide insights into the functional performance of the aircraft systems at various flight angles of attack, thus providing a basis for aircraft system design, optimization, and performance evaluation.

[0003] Aircraft angle of attack data from excitation tests is crucial for pilots to correctly control the aircraft and ensure stable flight. Verifying the proper functioning of the aircraft's angle of attack wind vane and related systems is essential during flight tests and ground tests of civil aircraft.

[0004] Currently, angle-of-attack wind vane excitation devices designed both domestically and internationally are mainly used for standalone testing of angle-of-attack wind vanes. After connecting the angle-of-attack wind vane excitation device to the angle-of-attack wind vane, the wind vane is rotated to a specific angle by manual rotation or remote control, and the value displayed on the instrument is observed to see if it matches the required rotation angle.

[0005] Meanwhile, during the ground-based hardware-in-the-loop simulation test of the aircraft, the signal injection method could not fully reproduce the process of acquiring in-flight angle of attack data, and could not verify the function of the angle of attack wind vane in the entire flight control system.

[0006] For example, patent document CN221976909U discloses a device for measuring and setting the angle of attack of an aircraft angle sensor wind vane. This device inputs a target angle into a remote control terminal, and the controller within the device automatically rotates the wind vane to the target angle and maintains it after receiving the control command, while simultaneously transmitting the angle input back to the remote control terminal. However, this patent's technical solution does not limit the deflection angle of the wind vane clamp, thus lacking protection for the aircraft's wind vane.

[0007] Patent document CN110530328A discloses an angle-of-attack sensor setting device. This device uses a sensor clamping device to clamp the angle-of-attack weather vane and designs a rotating setting device to set the weather vane angle. At the same time, the rotating device is connected to a graduated disk, which can read the given weather vane angle. However, the technical solution of this patent only supports manually setting one angle and cannot drive the weather vane to rotate in real time.

[0008] Furthermore, patent document CN217465767U discloses a weather vane-type angle-of-attack sensor testing device, which can be used for ground and on-board testing of weather vane-type angle-of-attack sensors for medium-sized, medium-range transport aircraft. The weather vane locking device used ensures a secure lock on the angle-of-attack sensor weather vane, eliminating any wobble or gaps, and resulting in a stable and accurate output signal. This device has a high degree of automation, is simple and convenient to operate, and facilitates testing of the angle-of-attack signal output by the sensor. However, this patent's technical solution also only supports manually setting one angle and cannot continuously drive the weather vane to rotate in real time.

[0009] Patent document CN204846393U discloses an aircraft angle of attack setting device. In use, this device attaches a weather vane pointer to an angle of attack weather vane and allows manual adjustment of the pointer to the desired aircraft angle of attack direction, thus achieving the function of angle of attack setting. However, this patent's technical solution only supports manually setting one angle and is primarily used for static testing of angle of attack weather vanes.

[0010] Furthermore, patent document CN104986355B discloses a method and device for setting the angle of attack of an aircraft. This device includes a base, a dial, and a weather vane pointer. The inner ring of the base has an annular step supporting the dial, and at the center of the base is an open ring corresponding to the weather vane. This open ring is connected in a recessed manner to the inner ring of the base. The outer ring of the base is connected to suction cup feet via adjusting bolts. The surfaces of the two dials have angle lines indicating the aircraft's angle of attack. The dial is placed on the annular step of the inner ring of the base, and the tail end of the weather vane pointer has a connection hole for attaching to an angle weather vane. However, this patent's technical solution also only supports manually setting one angle and is mainly used for static testing of the angle of attack weather vane.

[0011] To address the shortcomings of the existing technology, it is necessary to design an angle-of-attack excitation device that can be installed on an aircraft angle-of-attack wind vane. This device uses model data to drive a motor and deflect the aircraft angle-of-attack wind vane, thereby providing the angle of attack in real time from the sensor and introducing a real angle-of-attack wind vane into ground simulation tests. Utility Model Content

[0012] This disclosure is made to solve the above-mentioned technical problems, and its purpose is to provide an aircraft angle of attack excitation device, which can be remotely driven by real-time simulation model data, thereby causing the aircraft angle of attack to rotate to a specific angle.

[0013] To achieve the objectives of this disclosure, an aircraft angle of attack excitation device is provided, which can remotely adjust the rotation angle of an aircraft angle of attack weather vane. The aircraft angle of attack excitation device includes: a weather vane clamp for clamping and fixing the aircraft angle of attack weather vane; a fixing part for fixing the weather vane clamp to the aircraft angle of attack excitation device; a drive part for driving the weather vane clamp to rotate; and a control part for communicating with the drive part, receiving remote control signals from a real-time simulation model, and controlling the drive part to rotate to a desired angle.

[0014] Based on the above-described configuration, the aircraft angle-of-attack excitation device disclosed herein allows test personnel to realistically simulate the working process of an aerial angle-of-attack weather vane on the ground, thereby effectively improving the realism and accuracy of ground-based hardware-in-the-loop simulation tests.

[0015] Preferably, it further includes a power supply unit, which is a rechargeable battery and is connected to the drive unit and the control unit in a manner that enables it to supply power.

[0016] According to the configuration described above, by incorporating a rechargeable battery into the aircraft angle-of-attack excitation device, the service life of the device can be effectively extended, and its environmental adaptability can be significantly improved.

[0017] Preferably, it further includes a housing, which is the outer casing of the aircraft angle of attack excitation device, and houses the drive unit, the control unit, and the power supply unit inside.

[0018] As described above, by integrating the drive unit, control unit, and power supply unit inside the device through the storage unit, the overall size of the device can be reduced, which is beneficial for the installation of the aircraft angle of attack excitation device.

[0019] Preferably, it further includes a limiting part, which is formed as part of the receiving part and restricts the rotational movement of the wind vane clip.

[0020] Preferably, it further includes a limiting part, which is formed as a component integral with the receiving part, and restricts the rotational movement of the wind vane clip.

[0021] As described above, the limiting part can restrict the rotational movement of the wind vane clamp and limit the rotational movement within a predetermined angle range, thereby effectively preventing damage to the aircraft angle-of-attack wind vane.

[0022] Preferably, the control unit is connected to the outside and can receive control signals from a remote control terminal, and the power supply unit is connected to the outside and can receive charging power from an external power source.

[0023] As described above, the device can transmit control signals to the control unit via remote operation and can charge the power supply unit via an external power source. It has a simple structure and is easy to operate.

[0024] Preferably, the weather vane clamp has a clamping portion formed at one end, which is composed of two elastic plates facing each other.

[0025] As described above, the clamping part can clamp aircraft angle-of-attack weather vanes of any size, thereby improving the adaptability of the device.

[0026] Preferably, the weather vane clip also has a fastening part and a mounting part. The fastening part is formed in the middle part of the weather vane clip and is formed in the form of an external thread. The mounting part is formed at the other end opposite to the aforementioned one end and is fixedly connected to the aforementioned drive part.

[0027] Preferably, the fixing part further includes a locking sleeve and a locking nut. The locking sleeve is formed as a hollow cylinder with internal threads and is screwed into the fastening part. The locking nut is formed as a cap-shaped part with an orifice whose cross-section matches the clamping part.

[0028] As described above, the aircraft angle-of-attack wind vane can be firmly fixed by the cooperation of the fastening part, the locking sleeve and the locking nut, thereby preventing the aircraft angle-of-attack wind vane from falling off during rotation and significantly improving the reliability of the test.

[0029] Preferably, the aforementioned storage section is L-shaped when viewed from above.

[0030] As described above, the drive unit is installed at the corner of the "L"-shaped storage unit through the storage unit, and the limiting part is formed by the two side frames of the "L" shape. The structure is simple, easy to install, and highly reliable. Attached Figure Description

[0031] With reference to the above objectives, the technical features of this utility model are clearly described in the following technical solutions, and its advantages are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of this utility model by way of example, without limiting the scope of the inventive concept.

[0032] Figure 1 This is a schematic diagram of the overall structure of the aircraft angle of attack excitation device of this utility model.

[0033] Figure 2 This is a schematic diagram of the split structure of the aircraft angle of attack excitation device of this utility model.

[0034] Figure 3 This is a schematic diagram of the working process of the aircraft angle of attack excitation device of this utility model.

[0035] Symbol Explanation

[0036] 1. Aircraft angle of attack excitation device;

[0037] 11. Weather vane clip;

[0038] 111 Clamping part;

[0039] 112 Fastening parts;

[0040] 113 Installation Department;

[0041] 12. Fixing part;

[0042] 121 Locking sleeve;

[0043] 122 Locking nut;

[0044] 123 Fixed bridge code;

[0045] 13. Drive unit;

[0046] 131 Electric servo motor;

[0047] 14. Control Department;

[0048] 141 Control chip;

[0049] 142 wireless connector;

[0050] 15. Power Supply Department;

[0051] 151 Storage battery;

[0052] 152 Charging connector;

[0053] 16. Storage Department;

[0054] 161. Outer shell frame;

[0055] 17. Limiting part;

[0056] 171 Physical limit frame. Detailed Implementation

[0057] Various embodiments of the present invention will now be described in detail, examples of which are shown in the accompanying drawings.

[0058] Although this invention has been described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to the exemplary embodiments described below. Rather, the invention is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents, and other embodiments that may be included within the spirit and scope of the invention as defined by the appended claims.

[0059] The following is for reference Figure 1 The overall structure of the aircraft angle of attack excitation device 1 of this utility model will be described. Figure 1 This is a schematic diagram showing the overall structure of the aircraft angle of attack excitation device 1 of this utility model.

[0060] like Figure 1 As shown, the aircraft angle of attack excitation device 1 of this utility model mainly includes a wind vane clip 11, a fixing part 12, a driving part 13, a control part 14, a power supply part 15, a storage part 16, and a limiting part 17.

[0061] The aforementioned weather vane clip 11 is formed in a roughly cylindrical shape and is mainly used to clamp and fix the aircraft weather vane used in the aircraft angle of attack excitation test.

[0062] The aforementioned fixing part 12 mainly includes a weather vane clamp fixing part and a weather vane clamp fastening part. The weather vane clamp fixing part is used to fix the weather vane clamp 11 to the aircraft angle of attack excitation device 1. The weather vane clamp fastening part is used to fasten the angle of attack weather vane to the weather vane clamp 11 when the weather vane clamp 11 clamps the angle of attack weather vane.

[0063] The aforementioned drive unit 13 is fixedly connected to the aforementioned wind vane clamp 11 and is used to drive the wind vane clamp 11 to rotate, thereby rotating the aircraft angle of attack wind vane to a specific angle.

[0064] The control unit 14 is installed inside the aircraft angle of attack excitation device 1 and is connected to the drive unit 13 via a communication line, thereby enabling remote control of the drive unit 13 to rotate to a specific angle.

[0065] The power supply unit 15 is built into the aircraft angle of attack excitation device 1 and is connected to the drive unit 13 and the control unit 14 via a power line so as to supply power to the drive unit 13 and the control unit 14.

[0066] The aforementioned housing 16 is the casing of the aircraft angle of attack excitation device 1, which can accommodate the wind vane clip 11, the fixing part 12 and the drive part 13, and houses the control part 14 and the power supply part 15 inside.

[0067] The aforementioned limiting part 17 is provided in the rotation path of the aforementioned weather vane clamp 11, and is mainly used to limit the rotational movement of the weather vane clamp 11.

[0068] The following is for reference Figure 2 The specific structure of each part of the aircraft angle of attack excitation device 1 of this utility model will be described. Figure 2 This is a schematic diagram of the split structure of the aircraft angle of attack excitation device 1 of this utility model.

[0069] like Figure 2 As shown, in the aircraft angle of attack excitation device 1 of this utility model, the aforementioned wind vane clip 11 mainly includes a clamping part 111, a fastening part 112, and a mounting part 113.

[0070] The aforementioned clamping part 111 is formed at one end of the weather vane clamp 11 and is composed of two opposing plates to facilitate clamping the aircraft angle of attack weather vane.

[0071] Preferably, the two plates constituting the clamping part 111 have a certain degree of elasticity and are able to clamp an aircraft angle-of-attack wind vane of any size.

[0072] The aforementioned fastening part 112 is formed in the middle part of the weather vane clamp 11 and is formed in the form of an external thread to facilitate the fastening installation of the fixing part 12, thereby fastening and fixing the aircraft angle of attack weather vane held by the clamping part 111. The aforementioned mounting part 113 is formed in the weather vane clamp 11 at the other end opposite to the clamping part 111 and is fixedly connected to the aforementioned driving part 13.

[0073] In the aforementioned fixing part 12, the weather vane clamp fixing part includes a locking sleeve 121 and a locking nut 122. The locking sleeve 121 is formed into the shape of a hollow cylinder with internal threads. In use, the locking sleeve 121 is fitted onto the clamping part 111 and screwed into the fastening part 112 so that the clamped aircraft angle of attack weather vane is fastened and fixed by clamping the clamping part 111. The locking nut 122 is formed into a cap shape with an opening, and the cross-section of the opening is formed to match the cross-sectional shape of the clamping part 111 so that after the locking sleeve 121 is fitted onto the clamping part 111, the locking nut 122 is installed on the locking sleeve 121, thereby further fastening and fixing the locking sleeve 121 to the clamping part 111.

[0074] The aforementioned weather vane clamp fastening part is formed as a fixed bridge bracket 123. Through the fixed bridge bracket 123, the aforementioned mounting part 113 is fixedly installed on the aforementioned driving part 13 via a fixing screw, thereby fixing the weather vane clamp 11 to the aircraft angle of attack excitation device 1.

[0075] The aforementioned drive unit 13 is formed in the form of an electric servo motor 131. The mounting part 113 of the aforementioned wind vane clip 11 is fixedly installed on the top of the electric servo motor 131. The electric servo motor 131 can rotate around its own rotation axis, thereby driving the aforementioned wind vane clip 11 to rotate, so as to drive the aircraft angle of attack wind vane and change the aircraft angle of attack.

[0076] The aforementioned control unit 14 is installed inside the aircraft angle-of-attack excitation device 1, and mainly includes a control chip 141 and a wireless connector 142. The control chip 141 is connected to the electric servo motor 131 via a communication line, thereby controlling the rotational movement of the electric servo motor 131. The wireless connector 142 is connected to the outside and is connected to the control chip 141 via a communication line, thereby receiving control signals from a remote control terminal and transmitting the control signals to the control chip 141 to drive the electric servo motor 131 to rotate a specific angle.

[0077] The aforementioned power supply unit 15 is also installed inside the aircraft angle-of-attack excitation device 1, and mainly includes a battery 151 and a charging connector 152. The battery 151 is connected to the drive unit 13 and the control unit 14 via a power line, thereby supplying power to the electric servo motor 131 and the control chip 141. The battery 151 is a rechargeable battery, which receives charging power from an external power source via the charging connector 152 that communicates with the outside, thereby storing power.

[0078] The aforementioned storage section 16 is the outer frame of the aircraft angle of attack excitation device 1, and is formed into an approximately "L" shape when viewed from above. The aforementioned drive section 13 is installed at the corner of the "L"-shaped storage section 16 through the storage section 16, and the aforementioned control section 14 and power supply section 15 are integrated inside the aircraft angle of attack excitation device 1, thereby reducing the overall size of the device and making it easier to install the aircraft angle of attack excitation device 1 on the aircraft.

[0079] The aforementioned limiting part 17 is formed as a physical limiting frame 171 as part of the aforementioned storage part 16. Through the physical limiting frame 171, the rotational movement of the wind vane clip 11 installed on the electric servo motor 131 can be limited, and the rotational movement is limited to a predetermined angle range, thereby effectively preventing damage to the aircraft angle of attack wind vane.

[0080] In the aircraft angle of attack excitation device 1 of this utility model, the aforementioned limiting part 17 is formed as part of the storage part 16. However, this utility model is not limited to this. The limiting part 17 can also be separately provided relative to the aforementioned storage part 16, and the position of the limiting part 17 can be adjusted as needed to limit the rotational movement of the wind vane clip 11 within the desired angle range.

[0081] Finally, refer to Figure 3The overall working process of the aircraft angle of attack excitation device 1 of this utility model is described. Figure 3 This is a schematic diagram of the working process of the aircraft angle of attack excitation device 1 of this utility model.

[0082] like Figure 3 As shown, when using the aircraft angle of attack excitation device 1 of this utility model, ground personnel send the required angle information to the antenna module of the aircraft angle of attack excitation device 1 through a real-time simulation model of the aircraft angle of attack excitation test, that is, send the data to the control chip 141 via the wireless connector 142. After the control chip of the angle of attack excitation device receives the data, the control chip 141 controls the electric servo of the angle of attack excitation device, that is, the electric servo 131 of the drive unit 13, based on the received instruction information, thereby driving the wind vane clamp 11 of the angle of attack excitation device, so as to drive the airborne angle of attack wind vane held by the wind vane clamp 11 to rotate to a specific position.

[0083] (Technical effect)

[0084] As described above, the aircraft angle of attack excitation device 1 of this utility model, based on the background of real-time simulation, can drive the rotation of the angle of attack wind vane in real time according to the model data, without the need to manually set the angle of attack wind vane angle, thus simultaneously meeting the needs of wind vane testing and semi-physical real-time simulation.

[0085] Furthermore, the wind vane clamp 11 of the aircraft angle of attack excitation device 1 of this utility model can clamp and rotate an angle of attack wind vane of any size, and is also provided with a limiting part to physically limit the rotation angle of the wind vane clamp 11, thereby further protecting the aircraft angle of attack wind vane from damage.

[0086] Meanwhile, the aircraft angle of attack excitation device 1 of this utility model supports wireless connection methods such as WIFI, 5G, and Bluetooth, and can be connected to remote computers, smartphones, etc., thereby realizing wireless control, which is convenient for ground staff to operate and helps to ensure the smooth progress of aircraft angle of attack excitation tests.

[0087] Although the structure and working principle of this utility model have been described above in conjunction with preferred embodiments, those skilled in the art should recognize that the above examples are merely illustrative and do not constitute a limitation on this utility model. Modifications and variations can be made to this utility model within the spirit and scope of the claims, and all such modifications and variations will fall within the protection scope of this utility model.

Claims

1. An aircraft angle of attack excitation device (1) capable of remotely adjusting the angle of rotation of an aircraft angle of attack wind vane, characterized in that, The aircraft angle of attack excitation device (1) includes: Anchor clip (11), the anchor clip (11) is used to clamp and fix the aircraft angle of attack anchor; The fixing part (12) fixes the wind vane clip (11) to the aircraft angle of attack excitation device (1); A drive unit (13), which is fixedly connected to the weather vane clamp (11) and is used to drive the weather vane clamp (11) to rotate; and The control unit (14) is connected to the drive unit (13) in a communicable manner, receives remote control signals from the real-time simulation model, and controls the drive unit (13) to rotate to the desired angle.

2. Aircraft angle of attack excitation device (1) according to claim 1, characterized in that Also includes: The power supply unit (15) is a rechargeable battery (151) and is connected to the drive unit (13) and the control unit (14) in a manner that can supply power.

3. Aircraft angle of attack excitation device (1) according to claim 2, characterized in that Also includes: The storage unit (16) is the outer frame of the aircraft angle of attack excitation device (1), and houses the drive unit (13), the control unit (14) and the power supply unit (15) inside.

4. Aircraft angle of attack excitation device (1) according to claim 3, characterized in that Also includes: The limiting part is formed as part of the receiving part (16) and restricts the rotational movement of the wind vane clip (11).

5. Aircraft angle of attack excitation device (1) according to claim 3, characterized in that Also includes: The limiting part is formed as a separate component from the storage part (16) and restricts the rotational movement of the wind vane clip (11).

6. The aircraft angle of attack excitation device (1) as described in claim 3, characterized in that, The control unit (14) is connected to the outside and can receive control signals from a remote control terminal. The power supply unit (15) is connected to the outside and can receive charging power from an external power source.

7. The aircraft angle of attack excitation device (1) as described in claim 1, characterized in that, The weather vane clip (11) has a clamping portion (111) formed at one end, the clamping portion (111) being composed of two elastic plates facing each other.

8. The aircraft angle of attack excitation device (1) as described in claim 7, characterized in that, The weather vane clip (11) also has a fastening part (112) and a mounting part (113). The fastening part (112) is formed in the middle part of the weather vane clip (11) and is formed in the form of an external thread. The mounting part (113) is formed at the other end opposite to the first end and is fixedly connected to the driving part (13).

9. The aircraft angle of attack excitation device (1) as described in claim 8, characterized in that, The fixing part (12) also has a locking sleeve (121) and a locking nut (122). The locking sleeve (121) is formed as a hollow cylinder with internal threads and is screwed into the fastening part (112). The locking nut (122) is formed as a cap shape with an orifice whose cross-section matches the clamping part (111).

10. The aircraft angle of attack excitation device (1) as described in claim 4, characterized in that, The storage section (16) is L-shaped when viewed from above.

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