A differential pressure aircraft angle of attack sensor warning test apparatus and method

Abstract

An aircraft differential pressure angle of attack sensor warning test device and test method, the differential pressure angle of attack sensor is arranged on both sides of the aircraft, the differential pressure angle of attack sensor is connected with the stall warning system, the test device contains a driving motor, a display controller and a clamp, the clamp is matched with the differential pressure angle of attack sensor, the clamp can clamp and fix the differential pressure angle of attack sensor, the rotating shaft of the driving motor is connected with the clamp, an angular displacement sensor is connected on the rotating shaft of the driving motor, the driving motor drives the clamp and the differential pressure angle of attack sensor to rotate, the angular displacement sensor transmits the rotation angle information to the display controller, the driving motor is controlled by the display controller to drive the differential pressure angle of attack sensor to rotate to the warning angle, the stall warning simulation and comparison warning functions are realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft design and manufacturing, in particular to an aircraft differential pressure angle of attack sensor warning test device and test method. BACKGROUND

[0002] The aircraft differential pressure angle of attack sensor is installed on both sides of the aircraft and is used to detect changes in the angle of attack of the aircraft. When the aircraft is flying, if the angle of attack changes to the stall warning angle, the differential pressure angle of attack sensor transmits a stall warning signal to the aircraft. During the production and manufacturing process of the aircraft, the functions of the aircraft differential pressure angle of attack sensor need to be tested, including zero confirmation, comparison warning, and stall warning functions.

[0003] The existing differential pressure angle of attack sensor test method is generally manual testing. Two scale tables are drawn in advance and pasted next to the differential pressure angle of attack sensors on both sides of the aircraft. A commander gives instructions, and two operators stand next to the differential pressure angle of attack sensors on both sides of the aircraft. After receiving the instructions from the commander, the operators manually rotate the differential pressure angle of attack sensors to the corresponding scale to simulate the stall warning function. Although the above test method can simulate the system function, it has problems such as poor precision, unclear zero reference, and cannot confirm whether the warning angle of the differential pressure angle of attack sensor rotation meets the design requirements, which poses a certain safety risk to the aircraft test flight. SUMMARY

[0004] The purpose of the present application is to provide an aircraft differential pressure angle of attack sensor warning test device and test method to check and test the stall warning, comparison warning, and angle of attack sensor zero of the aircraft. It can also be used for aircraft field maintenance and has the advantages of convenience, accuracy, and safety, meeting the design requirements for the test precision of the differential pressure angle of attack sensor.

[0005] An aircraft differential pressure angle of attack sensor warning test device, the differential pressure angle of attack sensor is arranged on both sides of the aircraft, and the differential pressure angle of attack sensor is connected with a stall warning system. The test device comprises a driving motor, a display controller, and a clamp. The clamp is matched with the differential pressure angle of attack sensor, and the clamp can clamp and fix the differential pressure angle of attack sensor. The rotating shaft of the driving motor is connected with the clamp. An angular displacement sensor is connected on the rotating shaft of the driving motor. The driving motor drives the clamp and the differential pressure angle of attack sensor to rotate, and the angular displacement sensor transmits the rotation angle information to the display controller.

[0006] The application also provides an aircraft differential pressure angle of attack sensor warning test method, which is characterized in that the method comprises the following steps: 1) connecting a driving motor to each differential pressure angle of attack sensor on the two sides of the aircraft through a clamp, and connecting an angle displacement sensor to the rotating shaft of each driving motor; the driving motors on the two sides are controlled by a display controller, and the angle displacement sensors on the two sides respectively transmit the rotating angle information of the driving motors to the display controller; 2) reading the current angle signal of the differential pressure angle of attack sensor through the man-machine interface of the display controller, reading the angle information of the aircraft itself and the differential pressure angle of attack sensor through an ARINC429 reader, and adjusting the angle of the differential pressure angle of attack sensor to zero by the display controller according to the angle information of the aircraft itself and the differential pressure angle of attack sensor; 3) when testing the stall warning function, the driving motors on the two sides can be controlled by the display controller to drive the differential pressure angle of attack sensors on the two sides to rotate to the warning angle synchronously, so as to detect whether the stall warning system on the aircraft is normal; 4) when testing the comparison warning function, one driving motor and one differential pressure angle of attack sensor can be controlled by the display controller to rotate alone, and the driving motor and the differential pressure angle of attack sensor on the other side remain stationary, so as to detect whether the comparison warning function is normal when the included angle between the differential pressure angle of attack sensors on the two sides reaches the comparison warning angle.

[0007] The application has the following beneficial effects: 1) the application is used for testing the information transmission state and the warning function verification of the differential pressure angle of attack sensors installed on the two sides of the aircraft, the driving motors can be controlled by the display controller to drive the differential pressure angle of attack sensors to rotate to the warning angle synchronously, so as to realize the stall warning simulation; or one driving motor and one differential pressure angle of attack sensor can be controlled by the display controller to rotate alone, and the driving motor and the differential pressure angle of attack sensor on the other side remain stationary, so as to realize the comparison warning function when the included angle between the differential pressure angle of attack sensors on the two sides reaches the comparison warning angle; 2) the above device and test method can avoid human errors in the existing measurement method, and improve the test accuracy; 3) the above device and test method can be used for ground simulation test before the flight test of the aircraft, so as to verify the correctness of the differential pressure angle of attack sensor and the related system function, effectively reduce and avoid faults of the system in the flight test, improve the safety of the aircraft, and reduce the safety risk level; 4) the above device and test method can also confirm the mechanical zero reference of the differential pressure angle of attack sensor of the aircraft by comparing the angle values read by the ARINC429 reader, so as to facilitate the installation and adjustment of the sensor;

[0008] 5) the application is convenient, safe and reliable to use, and can effectively improve the work efficiency.

[0009] The application will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF DRAWINGS

[0010] Figure 1This is a block diagram illustrating the working principle of an aircraft differential pressure angle-of-attack sensor alarm test device.

[0011] Figure 2 This is a schematic diagram of the alarm test method for aircraft differential pressure angle-of-attack sensors.

[0012] The numbers in the diagram are explained as follows: 1 Aircraft fuselage, 2 Differential pressure angle of attack sensor, 3 Display controller, 4 Test cable, 5 Drive motor, 6 Angular displacement sensor, 7 Fixture, 8 Bracket, 9 ARINC429 reader. Detailed Implementation

[0013] Referring to the attached diagram, the differential pressure angle-of-attack sensor 2 is located on both sides of the aircraft fuselage 1, and is connected to the aircraft's stall warning system. The working principle of the aircraft differential pressure angle-of-attack sensor alarm testing device of this application is as follows: Figure 1 As shown, the alarm test method for aircraft differential pressure angle-of-attack sensors is as follows: Figure 2 As shown. The differential pressure angle-of-attack sensor alarm test device includes a drive motor 5, a display controller 3, and a clamp 7. The clamp 7 is matched with the differential pressure angle-of-attack sensor 2, and the clamp 7 can hold and fix the differential pressure angle-of-attack sensor 2. The rotation shaft of the drive motor 5 is connected to the clamp 6, and an angular displacement sensor is connected to the rotation shaft of the drive motor 5. Figure 2 (Not shown in the image) The drive motor 5 drives the clamp 7 and the differential angle of attack sensor 2 to rotate. The angular displacement sensor 6 transmits the rotation angle information of the drive motor 5 and the differential angle of attack sensor to the display controller.

[0014] In this embodiment, the drive motor 5 can drive in both forward and reverse directions, and the direction of the drive motor 5 is independently adjustable; it can drive the differential angle-of-attack sensors 2 on both sides of the aircraft fuselage 1 to rotate simultaneously at a set speed, with one or more speed levels to meet different test requirements; it can drive the differential angle-of-attack sensors 2 to rotate within a certain range; it can rotate the differential angle-of-attack sensors 2 simultaneously or individually to a set angle and stop. The angular displacement sensor 6 can measure the rotation angle of the differential angle-of-attack sensors 2 and feed back the angle signal to the display controller.

[0015] In this embodiment, the display controller 3 has a human-machine interface; it can control the two drive motors 5 to rotate and stop synchronously; it can control the drive motors 5 to rotate and stop individually to verify the angle of attack comparison alarm function; it can display the rotation angle x of the angular displacement sensor; it has the angular displacement sensor angle zeroing function; it can calculate the rotation angle x of the angular displacement sensor to obtain the fuselage angle of attack sensor angle Y (Y=ax+b) and display it, where the values ​​of a and b can be manually input.

[0016] In the embodiment, the clamp 7 is used to fix the differential pressure angle sensor 2; the driving motor 5 can drive the clamp to rotate, thereby driving the differential pressure angle sensor 2 to rotate; the clamp 7 is mechanically connected with the driving motor 5 and the support, thereby avoiding the force acting on the differential pressure angle sensor 2; and the material fixed with the differential pressure angle sensor 2 is made of soft rubber material and can be attached to the differential pressure angle sensor 2.

[0017] In the embodiment, the driving motor 5 and the clamp 7 are placed on the support 8, the height of the support 8 can be adjusted within a certain range; the support 8 is stably supported on the ground; and the driving motor 5 and the clamp 8 can be fixed, and the height (up and down adjustment) and the horizontal lateral position (left and right adjustment) of the driving motor 5 and the clamp 7 can be adjusted by adjusting the horizontal supporting surface of the support 8; the pitch angle and the roll angle between the driving motor 5, the clamp 7 and the support can be adjusted, thereby avoiding the force acting on the differential pressure angle sensor 2.

[0018] The test cable 4 is used to connect the display controller with the driving motor 5 and the angle displacement sensor and transmit data.

[0019] When the differential pressure angle sensor of the airplane is tested, one driving motor 5 is connected with one differential pressure angle sensor 2 on each side of the airplane body 1 through the clamp 7; one angle displacement sensor 6 is connected with the rotating shaft of each driving motor 5; the two driving motors 5 on the two sides are controlled by one display controller 4 through the test cable 4; the rotating angle information of the driving motor 5 is transmitted to the display controller 2 through the test cable 4 by the angle displacement sensor 6 on the two sides; the current angle signal of the differential pressure angle sensor 2 is read through the man-machine interface of the display controller 4; the angle signal of the airplane itself is read by the ARINC429 reader 9; and the display controller 4 adjusts the angle of the differential pressure angle sensor 2 to zero according to the angle signal of the airplane itself.

[0020] When the stall warning function is tested, the two driving motors 5 can be controlled by the display controller 4 to drive the two differential pressure angle sensors 2 to rotate to the warning angle synchronously, thereby detecting whether the stall warning system on the airplane is normal.

[0021] When the comparison warning function is tested, one driving motor 5 can be controlled by the display controller 4 to drive one differential pressure angle sensor 2 to rotate alone, and the other driving motor 5 and the differential pressure angle sensor 2 remain unchanged; when the included angle between the two differential pressure angle sensors 2 reaches the comparison warning angle, whether the comparison warning function on the airplane is normal is detected.

[0022] In the embodiment, two differential pressure angle sensors 2 are fixed by the clamp 7. The current angle value is read on the display controller 4, the rotating angle is set, the clamp 7 and the differential pressure angle sensor 2 are rotated to the set angle by the driving motor 5, and the stall warning function and the angle comparison warning function are checked. The differential pressure angle sensor 2 is rotated to zero by reading the angle on the AIRNC429, the measurement value of the current angle displacement sensor 6 is zeroed, the a and b values of the aircraft are set, and whether the aircraft body angle meets the requirements is checked.

[0023] Figure 2 The embodiment shown is a differential pressure angle sensor warning test device for an aircraft, which comprises a display controller 3, two test cables 4, two driving motors 5, two sets of clamps 7 and angle displacement sensors 6, and two supports 8. The specific test process is as follows:

[0024] First, the installation and adjustment of the differential pressure angle sensor warning test device are performed: after the aircraft is parked in place, the supports 8 are placed beside the differential pressure angle sensors 2 on both sides of the aircraft body 1, the supports 8 can be adjusted within the range of 1500mm-1900mm and can be firmly fixed to the ground. The driving motor 5 is installed on the horizontal supporting surface of the support 8, which can be adjusted up and down within the range of 100mm and left and right. The clamp 7 is coaxially connected to the driving motor 5, the pitch angle between the clamp 7 and the support 8 is 5°, and can be adjusted within the range of 15° up and down and 15° left and right. The position of the support 8 and the angle of the clamp are adjusted, the differential pressure angle sensor 2 is clamped by the clamp 7, and the display controller 3 is connected with the driving motor 5 and the angle displacement sensor 6 by the test cable 4 for signal transmission and reception.

[0025] The test of the device for testing the differential pressure angle sensor of an airplane is as follows: a touch screen is provided on the display controller 3, and whether the driving motor 5 rotates synchronously can be set; the angle (-30°-40°) and speed (0.5° / s or 1.0° / s) of the rotation of each differential pressure angle sensor 2 can be set; the measured angle of the angle displacement sensor 6 is received; the angle information of the differential pressure angle sensor 2 on the airplane body 1 is displayed; and the variable values a and b of the angle of attack of the airplane body are set. After the power supply of the airplane is turned on, the angle information of the differential pressure angle sensor 2 is read by the ARINC429 reader 9 connected with the interface of the airplane itself, the two differential pressure angle sensors 2 can be controlled to rotate to zero position by the display controller 3, the mechanical zero position of the differential pressure angle sensor 2 is found by clicking the zero reset button on the display controller 3, the angle of attack information is read by the ARINC429 reader 9 connected with the interface of the airplane itself, and whether the angle of attack value of the airplane body is consistent with the expected value is checked. The two driving motors 5 are set to rotate synchronously by the display controller 3, the angles of attack of the two driving motors 5 are set to be less than, equal to and greater than the warning angle of attack respectively, and the stall warning function is verified; the two driving motors 5 are set to rotate respectively or one driving motor 5 is set to rotate alone to a comparative warning angle by the display controller 3, and the angle of attack comparison warning function is verified.

Claims

1. A test device for an aircraft differential pressure angle-of-attack sensor alarm, wherein the differential pressure angle-of-attack sensor is installed on both sides of the aircraft and is connected to a stall warning system, characterized in that, The testing device includes a drive motor, a display controller, and a fixture. The fixture is matched with a differential pressure angle-of-attack sensor and can hold and fix the differential pressure angle-of-attack sensor. The rotating shaft of the drive motor is connected to the fixture, and an angular displacement sensor is connected to the rotating shaft of the drive motor. The drive motor drives the fixture and the differential pressure angle-of-attack sensor to rotate, and the angular displacement sensor transmits the rotation angle information to the display controller.

2. The aircraft differential pressure angle-of-attack sensor alarm test device as described in claim 1, characterized in that, An ARINC429 reader is used to read angle information from the aircraft itself and the differential angle of attack sensor.

3. A test method for alarming aircraft differential pressure angle-of-attack sensors, characterized in that... The system includes the following components: 1) A drive motor is connected to the differential angle-of-attack sensors on both sides of the aircraft via clamps. An angular displacement sensor is connected to the rotation shaft of each drive motor. The drive motors on both sides are controlled by a display controller, and the angular displacement sensors transmit the rotation angle information of the drive motors to the display controller respectively; 2) The current angle signal of the differential angle-of-attack sensor is read through the human-machine interface of the display controller. The angle information of the aircraft itself and the differential angle-of-attack sensors is read by the ARINC429 reader. The display controller then adjusts the angle information based on the aircraft's own angle and the differential angle-of-attack sensor's angle. 3) When testing the stall alarm function, the display controller can control the two drive motors to drive the two differential angle sensors to rotate synchronously to the alarm angle, and check whether the stall alarm system on the machine is working properly; 4) When testing the comparison alarm function, the display controller can control one drive motor to drive one differential angle sensor to rotate independently, while the other drive motor and differential angle sensor remain stationary. When the angle between the two differential angle sensors reaches the comparison alarm angle, check whether the comparison alarm function on the machine is working properly.

4. The alarm test method for aircraft differential pressure angle-of-attack sensor as described in claim 3, characterized in that, In step 1), a bracket is set up near the differential angle of attack sensors on both sides of the aircraft, and the drive motor and clamp are placed on the bracket to ensure that the central axis of the differential angle of attack sensor is matched with the drive motor and clamp.

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