Non-contact aircraft control system deflection measurement system

Abstract

This invention discloses a non-contact aircraft control system deflection angle measurement system for measuring and displaying the deflection angle of the aircraft control system. The system includes: a display and control device for displaying the deflection information of the measured object within the aircraft control system; a sensing device wirelessly connected to the display and control device for sensing the deflection angle of the measured object rotating around a fixed axis, obtaining a deflection signal; and a dedicated clamping device, detachably connected to the measured object and detachably connected to the sensing device. The sensing device is mounted on the measured object within the aircraft control system using the dedicated clamping device. During the rotation of the measured object around the fixed axis, the sensing device measures the angle of deflection, obtaining a deflection signal, and transmits the deflection signal to the display and control device. The display and control device calculates the deflection signal and presents the deflection information, providing accurate data for static adjustments of the aircraft control system, meeting the requirements of flight parameter channel calibration, and adapting to complex measurement environments.

Description

Technical Field

[0001] This invention relates to the field of measurement technology for non-contact aircraft control systems, and more particularly to an angle measurement system for non-contact aircraft control systems. Background Technology

[0002] The control system of a non-contact aircraft is an important control mechanism for controlling the aircraft's flight trajectory and attitude, and is especially crucial for the smooth flight of the aircraft in complex flight environments.

[0003] Chinese Patent No. CN202221872444.0 discloses a deflection angle measuring device for an aircraft control system, comprising a clamp and a sensor. The clamp is used for quick clamping of the sensor to the part to be detected and for adjusting the sensor's measuring angle. The sensor is detachably connected to the clamp. This combination of clamp and sensor results in a simple structure, quick installation, and convenient adjustment. The clamp can adapt to different control surface curvatures. After the clamp clamps the control surface, the sensor connected to the clamp can adjust its deflection angle according to the control surface axis. Simultaneously, an internal tilt sensor measures the angle in real time and displays the result on a circuit board, providing real-time measurement data, high accuracy, and intuitive and convenient readings. However, this deflection measurement device only measures the deflection angle of the control surfaces of traditional aircraft. For non-contact aircraft control systems that operate in complex environments, static adjustments to the control system require simulating complex environments to measure the deflection angle. For example, there are many aircraft types, many sticks, surfaces, and positions to be measured, and many installation locations with complex environments. This technology cannot meet the measurement requirements and is difficult to provide accurate data for the calibration of flight parameter channels.

[0004] Therefore, existing technologies are insufficient to meet the needs of overhaul shops in complex environments for static adjustments of aircraft control systems and calibration of flight parameter channels, and are also insufficient for angle measurement in complex environments. Summary of the Invention

[0005] To address the aforementioned problem of difficulty in measuring the deflection angle in complex environments, this invention provides a deflection angle measurement system for non-contact aircraft control systems. This system uses a display and control device, a sensing device, and a dedicated fixture to collaboratively measure the deflection angle of the non-contact aircraft control system.

[0006] To achieve the above objectives, the present invention is implemented through the following technical solution:

[0007] A non-contact aircraft control system deflection measurement system, used to measure and display the deflection angle of the aircraft control system, including:

[0008] The display and control device is used to display the deflection information of the object under test in the aircraft control system.

[0009] The sensing device is wirelessly connected to the display and control device to sense the deflection angle of the object under test rotating around a fixed axis and obtain the deflection signal.

[0010] A special clamping device is detachably connected to the object under test and detachably connected to the sensing device. It is used to clamp the sensing device onto the object under test, which includes the horizontal stabilizer, rudder, joystick, and pedals of a non-contact aircraft control system.

[0011] Compared with the prior art, the present invention has the following advantages:

[0012] The sensing device is mounted on the object under test on the aircraft control system using a specialized fixture. As the object rotates around a fixed axis, the sensing device measures the angle of deflection, obtaining a deflection signal, which is then transmitted to the display and control device. The display and control device calculates the deflection signal to obtain deflection information and displays it, providing accurate data for static adjustments to the aircraft control system, meeting the requirements of flight parameter channel calibration, and adapting to complex measurement environments.

[0013] More preferably, the display and control device includes:

[0014] The main computer communicates with the sensing device and is used to receive deflection signals through its internal wireless transceiver module and calculate deflection information through algorithms. It is also used to display the deflection information in real time.

[0015] The auxiliary computer is connected to the main computer and is used to receive deflection information through the wireless pass-through module and display the deflection information in real time.

[0016] Using the above technical solution, the main computer calculates the deflection angle of the object under test, displays the deflection information, and transmits the deflection information to the auxiliary computer for real-time display, providing accurate data for static debugging of the aircraft control system.

[0017] More preferably, the dedicated clamping device includes:

[0018] Control surface clamps are used to hold the horizontal stabilizer and rudder of non-contact aircraft, and are detachably connected to the sensing device for mounting the sensing device on the horizontal stabilizer or rudder.

[0019] A stick clamp, which is attached to the control stick on a non-contact aircraft, is detachably connected to the sensing device and is used to mount the sensing device on the control stick.

[0020] An arc-shaped clamp, mounted on the pedals, is detachably connected to the sensing device and is used to connect the sensing device to the pedals.

[0021] By adopting the above technical solution, the deflection angle of different objects on the aircraft control system can be measured to meet the measurement needs of different positions of multiple aircraft types, sticks, and surfaces. This makes the entire special fixture device versatile and highly applicable to meet complex measurement environments.

[0022] More preferably, the rudder surface fixture includes:

[0023] First support.

[0024] The first clamping arm is mounted on the first bracket, with one end movably connected to the side wall of the first bracket, and is used to cooperate with the first bracket to clamp the horizontal stabilizer and rudder.

[0025] The first anti-slip pad is set on the surface of the first bracket and fixed to the other end of the first clamping arm.

[0026] The second anti-slip pad is disposed on the inner wall of the first clamping arm and is fixedly connected to the inner wall. The first anti-slip pad, the second anti-slip pad, the first bracket and the first clamping arm form a first clamping cavity, which is used to place the horizontal tail or rudder surface.

[0027] By adopting the above technical solution and connecting it with the object under test, which has a horizontal tail or rudder surface, the sensing device is indirectly installed on the object under test, thereby realizing the measurement of the deflection angle of the object under test.

[0028] Further optimizations include the following for the control surface fixture:

[0029] The first locking member is disposed on the first bracket and rotatably connected to the first bracket. One end of the member passes through the upper part of the first bracket and abuts against the upper part of the first clamping arm, while the other end extends to the outside of the first bracket.

[0030] The first connector is mounted on the first bracket, located at the lower part of the first bracket, and is fixedly connected to the outer wall of the first bracket. Its end is detachably connected to the sensing device.

[0031] Using the above technical solution, the sensing device is connected to the rudder surface clamp via the first connector, and the first locking member is rotated to clamp the horizontal stabilizer or rudder surface in the first clamping cavity, so that the sensing device can measure the deflection angle of the horizontal stabilizer or rudder.

[0032] Further optimized, the pole-mounting device includes:

[0033] Second support.

[0034] The second clamping arm is mounted on the second bracket, with one end hinged to one end of the second bracket, and is used to clamp the control lever between the clamping arm and the second bracket.

[0035] The third anti-slip pad is adhered to the surface of the second bracket opposite the position of the second clamping arm.

[0036] The fourth anti-slip pad is fixed to the second clamping arm and is positioned opposite to the third anti-slip pad. Together with the third anti-slip pad, the second clamping arm, and the first bracket, it forms a second clamping cavity, which is used to clamp the control lever.

[0037] By adopting the above technical solution, a third anti-slip pad is set to increase the friction between the second support and the control stick surface, and a fourth anti-slip pad is set to increase the friction between the second clamping arm and the control stick, so as to prevent damage to the control stick surface during the measurement process. The second support and the second clamping arm form a clamp body suitable for measuring the control stick deflection angle, which has wide applicability.

[0038] Further optimization includes the following:

[0039] The second locking element is disposed in the second clamping arm and is rotatably connected to the second clamping arm. One end of the locking element passes through the second clamping arm and extends into the first bracket.

[0040] The first connecting seat is disposed on the second bracket and located at the end of the second bracket. Its end extends into the second bracket and abuts against the second locking member, and is used to assist the second locking member in fixing the relative position of the second clamping arm and the second bracket.

[0041] The first connector is fixed to the bottom of the second connector and can be detached from and connected to the sensing device.

[0042] The positioning rod is set in the second clamping arm and rotatably connected to the second clamping arm. It is located on one side of the second locking member, with one end extending to one side of the second clamping arm and the other end passing through the second clamping arm and abutting against the inside of the second bracket. It is used to lock the operating lever between the second clamping arm and the second bracket by rotation.

[0043] By adopting the above technical solution, the control lever is positioned and installed through the second locking member, the first connecting seat, the first connecting head and the positioning rod, thereby indirectly connecting the sensing device and the control lever together, which facilitates accurate measurement of the control lever's deflection angle.

[0044] Further optimized, the bow-shaped clamp includes:

[0045] The third support.

[0046] The third clamping arm is vertically mounted on the third bracket and integrally connected to the end of the third bracket.

[0047] The foot pedal pad, shaped like an inverted V, is mounted on the third clamp arm and fixed to the surface of the third clamp arm to bear the force of stepping on the foot.

[0048] The third locking element is installed on the third bracket, with one end located on one side of the third bracket and the other end passing through the third bracket and located between the third bracket and the third clamping arm.

[0049] The clamping platform is located below the third clamping arm. Its bottom is fixed to the top of the third locking member, and its upper part is separated from the third clamping arm. The foot pedal is clamped between the clamping platform and the third locking member.

[0050] Using the above technical solution, the pedal can be clamped and fixed by the third bracket, the third clamping arm, the third locking member and the clamping platform. The pedal pad simulates the pedal bearing the force of the foot and deflects, which makes it easy for the sensing device to measure the deflection angle of the pedal.

[0051] Further optimizations include the following:

[0052] The second connecting seat is located on the third clamping arm, and its end is fixedly connected to the side wall of the third clamping arm.

[0053] The third connector is located on the second connector, with one end detachably connected to the sensing device and the other end fixedly connected to the second connector.

[0054] Using the above technical solution, the second connector and the third connector sensing device are indirectly connected to the pedal, ensuring that the sensing device accurately measures the pedal's deflection angle.

[0055] Further optimized, the sensing device includes: a first angle measuring sensor, a second angle measuring sensor, and a third angle measuring sensor, all of which are communicatively connected to the host computer.

[0056] The first, second, and third angle sensors are all provided with mounting holes, which are detachably connected to the rudder surface clamp, the support rod clamp, and the bow clamp.

[0057] The above technical solution is used to measure the deflection angle generated during the rotation of different objects. Attached Figure Description

[0058] Figure 1 This is a schematic diagram of the measurement principle block structure in this embodiment.

[0059] Figure 2 This is a schematic diagram of the rudder surface fixture in this embodiment.

[0060] Figure 3 This is a schematic diagram of the support rod clamp in this embodiment.

[0061] Figure 4 This is a schematic diagram of the bow-shaped clamp in this embodiment.

[0062] Figure 5 This is a schematic diagram of the sensing device in this embodiment.

[0063] Figure 6 This is a screenshot of the interface of the main computer in this embodiment.

[0064] Figure 7 This is a diagram showing the interface of the auxiliary computer in this embodiment.

[0065] Reference numerals: 1-Display and control device; 11-Main computer; 12-Auxiliary computer; 2-Clamping device; 21-Rudder surface clamp; 211-First bracket; 212-First clamping arm; 213-First anti-slip pad; 214-Second anti-slip pad; 215-First locking element; 216-First connector; 22-Stick clamp; 221-Second bracket; 222-Second clamping arm; 223-Third anti-slip pad; 224-Fourth anti-slip pad; 225-Second locking element Components; 226-Second connector; 227-First connector; 228-Positioning rod; 23-Arch-shaped clamp; 231-Third bracket; 232-Third clamping arm; 233-Foot pad; 234-Clamping platform; 235-Third locking component; 236-Third connector; 237-Second connector; 3-Sensing device; 31-First angle sensor; 32-Second angle sensor; 33-Third angle sensor; 34-Antenna; 35-Mounting hole. Detailed Implementation

[0066] The following is in conjunction with the appendix Figures 1-7 The present invention will be described in further detail below.

[0067] Non-contact aircraft control system deflection measurement system, such as Figure 1 As shown, the measurement and display of the aircraft control system's deflection angle includes:

[0068] Display and control device 1 is used to display the deflection information of the object under test in the aircraft control system.

[0069] The sensing device 3 is wirelessly connected to the display and control device 1 and is used to sense the deflection angle of the measured object rotating around a fixed axis to obtain the deflection signal.

[0070] The special clamping device 2 is detachably connected to the object under test and detachably connected to the sensing device 3. It is used to clamp the sensing device 3 onto the object under test, which includes the horizontal stabilizer, rudder, control stick and pedals on a non-contact aircraft control system.

[0071] The sensing device 3 is mounted on the object under test on the aircraft control system using a dedicated clamping device 2. As the object rotates around a fixed axis, the sensing device 3 measures the angle of deflection, obtaining a deflection signal, which is then transmitted to the display and control device 1. The display and control device 1 calculates the deflection signal to obtain deflection information and displays it, providing accurate data for static adjustments to the aircraft control system, meeting the requirements of flight parameter channel calibration, and adapting to complex measurement environments.

[0072] Specifically, such as Figure 1 As shown, the display and control device 1 in this embodiment includes:

[0073] The main computer 11, communicatively connected to the sensing device 3, receives deflection signals via its internal wireless transceiver module and calculates deflection information using an algorithm. It also displays the deflection information in real time. It should be noted that the wireless transceiver module is existing technology and is directly applied in this invention. The interface of the main computer 11 allows selection of the object being measured, such as the horizontal stabilizer, rudder, front flap, and control stick. Figure 6 As shown, the parameters measured by the sensing device 3 are also displayed in real time.

[0074] The auxiliary computer 12, which is communicatively connected to the main computer 11, is used to receive deflection information through a wireless transparent transmission module and display the deflection information in real time, such as... Figure 7 As shown, the deflection angle of the object being measured is displayed on the interface of the auxiliary computer 12.

[0075] The main computer 11 calculates the deflection angle of the object under test, displays the deflection information, and transmits the deflection information to the auxiliary computer 12 for real-time display, providing accurate data for static debugging of the aircraft control system.

[0076] Specifically, such as Figure 1 , Figure 2 , Figure 3 as well as Figure 4 As shown, the dedicated clamping device 2 in this embodiment includes:

[0077] The control surface clamp 21 is clamped on the horizontal stabilizer and rudder of the non-contact aircraft and is detachably connected to the sensing device 3 for mounting the sensing device 3 on the horizontal stabilizer or rudder.

[0078] The stick clamp 22 is clamped onto the control stick on the non-contact aircraft and is detachably connected to the sensing device 3 for mounting the sensing device 3 onto the control stick.

[0079] The bow-shaped clamp 23 is mounted on the pedal and is detachably connected to the sensing device 3, used to connect the sensing device 3 to the pedal.

[0080] It enables the measurement of the deflection angle of different objects on the aircraft control system, so as to meet the measurement needs of different positions of multiple aircraft types, sticks, and surfaces. This makes the entire special fixture device 2 versatile and highly applicable, so as to meet the needs of complex measurement environments.

[0081] Specifically, such as Figure 2 As shown, the rudder surface clamp 21 in this embodiment includes:

[0082] The first bracket 211 is L-shaped and is connected to the bottom surface of the horizontal stabilizer or rudder.

[0083] The first clamping arm 212 is mounted on the first bracket 211, with one end movably connected to the side wall of the first bracket 211, and is used to cooperate with the first bracket 211 to clamp the horizontal tail and rudder.

[0084] The first anti-slip pad 213 is disposed on the surface of the first bracket 211 and fixedly connected to the other end of the first clamping arm 212.

[0085] The second anti-slip pad 214 is disposed on the inner wall of the first clamping arm 212 and is fixedly connected to the inner wall. The first anti-slip pad 213, the second anti-slip pad 214, the first bracket 211 and the first clamping arm 212 form a first clamping cavity, which is used to place the horizontal tail or rudder surface.

[0086] This allows for connection with a test object having a horizontal stabilizer or rudder surface. Specifically, the first clamping arm 212 is rotated so that it is offset from the first support 211, creating a significant distance between them. This distance is sufficient to place the test object onto the first support 211. Then, the first clamping arm 212 is rotated back to hold the test object within the first clamping cavity, causing the first anti-slip pad 213 and the second anti-slip pad 214 to contact different surfaces of the test object. This indirectly clamps the sensing device 3 onto the test object, enabling the measurement of the deflection angle of the test object.

[0087] Specifically, such as Figure 2 As shown, the rudder surface fixture 21 in this embodiment further includes:

[0088] The first locking member 215 is disposed on the first bracket 211 and rotatably connected to the first bracket 211. One end of the locking member passes through the upper part of the first bracket 211 and abuts against the upper part of the first clamping arm 212, while the other end extends to the outside of the first bracket 211.

[0089] The first connector 216 is disposed on the first bracket 211, located at the lower part of the first bracket 211, and is fixedly connected to the outer side wall of the first bracket 211. Its end is detachably connected to the sensing device 3.

[0090] After being pre-connected to the sensing device 3 via the first connector 216, the first locking member 215 is rotated and the first clamping arm 212 is pressed against the first anti-slip pad 213, thus clamping the object to be measured in the first clamping cavity. Therefore, the sensing device 3 is connected to the rudder surface clamp 21 via the first connector 216, and the first locking member 215 is rotated to clamp the horizontal stabilizer or rudder surface in the first clamping cavity, thus completing the clamping and installation of the object to be measured and preparing for measuring the deflection angle of the horizontal stabilizer or rudder.

[0091] Specifically, such as Figure 3 As shown, the pole-mounted device in this embodiment includes:

[0092] The second bracket 221 is J-shaped and connected to the control lever.

[0093] The second clamping arm 222 is mounted on the second bracket 221, with one end hinged to one end of the second bracket 221, and is used to clamp the control lever between the arm and the second bracket 221.

[0094] The third anti-slip pad 223 is adhered to the surface of the second bracket 221 opposite to the position of the second clamping arm 222.

[0095] The fourth anti-slip pad 224 is fixed to the second clamping arm 222 and is positioned opposite to the third anti-slip pad 223. It forms a second clamping cavity with the third anti-slip pad 223, the second clamping arm 222 and the first bracket 211. The clamping cavity is used to clamp the control lever.

[0096] By setting a third anti-slip pad 223 to increase the friction between the second support 221 and the control stick surface, and a fourth anti-slip pad 224 to increase the friction between the second clamping arm 222 and the control stick, damage to the control stick surface is prevented during the measurement process. The second support 221 and the second clamping arm 222 form a clamping body suitable for measuring the control stick deflection angle, which has wide applicability.

[0097] Specifically, such as Figure 3 As shown, the pole-mounting device in this embodiment further includes:

[0098] The second locking member 225 is disposed in the second clamping arm 222 and is rotatably connected to the second clamping arm 222. One end of the locking member passes through the second clamping arm 222 and extends into the first bracket 211.

[0099] The first connecting seat 227 is disposed on the second bracket 221 and located at the end of the second bracket 221. Its end extends into the second bracket 221 and abuts against the second locking member 225, and is used to assist the second locking member 225 in fixing the relative position of the second clamping arm 222 and the second bracket 221.

[0100] The first connector 216 is fixed to the bottom of the second connector 237 and is detachably connected to the sensing device 3.

[0101] The positioning rod 228 is disposed in the second clamping arm 222 and rotatably connected to the second clamping arm 222. It is located on one side of the second locking member 225. One end of the rod extends to one side of the second clamping arm 222, and the other end passes through the second clamping arm 222 and abuts against the inside of the second bracket 221. It is used to lock the operating lever between the second clamping arm 222 and the second bracket 221 by rotation.

[0102] To connect the joystick, the process is as follows: First, rotate the second clamping arm 222 to open the second clamping cavity. Place the joystick on the third anti-slip pad 223, then rotate the second clamping arm 222 again to make the fourth anti-slip pad 224 contact the joystick, thus clamping the joystick in the second clamping cavity. Then, move and tighten the positioning rod 228 to make it contact the side wall of the joystick, preventing the joystick from shaking in the second clamping cavity. Rotate the second locking member 225 to press the second clamping arm 222 onto the joystick, completing the installation of the joystick. The joystick is positioned and installed using the joystick holder 22, thereby indirectly connecting the sensing device 3 to the joystick for accurate measurement of the joystick's deflection angle.

[0103] Specifically, such as Figure 3 As shown, the bow-shaped clamp 23 in this embodiment includes:

[0104] The third support 231 has an internal depression.

[0105] The third clamping arm 232 is vertically mounted on the third support 231 and integrally connected to the end of the third support 231. The upper part of the third clamping arm 232 has the same shape as the foot pedal and is inclined.

[0106] The foot pedal pad 233 is in the shape of an inverted V and is set on the third clamp arm 232 and fixed to the surface of the third clamp arm 232 to bear the force of stepping on the foot.

[0107] The third locking member 235 is disposed on the third bracket 231, with one end located on one side of the third bracket 231 and the other end passing through the third bracket 231 and located between the third bracket 231 and the third clamping arm 232.

[0108] The clamping platform 234 is located below the third clamping arm 232. Its bottom is fixed to the top of the third locking member 235, and its upper part is separated from the third clamping arm 232. The foot pedal is clamped between the clamping platform 234 and the third locking member 235.

[0109] This allows for connection to the pedals. Specifically, the clamping platform 234 is brought into contact with the bottom surface of the pedal, and the third locking member 235 is rotated to push the pedal towards the third clamping arm 232. Once the top surface of the pedal is in full contact with the third clamping arm 232, the third locking member 235 is tightened. The foot then deflects by stepping on the pedal pad 233. The pedals are clamped and fixed by the third bracket 231, the third clamping arm 232, the third locking member 235, and the clamping platform 234. The pedal pad 233 simulates the pedal bearing the force of the foot and deflects, facilitating the measurement of the pedal's deflection angle by the sensing device 3.

[0110] Specifically, such as Figure 3 As shown, the bow-shaped clamp 23 in this embodiment also includes:

[0111] The second connecting seat 237 is provided on the third clamping arm 232, and its end is fixedly connected to the side wall of the third clamping arm 232.

[0112] The third connector 236 is disposed on the second connector 237, with one end detached from the sensing device 3 and the other end fixedly connected to the second connector 237.

[0113] The second connector 237 and the third connector 236 are indirectly connected to the pedal, ensuring that the sensor 3 accurately measures the pedal's deflection angle.

[0114] Specifically, such as Figure 3 As shown, the sensing device 3 in this embodiment includes a first angle measuring sensor 31, a second angle measuring sensor 32, and a third angle measuring sensor 33, all of which are communicatively connected to the host computer 11. All three sensors are WJC-3A wireless angle measuring sensors.

[0115] Mounting holes 35 are provided on one side wall of the first angle measuring sensor 31, the second angle measuring sensor 32, and the third angle measuring sensor 33. The mounting holes 35 are detachably connected to the control surface clamp 21, the support rod clamp 22, and the bow-shaped clamp 23. An antenna 34 is connected to the other side wall. The antenna 34 is wirelessly connected to the main computer 11 to transmit the measured deflection signal to the main computer 11. When the first angle measuring sensor 31 is used to measure the horizontal stabilizer or control surface, it is mounted on the horizontal stabilizer or control surface through the control surface clamp 21; when the second angle measuring sensor 32 is used to measure the deflection angle of the control stick, it is connected to the control stick through the support rod clamp 22; when the third angle measuring sensor 33 is used to measure the deflection angle of the pedals, it is connected to the pedals through the bow-shaped clamp 23, thereby realizing the measurement and transmission of the deflection angle generated during the rotation of different measured objects.

[0116] Please combine Figures 1-7 The specific process for measuring the deflection angle of the object being measured is described as follows:

[0117] Using the horizontal stabilizer of the aircraft as the object of measurement, select "horizontal stabilizer" as the object of measurement on the main computer 11, and use sensor 1 on the interface for measurement, with the measurement axis being the X-axis.

[0118] Step 1: Install the horizontal stabilizer onto the control surface clamp 21, and then connect the first angle measuring sensor 31 to the control surface clamp 21.

[0119] Step 2: Perform system software operations on the main computer 11, specifically as follows:

[0120] Select basic information based on the actual situation. For example, in this case, select aircraft type XXX, aircraft number 10, flight number 01, and inspector Zhang Xiaoyi. Figure 6 As shown.

[0121] Select the object to be measured, the horizontal control surface measurement mode, and the measurement axis. Click the "Start" button to activate Sensor 1 window. Select the horizontal stabilizer as the object to be measured. At this point, the horizontal control surface measurement, measurement axis options, and axis tilt data are valid, while the vertical control surface measurement and azimuth coefficient data are invalid. Set the horizontal control surface measurement mode to angle and the measurement axis to the X-axis.

[0122] Step 3: Measurement

[0123] First, set the horizontal stabilizer to zero, then click the "Zero" button. The yaw angle and auxiliary parameters will both become 0, and the pivot angle data in the intermediate coefficients will be displayed in red. Figure 6 As shown, gently rotate the horizontal stabilizer until the shaft tilt angle data turns green (6), indicating that the shaft tilt angle calculation is complete and measurement work can begin. Measure and record point by point according to the requirements of the work card. During the measurement process, the main and auxiliary operators can coordinate their operations through the software. After the main operator completes the recording of a point, they need to proceed to the next step. Simply click the "Stabilize" button in the upper right corner of the interface; the button will change from red background with white text "Stabilize" to white background with red text "Next Point". After receiving the information from the main computer 11, the auxiliary computer 12 will synchronously display the relevant information and operate the horizontal stabilizer to the next point according to the requirements of the work card. Upon reaching the next point, the main operator sends a "Stabilize" signal through this button and records the data. After recording, the "Next Point" signal is sent again, and this process is repeated until all points have been measured according to the requirements of the work card.

[0124] This specific embodiment is merely an explanation of the invention and is not intended to limit the invention. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of protection of this invention, they are protected by patent law.

Claims

1. A non-contact aircraft control system deflection angle measurement system, used to measure and display the deflection angle of an aircraft control system, characterized in that, include: Display and control device (1) is used to display the deflection information of the object under test in the aircraft control system; The sensing device (3) is wirelessly connected to the display and control device (1) and is used to sense the deflection angle of the object under test rotating around a fixed axis to obtain a deflection signal. A special clamping device (2) is detachably connected to the object under test and detachably connected to the sensing device (3), used to clamp the sensing device (3) onto the object under test, which includes the horizontal stabilizer, rudder, control stick, and foot pedals of a non-contact aircraft control system; the special clamping device (2) includes: a control surface clamp (21), which is clamped on the horizontal stabilizer of the non-contact aircraft and detachably connected to the sensing device (3), used to install the sensing device (3) onto the horizontal stabilizer or rudder; a rod clamp (22), which is clamped on the control stick of the non-contact aircraft and detachably connected to the sensing device (3), used to install the sensing device (3) onto the control stick; and an arc-shaped clamp (23), which is installed on the foot pedal and detachably connected to the sensing device (3), used to install the sensing device (3) onto the control stick. The device (3) is connected to the foot pedal; the rudder clamp (21) includes: a first bracket (211); a first clamping arm (212), which is disposed on the first bracket (211), one end of which is movably connected to the side wall of the first bracket (211) for cooperating with the first bracket (211) to clamp the horizontal tail and the rudder; a first anti-slip pad (213), which is disposed on the surface of the first bracket (211) and fixedly connected to the other end of the first clamping arm (212); a second anti-slip pad (214), which is disposed on the inner wall of the first clamping arm (212) and fixedly connected to the inner wall, and a first clamping cavity is formed between the first anti-slip pad (213), the second anti-slip pad (214), the first bracket (211) and the first clamping arm (212), and the first clamping cavity is used to place the horizontal tail or the rudder; The bow-shaped clamp (23) includes: a third support (231); a third clamping arm (232), which is vertically disposed on the third support (231) and integrally connected to the end of the third support (231); and a second connecting seat (237), which is disposed on the third clamping arm (232) and whose end is fixedly connected to the side wall of the third clamping arm (232). The lever clamp (22) includes: a second bracket (221); a second clamping arm (222) disposed on the second bracket (221), one end of which is hinged to one end of the second bracket (221) for clamping the control lever between the lever and the second bracket (221); a third anti-slip pad (223) bonded to the surface of the second bracket (221) opposite to the position of the second clamping arm (222); and a fourth anti-slip pad (224) fixed to the second clamping arm (222), opposite to the position of the third anti-slip pad (223), forming a second clamping cavity with the third anti-slip pad (223), the second clamping arm (222), and the first bracket (211), the clamping cavity being used to clamp the control lever; The pole clamp (22) further includes: a second locking member (225), disposed in the second clamping arm (222), rotatably connected to the second clamping arm (222), one end of which passes through the second clamping arm (222) and extends into the first bracket (211); a first connecting seat (227), disposed on the second bracket (221), located at the end of the second bracket (221), the end of which extends into the second bracket (221) and abuts against the second locking member (225), for assisting the second locking member (225) in fixing the second clamping arm (222) and the second bracket (221). The relative positions of the two components are as follows: the second connector (226) is fixed to the bottom of the second connector (237) and is detachably connected to the sensing device (3); the positioning rod (228) is disposed in the second clamping arm (222) and rotatably connected to the second clamping arm (222), located on one side of the second locking member (225), with one end extending to one side of the second clamping arm (222) and the other end passing through the second clamping arm (222) and abutting against the inside of the second bracket (221), for using rotation to clamp the control lever between the second clamping arm (222) and the second bracket (221).

2. The deflection angle measurement system for a non-contact aircraft control system according to claim 1, characterized in that, The display and control device (1) includes: The main computer (11) is connected to the sensing device (3) for receiving the deflection signal through its internal wireless transceiver module and calculating the deflection information through an algorithm, and is also used to display the deflection information in real time. A secondary computer (12) is connected to the main computer (11) for receiving the deflection information through a wireless transparent transmission module and displaying the deflection information in real time.

3. The deflection angle measurement system for a non-contact aircraft control system according to claim 1, characterized in that, The rudder surface fixture (21) also includes: The first locking member (215) is disposed on the first bracket (211) and rotatably connected to the first bracket (211). One end of the locking member passes through the upper part of the first bracket (211) and abuts against the upper part of the first clamping arm (212). The other end extends to the outside of the first bracket (211). The first connector (216) is disposed on the first bracket (211), located at the lower part of the first bracket (211), and is fixedly connected to the outer side wall of the first bracket (211). Its end is detachably connected to the sensing device (3).

4. The deflection angle measurement system for a non-contact aircraft control system according to claim 1, characterized in that, The bow-shaped clamp (23) also includes: The foot pedal pad (233) is in the shape of an inverted V and is set on the third clamping arm (232) and fixed to the surface of the third clamping arm (232) to bear the force of stepping on the foot; The third locking member (235) is disposed on the third bracket (231), with one end located on one side of the third bracket (231) and the other end passing through the third bracket (231) and located between the third bracket (231) and the third clamping arm (232). A clamping platform (234) is located below the third clamping arm (232), with its bottom fixed to the top of the third locking member (235) and its upper part separated from the third clamping arm (232). The foot pedal is clamped between the clamping platform (234) and the third locking member (235).

5. The deflection angle measurement system for a non-contact aircraft control system according to claim 4, characterized in that, The bow-shaped clamp (23) also includes: The third connector (236) is disposed on the second connector (237), one end of which is detachably connected to the sensing device (3), and the other end is fixedly connected to the second connector (237).

6. The deflection angle measurement system for a non-contact aircraft control system according to claim 2, characterized in that, The sensing device (3) includes: a first angle sensor (31), a second angle sensor (32) and a third angle sensor (33), wherein the first angle sensor (31), the second angle sensor (32) and the third angle sensor (33) are all communicatively connected to the host computer (11); The first angle measuring sensor (31), the second angle measuring sensor (32) and the third angle measuring sensor (33) are all provided with mounting holes (35), and the mounting holes (35) are detachably connected to the rudder surface clamp (21), the support rod clamp (22) and the bow clamp (23).

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