An aircraft wheel brake dynamic verification system

Abstract

The application belongs to the field of aircraft wheel brake system verification, and particularly relates to an aircraft wheel brake dynamic verification system, which adds a signal adapter, a real-time simulation machine and a display device in a wheel brake test system, the real-time simulation machine is used for running an aircraft dynamics model, an input is a brake pressure signal, and an output is a wheel speed signal. The adapter is responsible for conversion of input and output signals of the real-time simulation machine, brake pressure of the brake system is input to the real-time simulation machine, wheel speed data output by the real-time simulation machine is converted into wheel speed simulation signals and sent to a brake control unit for wheel anti-skid control, so that aircraft wheel brake system dynamic verification of an aircraft level is realized.

Description

Technical Field

[0001] This application belongs to the field of aircraft wheel brake system verification, and specifically relates to an aircraft wheel brake dynamic verification system. Background Technology

[0002] The wheel braking system is used for ground braking and deceleration of aircraft and for directional assistance control, and is a critical system for ensuring the safety of aircraft takeoff and landing. During the development of aircraft wheel braking systems, dynamic verification is required for optimizing the system's anti-skid braking control law. Traditional verification methods for aircraft wheel braking systems include test bench verification and brake inertial bench dynamic verification. However, both verification methods have their own limitations. In test bench verification, the wheel speed signal is driven by a wheel speed drive device to drive the wheel speed sensor, but this can only simulate rapid changes in wheel speed and cannot simulate the wheel speed changes during actual aircraft braking. It can only verify the anti-skid function, and therefore cannot conduct aircraft-level dynamic verification of the braking system. Brake inertial bench verification simulates the initial speed and wheel load at the aircraft braking point using electrical inertia. However, the pavement contact coefficient differs significantly from the actual runway under various operating conditions. Adjusting the ground contact coefficient by adjusting the load is time-consuming and costly, making it impossible to conduct aircraft-level dynamic test verification. Only through aircraft flight testing can the dynamic verification of aircraft-level wheel braking be performed. Summary of the Invention

[0003] To address the aforementioned problems, this application provides an aircraft wheel brake dynamic verification system, comprising:

[0004] The wheel braking system includes a brake control device (1), a brake control unit (2), a brake valve (3) and a brake device (4) connected in sequence. The brake device (4) is used to simulate the braking load of a real wheel. A pressure sensor (6) is provided on the pipeline between the brake valve (3) and the brake device (4).

[0005] A real-time simulator (8) is used to run aircraft dynamics models;

[0006] The signal adapter (5) is connected to the pressure sensor (6) and the real-time simulator (8), respectively; and

[0007] The display device (7) is connected to the real-time simulator (8) and the brake control unit (2) respectively.

[0008] The brake control device (1) outputs a brake command signal to the brake control unit (2); the brake control unit (2) outputs a control signal to the brake valve (3); the pressure sensor (6) collects the brake pressure signal and sends it to the signal adapter (5); the signal adapter (5) converts the brake pressure signal into a digital signal and inputs it to the real-time simulator (8); the real-time simulator (8) calculates the wheel speed signal in the aircraft dynamics model based on the brake pressure signal and outputs the wheel speed signal to the brake control unit (2); the brake control unit (2) controls the brake valve (3) to perform brake anti-skid control based on the wheel speed signal; the real-time simulator (8) and the brake control unit (2) respectively send simulation data and system status data to the display device (7) for real-time display.

[0009] Preferably, the signal adapter (5) includes an A / D conversion module and a D / A conversion module;

[0010] The A / D conversion module is used to convert the brake pressure analog signal output by the pressure sensor (6) into a digital signal and transmit it to the real-time simulator (8).

[0011] The D / A conversion module is used to convert the digital signal of wheel speed output by the real-time simulator (8) into an analog signal and transmit it to the brake control unit (2).

[0012] Preferably, the signal adapter (5) is further equipped with a signal conditioning circuit for filtering, amplifying and linearizing the analog signal output by the pressure sensor (6) to match the input range of the A / D conversion module.

[0013] Preferably, the aircraft dynamics model in the real-time simulator (8) is configured as follows: the brake pressure signal is used as input, it is converted into a braking torque applied to the wheels, and the wheel speed signal is calculated and output by combining the six-degree-of-freedom motion equations of the aircraft and the ground contact coefficient.

[0014] Preferably, the aircraft dynamics model includes a six-degree-of-freedom aircraft model, an aircraft aerodynamic model, a landing gear model, an engine thrust model, and a tire ground mechanics model.

[0015] Preferably, the verification parameters of the aircraft dynamics model are configurable, and the verification parameters include at least the aircraft weight, center of gravity position, ground contact coefficient, initial braking speed, and airport altitude.

[0016] Preferably, the brake control unit (2) is configured to: receive the wheel speed signal, calculate the anti-skid control quantity based on a preset anti-skid control law, and adjust the duty cycle or current magnitude of the control signal output to the brake valve (3) accordingly, so as to achieve closed-loop regulation of the brake pressure.

[0017] Preferably, the brake control unit (2) has a built-in wheel slip ratio calculation module, which is used to calculate the real-time slip ratio based on the wheel speed signal and the aircraft body speed signal fed back by the real-time simulator (8), and to execute the anti-skid control law with the real-time slip ratio as the core variable.

[0018] Preferably, the braking system parameters displayed in real time by the display device (7) include braking command signal, braking valve control signal, braking pressure signal and wheel speed signal;

[0019] The display device (7) displays in real time the aircraft dynamics model parameters, including aircraft takeoff speed, taxiing distance, braking torque, wheel slip ratio and deceleration rate.

[0020] Preferably, the brake pressure signal collected by the pressure sensor (6) is also directly fed back to the brake control unit (2) for the brake control unit (2) to perform brake pressure monitoring, closed-loop pressure control and fault diagnosis.

[0021] Preferably, the data storage unit is communicatively connected to the real-time simulator (8) and the brake control unit (2) respectively, and is used to synchronously record all parameter data during the braking process, including brake pressure time series, wheel speed time series and aircraft dynamic response time series, so as to support data analysis and playback after the test.

[0022] Preferably, the real-time simulator (8) is also equipped with a real-time operating system and I / O interface board to ensure that the solution step size of the aircraft dynamics model is no more than 1ms, so as to meet the real-time verification requirements of the dynamic response of the wheel braking system.

[0023] Preferably, the braking device (4) is a physical wheel brake assembly, the brake valve (3) is a physical hydraulic servo valve or solenoid valve, and the system is configured as a semi-physical simulation verification system.

[0024] Preferably, the real-time simulator (8) supports online parameter adjustment, and the ground bonding coefficient can be dynamically adjusted without restarting the model during the verification process to simulate slippery conditions such as runway water accumulation, snow accumulation or ice formation.

[0025] Preferably, the system is also equipped with an emergency stop protection module. When the brake pressure signal exceeds a preset safety threshold or the real-time simulator (8) is in an abnormal operating state, the emergency stop protection module forcibly cuts off the output signal of the brake control unit (2) or releases the pressure in the brake device (4).

[0026] This application provides a dynamic verification system for aircraft wheel brakes. The wheel brake system uses a physical object and sends brake pressure data to the aircraft dynamics model in the real-time simulator 8 through a signal adapter 5 to perform wheel braking. The real-time simulator 8 sends wheel speed signals to the brake control unit 2 of the wheel brake system through the signal adapter 5. The brake control unit 2 outputs a control signal from the brake valve 3 according to the wheel speed signal to achieve brake anti-skid control, thereby achieving the purpose of dynamic verification of the aircraft wheel brake system. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of a dynamic verification system for aircraft wheel brakes according to this application. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. Figure 1 The purpose of this application is to provide a dynamic verification system for aircraft wheel brakes to overcome the above-mentioned problems.

[0029] The technical solution of this application is as follows: The wheel braking system includes a brake control device 1, a brake control unit 2, a brake valve 3, a brake device 4, and a brake pressure sensor 6. A signal adapter 5, a real-time simulator 8, and a display device 7 are added. The signal adapter converts the signal from the pressure sensor 6 into a digital quantity and sends it to the real-time simulator 8. The real-time simulator 8 runs an aircraft dynamics model and applies brakes to decelerate the aircraft according to the brake pressure. The wheel speed in the model is sent to the signal adapter 5 in real time through the real-time simulator 8. The signal adapter 5 converts the digital wheel speed into a wheel speed analog signal and sends it to the brake control unit 2. The brake control unit 2 controls the brake valve 3 to perform brake anti-skid control according to the wheel speed signal. At the same time, the brake system parameters and aircraft parameters are displayed dynamically in real time through the display device 7, thereby realizing dynamic verification of the aircraft-level aircraft braking system.

[0030] Preferably, the wheel braking system includes a brake control device 1, a brake control unit 2, a brake valve 3, a brake device 4, and a brake pressure sensor 6. The brake control unit 2 receives the brake command signal from the brake control device 1 and outputs a control signal to the brake valve 3. The brake valve 3 outputs brake pressure to the brake device 4 according to the control signal. The pressure sensor 6 detects the brake pressure and sends the signal to the brake control unit 2.

[0031] Preferably, a signal adapter 5, a real-time simulator 8, and a display device 7 are configured.

[0032] Preferably, the pressure sensor 6 sends the pressure signal to the signal adapter 5, and the signal adapter 5 converts the pressure signal into a digital quantity and sends it to the real-time simulator 8.

[0033] Preferably, the real-time simulator 8 runs an aircraft dynamics model, receives pressure data from the signal adapter 5, brakes the aircraft according to the wheel braking model, and outputs wheel speed data to the signal adapter 5.

[0034] Preferably, the signal adapter 5 converts the wheel speed data into an analog wheel speed signal and sends it to the brake control unit 2.

[0035] Preferably, the brake control unit 2 controls the brake valve 3 to perform brake anti-skid control based on the wheel speed signal.

[0036] Preferably, the real-time simulator 8 and the brake control unit 2 send the braking system and aircraft dynamics model parameters to the display device 7 for real-time display of the system status.

[0037] Preferably, the aircraft dynamics model running in the real-time simulator 8 should include: a six-degree-of-freedom aircraft model, a landing gear model, an aerodynamic model, a wheel brake model, etc., and the aircraft weight, center of gravity, ground contact coefficient and initial braking speed and other parameters can be adjusted according to the verification conditions.

[0038] This application has at least the following beneficial technical effects: It provides a dynamic verification system for aircraft wheel brakes. The wheel brake system uses a physical object and sends brake pressure data to the aircraft dynamics model in the real-time simulator 8 through the signal adapter 5 to perform wheel braking. The real-time simulator 8 sends wheel speed signals to the brake control unit 2 of the wheel brake system through the signal adapter 5. The brake control unit 2 outputs a brake valve 3 control signal according to the wheel speed signal to realize brake anti-skid control, thereby achieving the purpose of dynamic verification of the aircraft wheel brake system.

[0039] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A dynamic verification system for aircraft wheel brakes, characterized in that, include: The wheel braking system includes a brake control device (1), a brake control unit (2), a brake valve (3) and a brake device (4) connected in sequence. The brake device (4) is used to generate frictional braking torque in a controlled manner to simulate the braking load of a real wheel. A pressure sensor (6) is provided on the pipeline between the brake valve (3) and the brake device (4). A real-time simulator (8) is used to run aircraft dynamics models; The signal adapter (5) is connected to the pressure sensor (6) and the real-time simulator (8), respectively; and The display device (7) is connected to the real-time simulator (8) and the brake control unit (2) respectively. The brake control device (1) outputs a brake command signal to the brake control unit (2); the brake control unit (2) outputs a control signal to the brake valve (3); the pressure sensor (6) collects the brake pressure signal and sends it to the signal adapter (5); the signal adapter (5) converts the brake pressure signal into a digital signal and inputs it to the real-time simulator (8); the real-time simulator (8) calculates the wheel speed signal in the aircraft dynamics model based on the brake pressure signal and outputs the wheel speed signal to the brake control unit (2) through the signal adapter (5); the brake control unit (2) controls the brake valve (3) to perform brake anti-skid control based on the wheel speed signal; the real-time simulator (8) and the brake control unit (2) respectively send simulation data and system status data to the display device (7) for real-time display.

2. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The signal adapter (5) includes an A / D conversion module and a D / A conversion module; The A / D conversion module is used to convert the brake pressure analog signal output by the pressure sensor (6) into a digital signal and transmit it to the real-time simulator (8). The D / A conversion module is used to convert the digital signal of wheel speed output by the real-time simulator (8) into an analog signal and transmit it to the brake control unit (2).

3. The aircraft wheel brake dynamic verification system according to claim 2, characterized in that: The signal adapter (5) is also equipped with a signal conditioning circuit for filtering, amplifying and linearizing the analog signal output by the pressure sensor (6) to match the input range of the A / D conversion module.

4. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The aircraft dynamics model in the real-time simulator (8) is configured as follows: the brake pressure signal is used as input, and it is converted into a braking torque applied to the wheels. The wheel speed signal is calculated and output by combining the six-degree-of-freedom motion equations of the aircraft and the ground contact coefficient.

5. The aircraft wheel brake dynamic verification system according to claim 4, characterized in that: The aircraft dynamics model includes a six-degree-of-freedom aircraft model, an aircraft aerodynamic model, a landing gear model, an engine thrust model, and a tire-ground mechanics model.

6. The aircraft wheel brake dynamic verification system according to claim 5, characterized in that: The verification parameters of the aircraft dynamics model are configurable, and the verification parameters include at least the aircraft weight, center of gravity position, ground contact coefficient, initial braking speed, and airport altitude.

7. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The brake control unit (2) is configured to receive the wheel speed signal, calculate the anti-skid control quantity based on the preset anti-skid control law, and adjust the duty cycle or current of the control signal output to the brake valve (3) accordingly to achieve closed-loop regulation of the brake pressure.

8. The aircraft wheel brake dynamic verification system according to claim 7, characterized in that: The brake control unit (2) has a built-in wheel slip ratio calculation module, which is used to calculate the real-time slip ratio based on the wheel speed signal and the aircraft body speed signal fed back by the real-time simulator (8), and to execute the anti-skid control law with the real-time slip ratio as the core variable.

9. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The display device (7) displays the braking system parameters in real time, including the braking command signal, the braking valve control signal, the braking pressure signal, and the wheel speed signal. The display device (7) displays in real time the aircraft dynamics model parameters, including aircraft takeoff speed, taxiing distance, braking torque, wheel slip ratio and deceleration rate.

10. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The brake pressure signal collected by the pressure sensor (6) is also directly fed back to the brake control unit (2) for brake pressure monitoring, closed-loop pressure control and fault diagnosis.

11. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that, Also includes: The data storage unit is connected to the real-time simulator (8) and the brake control unit (2) respectively, and is used to synchronously record all parameter data during the braking process, including brake pressure time series, wheel speed time series and aircraft dynamic response time series, so as to support data analysis and playback after the test.

12. The aircraft wheel brake dynamic verification system according to claim 4, characterized in that: The real-time simulator (8) is also equipped with a real-time operating system and I / O interface board to ensure that the solution step size of the aircraft dynamics model is no more than 1ms, so as to meet the real-time verification requirements of the dynamic response of the wheel braking system.

13. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The braking device (4) is a physical wheel brake assembly, and the brake valve (3) is a physical hydraulic servo valve or solenoid valve. The system is configured as a semi-physical simulation verification system.

14. The aircraft wheel brake dynamic verification system according to claim 6, characterized in that: The real-time simulator (8) supports online parameter adjustment. During the verification process, the ground bonding coefficient can be dynamically adjusted without restarting the model to simulate slippery conditions such as runway water accumulation, snow accumulation, or ice formation.

15. The aircraft wheel brake dynamic verification system according to claim 1, characterized in that: The system is also equipped with an emergency stop protection module. When the brake pressure signal exceeds the preset safety threshold or the real-time simulator (8) is in an abnormal operating state, the emergency stop protection module forcibly cuts off the output signal of the brake control unit (2) or releases the pressure in the brake device (4).

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