High-reliability aircraft nose wheel turn system
By introducing ground speed signals and signal recognition and judgment modules into the turning control unit, the problem of only being able to turn at small angles when the aircraft wheel speed signals fail has been solved, enabling large-angle turns even when the wheel speed signals fail, thus improving the aircraft's mission reliability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
- Filing Date
- 2022-12-28
- Publication Date
- 2026-06-26
AI Technical Summary
In existing technologies, when the aircraft wheel speed signal fails, the aircraft can only make small-angle turns, resulting in low mission reliability.
By introducing a ground speed signal into the turning control unit, and combining it with a signal recognition, judgment module and a logic judgment module, the system switches to the ground speed signal to perform a large-angle control law switching logic when the aircraft wheel speed signal fails, ensuring that the front wheels can make large-angle turns.
It improves the aircraft's turning reliability when wheel speed signals fail, prevents the nose wheel turning system from being unable to make large-angle turns, and enhances the aircraft's mission reliability.
Smart Images
Figure CN115848618B_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the technical field of aircraft nose wheel steering systems, and specifically relates to a high-reliability aircraft nose wheel steering system. Background Technology
[0002] The basic components of an aircraft fly-by-wire steering control system are similar, mainly consisting of a turn command sensor, a turn control unit, a turn control valve, a turn actuator, and a turn angle feedback sensor. The turn control unit, as the control center of the steering system, collects turn command signals, feedback signals, and aircraft wheel signals to control the opening and closing of the turn control valve and the flow direction and magnitude of the hydraulic fluid. This, in turn, drives the nose wheel to rotate via the turn actuator, completing the aircraft turn.
[0003] The turning system incorporates aircraft wheel speed signals to switch between large and small angle control laws. At low speeds, the aircraft can make large-angle turns, while at high speeds, it can only make small-angle corrections. If the aircraft wheel speed signal fails, for safety reasons, the aircraft can only make small-angle corrections, resulting in lower mission reliability. Summary of the Invention
[0004] The purpose of this application is to provide a highly reliable aircraft nose wheel turning system to solve the problem in the prior art that when the aircraft wheel speed signal fails, the aircraft can only turn at a small angle.
[0005] The technical solution of this application is: a high-reliability aircraft nose wheel steering system, including a steering command sensor, a steering control valve, a steering control unit, a steering actuator, and a steering angle feedback sensor; the steering control valve is electrically connected between the steering control unit and the steering actuator, and the steering command sensor and the steering angle feedback sensor are both electrically connected to the steering control unit; it also includes a brake control unit and an integrated management computer, the steering control unit is electrically connected to the brake control unit and the integrated management computer, and the steering control unit receives aircraft wheel speed signals from the brake control unit and ground speed signals from the integrated management computer; after receiving both the aircraft wheel speed signals and the ground speed signals simultaneously, the steering control unit executes a switching logic for the large and small angle control laws based on the aircraft wheel speed signals; when it is determined that the aircraft wheel speed signals are invalid, it determines whether the received ground speed signals are valid; if valid, the steering control unit executes a switching logic for the large and small angle control laws based on the received ground speed signals.
[0006] Preferably, the turning control unit includes a signal recognition module, a signal judgment module, a logic judgment module, a memory, and a signal output module. The signal recognition module can receive and identify aircraft wheel speed signals and ground speed signals, and send the two different signals to the signal judgment module respectively. The signal judgment module can judge the aircraft wheel speed signals and ground speed signals separately and determine whether the corresponding signals are valid. The memory stores information on aircraft wheel speed signals and ground speed signals at different time points. The logic judgment module receives the signal from the signal judgment module and calls the stored information in the memory to determine whether to use the aircraft wheel speed signal or the ground speed signal to execute the large and small angle control law switching logic, or to perform small angle turn control. The signal output module receives the control execution from the logic judgment module and sends it to the signal output module.
[0007] Preferably, when the aircraft wheel speed signal recovers after a failure, the turning control unit still uses the ground speed signal to execute the size angle control law switching logic.
[0008] Preferably, when the ground speed signal recovers after a failure, if the aircraft wheel speed signal fails or recovers after a failure, the ground speed signal is used to execute the switching logic of the size angle control law.
[0009] Preferably, if both the aircraft wheel speed signal and the ground speed signal fail, the turn control unit performs a small-angle turn control on the aircraft.
[0010] Preferably, the turning control unit receives aircraft wheel speed signals from the brake control unit via a bus.
[0011] Preferably, the turning control unit receives the ground speed signal from the integrated management computer via a bus.
[0012] This application discloses a high-reliability aircraft nose wheel steering system, comprising a steering command sensor, a steering control valve, a steering control unit, a steering actuator, a steering angle feedback sensor, a brake control unit, and an integrated management computer. Upon simultaneously receiving aircraft wheel speed signals and ground speed signals, the steering control unit executes a switching logic for the large and small angle control laws based on the aircraft wheel speed signals. If the aircraft wheel speed signal is determined to be invalid, the system checks the validity of the received ground speed signal. If valid, the steering control unit executes the switching logic for the large and small angle control laws based on the received ground speed signal. By simultaneously using both aircraft wheel speed and ground speed signals, even when the aircraft wheel speed signal fails, the ground speed signal can still be used to control the nose wheel to make large-angle turns, preventing the nose wheel steering system from failing to make large-angle turns when the aircraft wheel speed signal fails, thus improving the aircraft's mission reliability. Attached Figure Description
[0013] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.
[0014] Figure 1 This is a schematic diagram of the overall structure of this application;
[0015] Figure 2 This is the overall control flowchart for this application.
[0016] 1. Turning command sensor; 2. Turning control valve; 3. Turning control unit; 4. Turning actuator; 5. Turning angle feedback sensor; 6. Brake control unit; 7. Integrated management computer. Detailed Implementation
[0017] 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.
[0018] A highly reliable aircraft nose wheel steering system, such as Figure 1-2 As shown, it includes a turning command sensor 1, a turning control valve 2, a turning control unit 3, a turning actuator 4, a turning angle feedback sensor 5, a brake control unit 6, and a comprehensive management computer 7; the turning control valve 2 is electrically connected between the turning control unit 3 and the turning actuator 4, and the turning command sensor 1 and the turning angle feedback sensor 5 are both electrically connected to the turning control unit 3.
[0019] The turning control unit 3 is electrically connected to the brake control unit 6 and the integrated management computer 7. The turning control unit 3 receives the aircraft wheel speed signal from the brake control unit 6 and the ground speed signal from the integrated management computer 7.
[0020] The turning command sensor 1 is used to collect turning command data, and the turning angle feedback sensor is used to collect turning angle information.
[0021] The turning control unit 3 calculates the front wheel deflection angle required to achieve the target turning angle by receiving data from the turning command sensor 1, the turning angle feedback sensor 5, and the aircraft wheel speed and ground speed signals.
[0022] The turning control valve 2 receives the control command from the turning control unit 3 and controls the turning actuator 4 to complete the deflection of the front wheels.
[0023] After receiving both the aircraft wheel speed signal and the ground speed signal, the turning control unit 3 executes the switching logic of the large and small angle control law based on the aircraft wheel speed signal. When it is determined that the aircraft wheel speed signal is invalid, it determines whether the received ground speed signal is valid. If it is valid, the turning control unit 3 executes the switching logic of the large and small angle control law based on the received ground speed signal.
[0024] By simultaneously referencing both aircraft wheel speed signals and ground speed signals, even if the aircraft wheel speed signal fails, the ground speed signal can still be used to control the nose wheel to make large-angle turns. This prevents the nose wheel steering system from being unable to make large-angle turns when the aircraft wheel speed signal fails, thus improving the aircraft's mission reliability.
[0025] The aforementioned switching logic for the large and small angle control law means that small-angle turns are performed at high speeds, and large-angle turns are performed at low speeds.
[0026] Preferably, the turning control unit 3 includes a signal recognition module, a signal judgment module, a logic judgment module, a memory, and a signal output module. The signal recognition module can receive and recognize aircraft wheel speed signals and ground speed signals, and send the two different signals to the signal judgment module respectively. The signal judgment module can judge the aircraft wheel speed signals and ground speed signals separately and determine whether the corresponding signals are valid. The memory stores information on aircraft wheel speed signals and ground speed signals at different time points. The logic judgment module receives the signals from the signal judgment module and calls the stored information in the memory, thereby being able to read whether there is any failure information and determine whether to use the aircraft wheel speed signal or the ground speed signal to execute the large and small angle control law switching logic, or to perform small angle turn control. The signal output module receives the control execution from the logic judgment module and sends it to the signal output module.
[0027] By identifying and logically judging the two signals separately, it is possible to accurately determine whether the aircraft wheel speed signal and ground speed signal are invalid, and whether the aircraft wheel speed signal and ground speed signal have been invalid. It is also possible to determine which data are needed for control commands, so that accurate control commands can be generated through logical judgment to efficiently control the turning actuator 4.
[0028] Preferably, when the aircraft wheel speed signal recovers after a failure, the turning control unit 3 still uses the ground speed signal to execute the switching logic of the large and small angle control law to ensure stable control.
[0029] Preferably, when the ground speed signal recovers after a failure, if the aircraft wheel speed signal fails or recovers after a failure, the ground speed signal is used to execute the switching logic of the large and small angle control law to ensure control stability.
[0030] If both the aircraft wheel speed signal and the ground speed signal fail, the turn control unit 3 will perform a small-angle turn control on the aircraft.
[0031] Preferably, the turning control unit 3 receives aircraft wheel speed signals from the brake control unit 6 via a bus; the turning control unit 3 also receives ground speed signals from the integrated management computer 7 via a bus. This ensures that the switching control unit can efficiently and accurately receive both aircraft wheel speed and ground speed signals.
[0032] 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 high-reliability aircraft nose wheel steering system, characterized in that: It includes a turning command sensor (1), a turning control valve (2), a turning control unit (3), a turning actuator (4), and a turning angle feedback sensor (5); the turning control valve (2) is electrically connected between the turning control unit (3) and the turning actuator (4), and the turning command sensor (1) and the turning angle feedback sensor (5) are both electrically connected to the turning control unit (3); It also includes a brake control unit (6) and an integrated management computer (7), wherein the turning control unit (3) is electrically connected to the brake control unit (6) and the integrated management computer (7), and the turning control unit (3) receives the aircraft wheel speed signal from the brake control unit (6) and the turning control unit (3) receives the ground speed signal from the integrated management computer (7); After receiving both the aircraft wheel speed signal and the ground speed signal, the turning control unit (3) executes the switching logic of the large and small angle control law according to the aircraft wheel speed signal; when it is determined that the aircraft wheel speed signal is invalid, it determines whether the received ground speed signal is valid. If it is valid, the turning control unit (3) executes the switching logic of the large and small angle control law according to the received ground speed signal. When the aircraft wheel speed signal is restored after it fails, the turn control unit (3) still uses the ground speed signal to execute the switching logic of the size angle control law; When the ground speed signal fails and then recovers, if the aircraft wheel speed signal fails or the aircraft wheel speed signal fails and then recovers, the ground speed signal is used to execute the switching logic of the size angle control law.
2. The high-reliability aircraft nose wheel steering system as described in claim 1, characterized in that: The turning control unit (3) is equipped with a signal recognition module, a signal judgment module, a logic judgment module, a memory, and a signal output module. The signal recognition module can receive and recognize aircraft wheel speed signals and ground speed signals, and send the two different signals to the signal judgment module respectively. The signal judgment module can judge the aircraft wheel speed signals and ground speed signals separately, and judge whether the corresponding signals are valid. The memory stores information on aircraft wheel speed signals and ground speed signals at different time points. The logic judgment module receives the signals from the signal judgment module and calls the stored information in the memory. The signal output module receives the control execution from the logic judgment module and sends it to the signal output module.
3. The high-reliability aircraft nose wheel steering system as described in claim 1, characterized in that: If both the aircraft wheel speed signal and the ground speed signal fail, the turn control unit (3) will perform a small-angle turn control on the aircraft.
4. The high-reliability aircraft nose wheel steering system as described in claim 1, characterized in that: The turning control unit (3) receives the aircraft wheel speed signal from the brake control unit (6) via a bus.
5. The high-reliability aircraft nose wheel steering system as described in claim 1, characterized in that: The turning control unit (3) receives the ground speed signal from the integrated management computer (7) via a bus.