Control surface actuating system capable of automatically returning to center after failure and working method

Abstract

The invention belongs to the technical field of flight control, and discloses a control surface actuating system capable of automatically returning to the center after a failure and a working method.The system comprises a controller, an active actuator, a returning actuator and a control surface, the active actuator is provided with an SOV valve and an EHSV valve, the returning actuator is provided with an SOV valve, the controller is connected with and controls the two SOV valves and the EHSV valve, and the controller is connected with the control surface. The mode of the active actuator connected with the SOV valve or the mode of the centering actuator connected with the SOV valve can be switched through switching-on and switching-off of the SOV valve, the EHSV valve drives the active actuator to operate, and the active actuator and the centering actuator are both connected and drive the control plane to deflect. The control surface is controlled by the centering actuator to automatically return to the neutral position and is kept, so that the risk of sudden deviation or oscillation of the control surface is effectively reduced, and the control safety of an aircraft is further improved.

Description

Technical Field

[0001] This invention belongs to the field of flight control technology and relates to a centering structure designed to solve the problem of control surface actuation system failure. Specifically, it relates to a control surface actuation system that can automatically center itself after a failure and its working method. Background Technology

[0002] Aircraft control surfaces are a crucial aspect of flight control and are closely related to the aircraft's maneuverability. During flight, a system malfunction causing sharp yaw or oscillation of the control surfaces is dangerous. Therefore, an automatic return-to-neutral control surface actuation system is needed. When a system failure occurs, including controller or active actuator malfunction, the return-to-neutral actuator automatically returns the control surfaces to a neutral position and maintains it, effectively reducing the risk of sharp yaw or oscillation and thus improving aircraft handling safety.

[0003] CN201710597244.6 proposes a structural design for actuator centering, which installs a centering mechanism on the actuator. This mechanism can center the actuator in the event of a system failure, but it cannot center the actuator in cases of jamming or other malfunctions. Furthermore, even after normal centering, the control surface may oscillate slightly at the centering position due to turbulent airflow, posing a danger. Summary of the Invention

[0004] Therefore, the present invention provides a control surface actuation system and working method that can automatically return to center after a failure, which can improve the control safety of flight operations.

[0005] The technical solution of the present invention is as follows: A rudder surface actuation system capable of automatic return to center after a failure includes a controller, an active actuator, a return-to-center actuator, and a rudder surface. The active actuator is equipped with an SOV valve and an EHSV valve, and the return-to-center actuator is equipped with an SOV valve. The controller is connected to and controls the two SOV valves and the EHSV valve. The opening and closing of the SOV valve switches the mode of the active actuator or the return-to-center actuator connected to the SOV valve. The EHSV valve drives the active actuator to operate. Both the active actuator and the return-to-center actuator are connected to and drive the rudder surface to deflect.

[0006] Furthermore, both the active actuator and the return actuator are hydraulic actuators, with each actuator equipped with a hydraulic power source.

[0007] Furthermore, the active actuator has a working mode and a damping mode, and the return actuator has a return mode and a bypass mode.

[0008] Furthermore, the EHSV valve controls the movement of the active actuator according to the controller's instructions, thereby controlling the deflection of the rudder surface; at this time, the return actuator is in bypass mode.

[0009] Furthermore, the active actuator is equipped with a linear displacement sensor, which feeds back the real-time displacement of the active actuator to the controller.

[0010] A method for operating a rudder surface actuation system that can automatically return to center after a fault: Using the aforementioned rudder surface actuation system that can automatically return to center after a fault, under normal conditions, the active actuator is in working mode, the SOV valve of the centering actuator is in a closed state, the controller monitors the command signal output to the active actuator, and compares the command signal with the feedback signal received from the active actuator. When a difference exceeding a set value occurs, it is determined that the active actuator is partially faulty, and the centering mode is activated.

[0011] Furthermore, in the centering mode, the active actuator is in the damping mode, and the centering actuator is in the centering mode.

[0012] Furthermore, the centering actuator has an oil inlet in each of its left and right chambers, and a return port at the center position of the centering actuator cylinder. Both the oil inlet and return of the centering actuator are unidirectional. When the SOV valve of the centering actuator cylinder is closed, the centering actuator is in bypass mode, the oil inlet and return of the system are cut off, and the load chamber of the mode valve connects the left and right chambers of the actuator cylinder, allowing the piston to move left and right. When the SOV valve is open, the centering actuator is in centering mode, both oil inlets are connected to high-pressure oil, and the actuator cylinder of the centering actuator communicates with the system return oil through the return port. When the rudder surface is not in the neutral position, the pressure in the left and right chambers of the actuator cylinder is inconsistent, and the piston begins to move until it reaches the center position and blocks the return port. At this time, the piston will stop moving.

[0013] Furthermore, when the active actuator is in the damped mode, the SOV valve of the active actuator is cut off, the EHSV valve no longer drives the active actuator, and the active actuator is in a bidirectional damped state based on the remaining high-pressure oil inside.

[0014] Technical effects: 1. This invention provides a control surface actuation system that can automatically return to center after a failure. When the control surface control system fails, the control surface is automatically returned to the neutral position and maintained by the centering actuator, which effectively reduces the risk of sharp deflection or oscillation of the control surface and thus improves the aircraft's handling safety.

[0015] 2. This invention automatically activates the mode switching function by comparing the output command signal and the received feedback signal, thereby completing the automatic centering of the control surface system.

[0016] 3. The present invention employs two actuators, which have redundant redundancy. The actuators in the damping mode can generate a certain resistance to the movement of the control surface, preventing it from deflecting after returning to center. Attached Figure Description

[0017] Figure 1This is a schematic diagram of the rudder surface actuation system that can automatically return to center after a failure, provided by the present invention.

[0018] Figure 2 This is a hydraulic schematic diagram of the bypass mode of the return actuator provided by the present invention.

[0019] Figure 3 This is a hydraulic principle diagram of the centering mode of the centering actuator provided by the present invention. Detailed Implementation

[0020] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of the invention. However, it will be apparent to those skilled in the art that the invention can be practiced without some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0021] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0022] Example 1: A rudder surface actuation system capable of automatic return to center after a failure includes a controller, an active actuator, a return-to-center actuator, and a rudder surface. The active actuator is equipped with an SOV valve and an EHSV valve, and the return-to-center actuator is equipped with an SOV valve. The controller is connected to and controls the two SOV valves and the EHSV valve. The opening and closing of the SOV valve switches the mode of the active actuator or the return-to-center actuator connected to the SOV valve. The EHSV valve drives the active actuator to operate. Both the active actuator and the return-to-center actuator are connected to and drive the rudder surface to deflect.

[0023] Both the active actuator and the return actuator are hydraulic actuators, and each is equipped with a hydraulic power source.

[0024] The active actuator has a working mode and a damping mode, while the return-center actuator has a return-center mode and a bypass mode.

[0025] The EHSV valve controls the movement of the active actuator according to the controller's instructions, thereby controlling the deflection of the rudder surface; at this time, the return actuator is in bypass mode.

[0026] The active actuator is equipped with a linear displacement sensor, which feeds back the real-time displacement of the active actuator to the controller.

[0027] A method for operating a rudder surface actuation system that can automatically return to center after a fault: Using the aforementioned rudder surface actuation system that can automatically return to center after a fault, under normal conditions, the active actuator is in working mode, the SOV valve of the centering actuator is in a closed state, the controller monitors the command signal output to the active actuator, and compares the command signal with the feedback signal received from the active actuator. When a difference exceeding a set value occurs, it is determined that the active actuator is partially faulty, and the centering mode is activated.

[0028] In centering mode, the active actuator is in damping mode and the centering actuator is in centering mode.

[0029] The centering actuator has an oil inlet in each of its left and right chambers, and a return port at the center position of the centering actuator cylinder. Both the oil inlet and return of the centering actuator are unidirectional. When the SOV valve of the centering actuator cylinder is closed, the centering actuator is in bypass mode, the oil inlet and return of the system are cut off, and the load chamber of the mode valve connects the left and right chambers of the actuator cylinder, allowing the piston to move left and right. When the SOV valve is open, the centering actuator is in centering mode, both oil inlets are connected to high-pressure oil, and the actuator cylinder of the centering actuator communicates with the system return oil through the return port. When the rudder is not in the neutral position, the pressure in the left and right chambers of the actuator cylinder is inconsistent, and the piston begins to move until it reaches the center position and blocks the return port. At this time, the piston will stop moving.

[0030] When the active actuator is in the damped mode, the SOV valve of the active actuator is cut off, the EHSV valve no longer drives the active actuator, and the active actuator is in a bidirectional damped state based on the remaining high-pressure oil inside.

[0031] Example 2: Figure 1 The schematic diagram of the automatic return-to-center rudder surface actuation system provided by an embodiment of the present invention is shown. The system consists of a controller, an SOV valve, an EHSV valve, an active actuator, a return-to-center actuator, and a linear displacement sensor.

[0032] The controller outputs rudder surface control commands and outputs SOV valve control signals to the active actuator and return actuator, respectively.

[0033] The active actuator and the return actuator are each equipped with a hydraulic power source. The actuator is driven by controlling the flow of hydraulic oil. The active actuator has two modes: working and damping. The return actuator has two modes: bypass and return.

[0034] The EHSV valve controls the movement of the active actuator according to the controller's instructions, thereby controlling the deflection of the rudder surface. At this time, the return actuator is in bypass mode and follows the movement of the active actuator.

[0035] The linear displacement sensor feeds back the real-time displacement of the active actuator to the controller.

[0036] The controller's command and monitoring branches compare the output command signal with the received feedback signal. When the two are inconsistent, the controller will determine that the active actuator is faulty and switch the actuator to damping mode. At the same time, the centering actuator switches from bypass to centering mode, so that the control surface can automatically return to center and maintain it.

[0037] The controller can monitor the control status of the active actuator by comparing the signals from the command and monitoring branches.

[0038] The control surface actuation system employs a dual-redundant control strategy.

[0039] The controller employs a redundant system.

[0040] Under normal circumstances, the SOV valve is in a normally closed state. When a system fault occurs, including a controller or active actuator fault, the controller will cut off the SOV valve signal, switch the active actuator to damping mode, and switch the return actuator to return mode.

[0041] When the SOV valve signal is cut off, the rudder surface will no longer accept the control of the controller output command, and the return actuator will mechanically fix the rudder surface in the neutral position.

[0042] Figure 2 and Figure 3 The diagram illustrates the hydraulic principle of the return-center actuator in bypass and return-center modes provided by this invention. The return-center actuator has an oil inlet in each of its left and right chambers, and a return port at the center position of the actuator. Both inlet and outlet are unidirectional. When the SOV valve is closed, the actuator is in bypass mode, and the system's inlet and return ports are cut off. The load chamber of the mode valve connects the left and right chambers of the actuator, allowing the piston to move left and right. When the SOV valve is open, the actuator is in return-center mode, and both inlets are connected to high-pressure oil. The actuator communicates with the system's return oil through the return port. When the steering surface is not in the neutral position, the pressure in the left and right chambers of the actuator is inconsistent, causing the piston to begin moving until it reaches the center position and blocks the return port. At this point, the piston will stop moving.

[0043] The centering actuator can control the centering speed of the rudder surface by controlling the flow rate at the return oil port.

[0044] Both actuators are driven by hydraulic oil. When the hydraulic source for the actuator to actively return to center fails, the left and right chambers of the actuator cylinder are closed and not connected. When the piston of the actuator cylinder is not in the neutral position, it can passively return to center by external load through the return oil port, which increases the reliability of the actuator system.

[0045] If the control surfaces are fixed in the neutral position due to a system malfunction, the crew may terminate the flight mission or continue safe flight as appropriate.

[0046] The above description is only a preferred embodiment of the present invention. It should be noted that those skilled in the art can make several improvements without departing from the principle of the present invention, and these improvements should also be considered within the scope of protection of the present invention.

Claims

1. A post-failure self-recoverable control surface actuation system, characterized by, The controller, the main actuator, the centering actuator and the rudder surface are included, the SOV valve and the EHSV valve are arranged on the main actuator, the SOV valve is arranged on the centering actuator, the controller is connected with and controls the two SOV valves and the EHSV valve, the connection and the closure of the SOV valve switch the mode of the main actuator or the centering actuator connected with the SOV valve, the EHSV valve drives the main actuator to operate, and the main actuator and the centering actuator are connected with and drive the rudder surface to deflect.

2. The system of claim 1, wherein, The main actuator and the centering actuator are hydraulic actuators, and one hydraulic source is arranged on the main actuator and the centering actuator.

3. The system of claim 2, wherein: The main actuator has a working mode and a damping mode, and the centering actuator has a centering mode and a bypass mode.

4. The automatically reconfigurable control surface actuation system of claim 1, wherein: The EHSV valve controls the movement of the main actuator according to the instruction of the controller, and then controls the deflection of the rudder surface; at this time, the centering actuator is in the bypass mode.

5. The automatically reconfigurable control surface actuation system of claim 1, wherein: A linear displacement sensor is arranged on the main actuator, and the linear displacement sensor feeds back the real-time displacement of the main actuator to the controller.

6. A method of operating a post-failure self-centering control surface actuation system using the post-failure self-centering control surface actuation system of claim 3, wherein, In the normal state of the rudder surface actuating system, the main actuator is in the working mode, the SOV valve of the centering actuator is in the closed state, the controller monitors the instruction signal output to the main actuator, and compares the instruction signal with the feedback signal received from the main actuator, when the difference exceeds the set value, it is judged that the main actuator is partially faulty, and the centering mode is started.

7. The method of claim 6, wherein the method further comprises: In the centering mode, the main actuator is in the damping mode, and the centering actuator is in the centering mode.

8. The method of claim 6, wherein, The left and right cavities of the centering actuator each have an oil inlet, and the centering cylinder has an oil return port at the middle position, and the oil inlet and the oil return of the centering actuator are unidirectional; when the SOV valve of the centering cylinder is connected, the centering actuator is in the bypass mode, the oil inlet and the oil return of the system are cut off, the mode valve load cavity is connected with the left and right cavities of the actuating cylinder, so that the piston can move left and right; when the SOV valve is disconnected, the centering actuator is in the centering mode, both oil inlets are connected with high-pressure oil, the actuating cylinder of the centering actuator communicates with the system oil return through the oil return port, and when the rudder surface is not in the neutral position, the pressures of the left and right cavities of the actuating cylinder are different, the piston starts to move until it reaches the middle position and blocks the oil return port, at this time, the piston will no longer move.

9. The method of claim 6, wherein, When the main actuator is in the damping mode, the SOV valve of the main actuator is cut off, the EHSV valve no longer drives the main actuator, and the main actuator is in the bidirectional damping state based on the remaining high-pressure oil inside.

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