A rotary aircraft control surface drive device and method having emergency drive functionality

Abstract

The application belongs to the field of flight control design, and particularly relates to a rotary aircraft control surface driving device and method with an emergency driving function. In an emergency state, a servo hydraulic channel is closed, an emergency hydraulic channel is opened, a driving control surface is mechanically braked after reaching a specified position, and the control surface is kept at the specified position. The purpose of the emergency mode is to keep the aircraft control surface at a safe position in a fault condition, reduce the impact of the uncontrolled control surface on the aerodynamic shape of the aircraft, and improve the emergency capability of the aircraft in a special situation. The multiple rotary actuators of the application are coaxially distributed through a transmission shaft, the synchronism between the rotary actuators is higher, and the distribution of the aerodynamic load on the driving device is more uniform. By adding the emergency mode of the driving device, the control surface driving device can still drive the control surface to deflect through the emergency mode when the servo state fails, so that the uncontrollable situation of the aircraft control surface is avoided, and the flight safety is ensured.

Description

Technical Field

[0001] This application belongs to the field of flight control design, and specifically relates to a rotary aircraft control surface drive device and method with emergency drive function. Background Technology

[0002] Due to the high speed and stealth requirements of modern aircraft, control surfaces are thinner and subject to greater loads. Conventional aircraft mostly use single or multiple servos in parallel to drive control surface deflection. However, the thinner wings of conventional designs come at the cost of a more prominent aircraft shape, impacting aerodynamic and stealth performance. Furthermore, the force conflicts inherent in parallel servos become more pronounced with increased aerodynamic loads. Therefore, a new control surface drive solution is needed to address the challenges of thinner wings and greater aerodynamic loads.

[0003] Therefore, it is desirable to have a technical solution to overcome or at least mitigate one of the aforementioned defects of the prior art. Summary of the Invention

[0004] The purpose of this application is to provide a rotary aircraft control surface drive device and method with emergency drive function to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A rotary aircraft control surface drive device with emergency drive function, comprising:

[0007] A control surface module, comprising multiple rotary actuators connected to the control surface, the rotary actuators being connected to a hydraulic drive and a brake;

[0008] The servo control module includes a servo solenoid valve, a function switching valve, and a servo valve. The servo solenoid valve is connected to the function switching valve through a first pipeline and to the brake through a second pipeline. The function switching valve is connected to the servo valve, and the servo valve is connected to the hydraulic motor of the hydraulic drive.

[0009] An emergency control module includes an emergency retraction solenoid valve, an emergency drive main control valve, and an emergency release solenoid valve. The emergency retraction solenoid valve is connected to the emergency drive main control valve via a third pipeline and to the brake via a fourth pipeline. The emergency release solenoid valve is connected to the emergency drive main control valve via a fifth pipeline and to the brake via a sixth pipeline. The emergency drive main control valve is connected to the hydraulic motor of the hydraulic actuator.

[0010] A controller is used to control the servo solenoid valve, the servo valve, the emergency take-off solenoid valve, and the emergency release solenoid valve.

[0011] In at least one embodiment of this application, two adjacent rotary actuators are connected by a drive shaft.

[0012] In at least one embodiment of this application, the servo solenoid valve, the function switching valve, the emergency take-up solenoid valve, the emergency drive main control valve, and the emergency release solenoid valve are all connected to hydraulic oil pipelines.

[0013] In at least one embodiment of this application, an angular displacement sensor is installed on the control surface, and the controller is used to control the servo solenoid valve, the servo valve, the emergency retraction solenoid valve, and the emergency release solenoid valve according to the control surface deflection angle fed back by the angular displacement sensor.

[0014] In at least one embodiment of this application, two bidirectional valves are further included: a first bidirectional valve and a second bidirectional valve, wherein,

[0015] The fourth and sixth pipelines are respectively connected to the two inlets of the first two-way valve, and the seventh pipeline is installed at the outlet of the first two-way valve.

[0016] The second pipeline and the seventh pipeline are respectively connected to the two inlets of the second two-way valve, and the outlet of the second two-way valve is connected to the brake through the eighth pipeline.

[0017] The second aspect of this application provides a rotary aircraft control surface drive method with emergency drive function, based on the rotary aircraft control surface drive device with emergency drive function as described above, comprising:

[0018] In servo mode:

[0019] The controller issues a servo solenoid valve open command and a servo valve open command.

[0020] After the servo solenoid valve opens according to the servo solenoid valve opening command, the hydraulic oil opens the function switching valve and at the same time unlocks the brake through the two-way valve.

[0021] The servo valve controls the size of the valve core opening according to the size of the servo valve opening command, thereby controlling the hydraulic oil flow rate and driving the hydraulic motor to rotate and the steering surface to deflect.

[0022] In emergency recovery mode:

[0023] The controller issues an emergency solenoid valve opening command;

[0024] After the emergency solenoid valve opens according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve in the forward direction, and at the same time unlock the brake through the two-way valve, thereby driving the hydraulic motor to rotate in the forward direction and the steering surface to deflect.

[0025] When the control surface is retracted to the designated position, the controller issues an emergency retraction solenoid valve closing command based on the retraction position signal fed back by the angular displacement sensor. The emergency retraction solenoid valve closes, and the brake locks the shaft system without hydraulic oil. The control surface is held in a specific position by mechanical locking.

[0026] In emergency release mode:

[0027] The controller issues a command to open the emergency solenoid valve;

[0028] After the emergency solenoid valve opens according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve in the reverse direction, and at the same time unlock the brake through the two-way valve, thereby driving the hydraulic motor to rotate in the reverse direction and the steering surface to deflect.

[0029] Once the control surface is lowered to the designated position, the controller issues an emergency solenoid valve closing command based on the lowering signal fed back by the angular displacement sensor. The emergency solenoid valve closes, and the brake locks the shaft system without hydraulic oil. The control surface is mechanically locked and held in a specific position.

[0030] The invention has at least the following beneficial technical effects:

[0031] The rotary aircraft control surface drive device with emergency drive function of this application can deflect the control surface in normal servo mode or emergency mode, thereby improving the aircraft's emergency response capability in special situations. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of a rotary aircraft control surface drive device with emergency drive function according to one embodiment of this application.

[0033] Figure 2 This is a schematic diagram of a rotary aircraft control surface drive device with emergency drive function according to one embodiment of this application.

[0034] in:

[0035] 1-Hydraulic actuator; 2-Drive shaft; 3-Rotary actuator; 4-Rudder surface; 5-Controller; 6-Servo solenoid valve; 7-Function switching valve; 8-Servo valve; 9-Emergency retraction solenoid valve; 10-Emergency drive main control valve; 11-Emergency release solenoid valve; 12-Hydraulic motor; 13-Two-way valve; 14-Brake; 15-Angular displacement sensor. Detailed Implementation

[0036] 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 some, but not all, 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.

[0037] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting the scope of protection of this application.

[0038] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0039] The first aspect of this application provides a rotary aircraft control surface drive device with emergency drive function, including: a control surface control module, a servo control module, an emergency control module, and a controller 5.

[0040] Specifically, the control module includes a control surface 4 and multiple rotary actuators 3 connected to the control surface 4. An angular displacement sensor 15 is installed on the control surface 4. Adjacent rotary actuators 3 are connected by a drive shaft 2. The rotary actuators 3 are connected to a hydraulic actuator 1 and a brake 14. The hydraulic actuator 1 drives the drive shaft 2 to rotate, which in turn drives the multiple rotary actuators 3 to rotate synchronously. The rotary actuators 3 cause the control surface 4 to deflect.

[0041] This application discloses a rotary aircraft control surface drive device with emergency drive function. The rotary control surface drive module is installed inside the wing, allowing for better integration into the wing structure and driving the deflection of the leading-edge flaps. Furthermore, the rotary actuation method allows for the coaxial parallel connection of multiple rotary actuators 3, which reduces the impact of force conflicts. The rotary actuators 3 are distributed along the control surface rotation axis, and the drive shaft 2 connects each rotary actuator 3. The entire control surface control module can include a hydraulic actuator 1, multiple rotary actuators 3, the drive shaft 2, and sensors, etc.

[0042] The servo control module includes a servo solenoid valve 6, a function switching valve 7, and a servo valve 8. The servo solenoid valve 6 is connected to the function switching valve 7 through a first pipeline and to the brake 14 through a second pipeline. The function switching valve 7 is connected to the servo valve 8, and the servo valve 8 is connected to the hydraulic motor 12 of the hydraulic drive 1. Both the servo solenoid valve 6 and the function switching valve 7 are connected to the hydraulic oil pipeline.

[0043] The emergency control module includes an emergency retraction solenoid valve 9, an emergency drive main control valve 10, and an emergency release solenoid valve 11. The emergency retraction solenoid valve 9 is connected to the emergency drive main control valve 10 via a third pipeline and to the brake 14 via a fourth pipeline. The emergency release solenoid valve 11 is connected to the emergency drive main control valve 10 via a fifth pipeline and to the brake 14 via a sixth pipeline. The emergency drive main control valve 10 is connected to the hydraulic motor 12 of the hydraulic actuator 1. The emergency retraction solenoid valve 9, the emergency drive main control valve 10, and the emergency release solenoid valve 11 are all connected to hydraulic oil pipelines.

[0044] The controller 5 controls the servo solenoid valve 6, servo valve 8, emergency retraction solenoid valve 9, and emergency release solenoid valve 11 based on the rudder surface deflection angle fed back by the angular displacement sensor 15. The controller 5 converts the rudder surface deflection angle into control of the servo valve core to control the hydraulic flow, thereby driving the rotary actuator 3 to deflect the rudder surface 4 to the corresponding angle. Then, the angular displacement sensor 15 collects the current position signal of the rudder surface 4 and feeds it back to the controller 5 to form a closed loop.

[0045] The rotary aircraft control surface drive device with emergency drive function of this application further includes two two-way valves 13, a first two-way valve and a second two-way valve. A fourth pipe and a sixth pipe are respectively connected to the two inlets of the first two-way valve, and a seventh pipe is installed at the outlet of the first two-way valve. The second pipe and the seventh pipe are respectively connected to the two inlets of the second two-way valve, and the outlet of the second two-way valve is connected to a brake 14 via an eighth pipe. Figure 2 As shown.

[0046] Based on the aforementioned rotary aircraft control surface drive device with emergency drive function, a second aspect of this application provides a rotary aircraft control surface drive method with emergency drive function, comprising:

[0047] In servo mode:

[0048] Controller 5 issues a servo solenoid valve open command and a servo valve open command.

[0049] After the servo solenoid valve 6 opens according to the servo solenoid valve opening command, the hydraulic oil opens the function conversion valve 7 and at the same time unlocks the brake 14 through the two-way valve 13.

[0050] The servo valve 8 controls the size of the valve core opening according to the size of the servo valve opening command, thereby controlling the hydraulic oil flow rate and driving the hydraulic motor 12 to rotate and the steering surface 4 to deflect.

[0051] In emergency recovery mode:

[0052] Controller 5 issues an emergency solenoid valve opening command;

[0053] After the emergency solenoid valve 9 is opened according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve 10 in the forward direction, and at the same time unlock the brake 14 through the two-way valve 13, thereby driving the hydraulic motor 12 to rotate in the forward direction and the rudder surface 4 to deflect.

[0054] When the rudder surface 4 is retracted to the designated position, the controller 5 issues an emergency retraction solenoid valve closing command based on the retraction signal fed back by the angular displacement sensor 15. The emergency retraction solenoid valve 9 is closed, and the brake 14 locks the shaft system without hydraulic oil. The rudder surface 4 is held in a specific position by mechanical locking.

[0055] In emergency release mode:

[0056] Controller 5 issues a command to open the emergency solenoid valve;

[0057] After the emergency solenoid valve 11 is opened according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve 10 in the reverse direction, and at the same time unlock the brake 14 through the two-way valve 13, thereby driving the hydraulic motor 12 to rotate in the reverse direction and the rudder surface 4 to deflect.

[0058] When the rudder surface 4 is lowered to the designated position, the controller 5 issues an emergency solenoid valve closing command based on the lowering signal fed back by the angular displacement sensor 15. The emergency solenoid valve 11 closes, and the brake 14 locks the shaft system without hydraulic oil. The rudder surface 4 is held in a specific position by mechanical locking.

[0059] The rotary aircraft control surface drive method with emergency drive function of this application uses controller 5 to select servo mode or emergency mode through logical judgment. In servo mode, controller 5 issues servo solenoid valve opening command and servo valve opening command, and at the same time issues emergency retract solenoid valve closing command and emergency release solenoid valve closing command. After servo solenoid valve 6 opens, high-pressure oil opens function conversion valve 7, and at the same time unlocks brake 14 through bidirectional valve 13. Servo valve 8 controls the valve core opening size according to the magnitude of controller current command, thereby controlling the hydraulic oil flow rate, and then drives hydraulic motor 12 to rotate. After brake 14 is unlocked, hydraulic motor 12 can drive shaft system to rotate, and aircraft control surface 4 can deflect to a specified angle. In emergency retraction mode, controller 5 issues a command to close servo solenoid valve 6, thereby closing function conversion valve 7. High-pressure oil will not enter hydraulic motor 12 through servo hydraulic channel. At the same time, controller 5 issues a command to open emergency retraction solenoid valve 9. High-pressure oil will open emergency drive main control valve 10 in the forward direction and unlock brake 14 through bidirectional valve 13, thereby driving hydraulic motor 12 to rotate in the forward direction. When rudder surface 4 is retracted to the designated position, angular displacement sensor 15 will feed back the retraction completion signal to controller 5. Controller 5 controls emergency retraction solenoid valve 9 to close, preventing high-pressure oil from entering hydraulic motor 12 through emergency hydraulic channel. Brake 14 locks the shaft system in the absence of high-pressure oil, and rudder surface 4 is mechanically locked in a specific position. In emergency release mode, controller 5 issues a command to close servo solenoid valve 6, thereby closing function conversion valve 7. High-pressure oil will not enter hydraulic motor 12 through servo hydraulic channel. At the same time, controller 5 issues a command to open emergency release solenoid valve 11. High-pressure oil will open emergency drive main control valve 10 in reverse and unlock brake 14 through bidirectional valve 13, thereby driving hydraulic motor 12 to rotate in reverse. When rudder surface 4 is lowered to the designated position, angular displacement sensor 15 will feed back the lowered position signal to controller 5. Controller 5 controls emergency retraction solenoid valve 11 to close. High-pressure oil will not enter hydraulic motor 12 through emergency hydraulic channel. Brake 14 locks the shaft system in the absence of high-pressure oil, and rudder surface is held in a specific position by mechanical locking.

[0060] The rotary aircraft control surface drive method with emergency drive function disclosed in this application, in normal servo mode, the controller 5 controls the deflection of the control surface by controlling the servo hydraulic channel; in emergency state, the servo hydraulic channel is closed and the emergency hydraulic channel is opened, driving the control surface 4 to a designated position and then mechanically braking it to keep the control surface 4 in the designated position. The purpose of the emergency mode is to keep the aircraft control surface 4 in a safe position in the event of a failure, reduce the impact on the aerodynamic shape of the aircraft when the control surface 4 is out of control, and improve the aircraft's emergency response capability in special situations.

[0061] This application discloses a rotary aircraft control surface drive device and method with emergency drive function. Multiple rotary actuators 3 are coaxially distributed and connected via a drive shaft 2, resulting in higher synchronization among the actuators 3 and a more uniform distribution of aerodynamic loads on the drive device. By adding an emergency mode to the drive device, the control surface drive device can still drive the control surface 4 to deflect in emergency mode even when the servo state fails, preventing the aircraft control surface 4 from becoming uncontrollable and ensuring flight safety.

[0062] 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 rotary aircraft control surface drive device with emergency drive function, characterized in that, include: The rudder control module includes multiple rotary actuators (3) connected to the rudder (4), and the rotary actuators (3) are connected to the hydraulic drive (1) and the brake (14). The servo control module includes a servo solenoid valve (6), a function switching valve (7), and a servo valve (8). The servo solenoid valve (6) is connected to the function switching valve (7) through a first pipeline and to the brake (14) through a second pipeline. The function switching valve (7) is connected to the servo valve (8), and the servo valve (8) is connected to the hydraulic motor (12) of the hydraulic drive (1). An emergency control module is provided, comprising an emergency solenoid valve (9), an emergency drive main control valve (10), and an emergency release solenoid valve (11). The emergency solenoid valve (9) is connected to the emergency drive main control valve (10) via a third pipeline and to the brake (14) via a fourth pipeline. The emergency release solenoid valve (11) is connected to the emergency drive main control valve (10) via a fifth pipeline and to the brake (14) via a sixth pipeline. The emergency drive main control valve (10) is connected to the hydraulic motor (12) of the hydraulic actuator (1). The controller (5) is used to control the servo solenoid valve (6), the servo valve (8), the emergency take-off solenoid valve (9), and the emergency release solenoid valve (11). An angular displacement sensor (15) is installed on the rudder surface (4). The controller (5) is used to control the servo solenoid valve (6), the servo valve (8), the emergency take-off solenoid valve (9), and the emergency release solenoid valve (11) according to the rudder surface deflection angle fed back by the angular displacement sensor (15). It also includes two two-way valves (13), a first two-way valve and a second two-way valve, wherein, The fourth and sixth pipelines are respectively connected to the two inlets of the first two-way valve, and the seventh pipeline is installed at the outlet of the first two-way valve. The second pipeline and the seventh pipeline are respectively connected to the two inlets of the second two-way valve, and the outlet of the second two-way valve is connected to the brake (14) through the eighth pipeline; Rotary aircraft control surface drive methods with emergency drive capabilities include: In servo mode: The controller (5) issues a servo solenoid valve opening command and a servo valve opening command; After the servo solenoid valve (6) is opened according to the servo solenoid valve opening command, the hydraulic oil opens the function switching valve (7) and at the same time unlocks the brake (14) through the two-way valve (13). The servo valve (8) controls the size of the valve core opening according to the size of the servo valve opening command, thereby controlling the hydraulic oil flow rate and driving the hydraulic motor (12) to rotate and the steering surface (4) to deflect. In emergency recovery mode: The controller (5) issues an emergency solenoid valve opening command; After the emergency solenoid valve (9) is opened according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve (10) in the forward direction, and at the same time unlock the brake (14) through the two-way valve (13), thereby driving the hydraulic motor (12) to rotate in the forward direction and the rudder surface (4) to deflect. When the rudder (4) is retracted to the designated position, the controller (5) issues an emergency retraction solenoid valve closing command based on the retraction position signal fed back by the angular displacement sensor (15). The emergency retraction solenoid valve (9) closes, and the brake (14) locks the shaft system without hydraulic oil. The rudder (4) is held in a specific position by mechanical locking. In emergency release mode: The controller (5) issues an emergency solenoid valve opening command; After the emergency solenoid valve (11) is opened according to the emergency solenoid valve opening command, the hydraulic oil will open the emergency drive main control valve (10) in the reverse direction, and at the same time unlock the brake (14) through the two-way valve (13), thereby driving the hydraulic motor (12) to rotate in the reverse direction and the rudder (4) to deflect. When the rudder (4) is lowered to the designated position, the controller (5) issues an emergency solenoid valve closing command based on the lowering signal fed back by the angular displacement sensor (15). The emergency solenoid valve (11) is closed, and the brake (14) locks the shaft system without hydraulic oil. The rudder (4) is held in a specific position by mechanical locking.

2. The rotary aircraft control surface drive device with emergency drive function according to claim 1, characterized in that, The two adjacent rotary actuators (3) are connected by a drive shaft (2).

3. The rotary aircraft control surface drive device with emergency drive function according to claim 2, characterized in that, The servo solenoid valve (6), the function switching valve (7), the emergency take-up solenoid valve (9), the emergency drive main control valve (10), and the emergency release solenoid valve (11) are all connected to the hydraulic oil pipeline.

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