A leading edge flap drive device with emergency drive function

Abstract

The application belongs to the field of aircraft servo actuating system, and particularly relates to a leading edge flap driving device with an emergency driving function. The device comprises a control surface control module, a servo control module, an emergency control module and a controller. The leading edge flap driving device with the emergency driving function receives an instruction signal from the controller when the system needs to be switched into an emergency working mode during the flight of an aircraft, drives a rotary actuator to work through a hydraulic driving motor, drives a leading edge flap surface to deflect, improves the safety and reliability of the flight, and ensures the stability of the landing of the aircraft. A perfect mode switching method ensures the safe and reliable working of the servo actuating system.

Description

Technical Field

[0001] This application belongs to the field of aircraft servo actuation systems, and specifically relates to a leading-edge flap drive device with emergency drive function. Background Technology

[0002] Aircraft have undergone rapid development in recent decades, with larger aircraft sizes, significantly increased flight speeds, and tailless, stealthy aerodynamic layouts gradually becoming the mainstream trend. Servo actuation systems are systems on aircraft that control the deflection angle of control surfaces, used to control the aircraft's balance, maneuverability, and flight direction; they are among the most critical systems for flight safety. Leading-edge flaps are one of the commonly used control surfaces in aircraft to improve lift. To meet the rapidly increasing performance requirements of next-generation aircraft and the safe and stable landing requirements of carrier-based aircraft, leading-edge flaps have become one of the key control surfaces for the new generation of aircraft. Rotary actuators are widely used to drive leading-edge flaps, but they suffer from limitations in redundancy, and low reliability in mechanically single-redundant and electrically dual-redundant architectures. Based on these issues, there is an urgent need for a new leading-edge flap drive device and operating mode switching method to achieve highly reliable and safe servo actuation of leading-edge flaps, meeting the new requirements and challenges of servo actuation systems for the next generation of aircraft.

[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 leading-edge flap drive device 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 leading-edge flap drive device with emergency drive function, comprising:

[0007] The control surface module includes a rotary actuator connected to the leading edge flap, the rotary actuator being connected to a hydraulic drive motor and a brake;

[0008] The servo control module includes a function switching solenoid valve, a function switching valve, and a servo valve. The function switching 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 drive motor.

[0009] An emergency control module includes an emergency retraction solenoid valve, an emergency release solenoid valve, and an emergency drive main control 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 drive motor.

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

[0011] In at least one embodiment of this application, the function switching solenoid valve, the function switching valve, the emergency take-up solenoid valve, the emergency release solenoid valve, and the emergency drive main control valve are all connected to hydraulic oil pipelines.

[0012] In at least one embodiment of this application, two bidirectional valves are further included: a first bidirectional valve and a second bidirectional valve, wherein,

[0013] 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.

[0014] 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.

[0015] In at least one embodiment of this application, microswitches are respectively provided at the maximum upper deflection position and the maximum lower deflection position of the rotary actuator housing. The controller is used to control the function switching solenoid valve, the servo valve, the emergency take-up solenoid valve, and the emergency release solenoid valve according to the feedback signal of the microswitches.

[0016] In at least one embodiment of this application, a mutually exclusive switching valve is provided between the servo valve and the emergency drive main control valve.

[0017] In at least one embodiment of this application, the leading edge flap drive device has a normal operation mode, a ground maintenance mode, a fault protection mode, and an emergency operation mode, wherein the fault protection mode includes a fail-safe mode and a fail operation mode.

[0018] In at least one embodiment of this application, the switching method for each operating mode of the leading edge flap drive device is as follows:

[0019] After the system is powered on, it performs a self-test within the motor.

[0020] During the self-test within the upper motor:

[0021] If a single-channel fault is detected, the system will enter fault operation mode.

[0022] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0023] If the internal self-test of the upper motor passes, then perform the pre-flight internal self-test;

[0024] During pre-flight in-flight self-test:

[0025] If a single-channel fault is detected, the system will enter fault operation mode.

[0026] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0027] If the pre-flight in-flight self-test passes, the aircraft will enter normal operating mode.

[0028] In normal working mode:

[0029] According to the self-test command inside the cycle machine, the cycle machine performs a self-test. If a single-channel fault is detected, it enters the fault working mode. If a dual-channel fault is detected, it enters the fail-safe mode.

[0030] When the system is on the ground and receives a self-test command from the maintenance unit, it enters the ground maintenance mode.

[0031] In ground maintenance mode:

[0032] If a single-channel fault is detected, the system will enter fault operation mode.

[0033] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0034] If the machine passes the self-test during maintenance, it will enter normal working mode.

[0035] In fault operation mode:

[0036] According to the self-test command inside the cycle machine, perform a self-test inside the cycle machine. If a dual-channel fault is detected, enter the fail-safe mode.

[0037] In fail-safe mode:

[0038] Upon receiving an emergency work order, enter emergency work mode;

[0039] In emergency work mode:

[0040] Once emergency response measures are in place, the system will enter fail-safe mode.

[0041] The invention has at least the following beneficial technical effects:

[0042] The leading-edge flap drive device of this application has an emergency drive function, which can complete highly reliable and safe leading-edge flap servo actuation. Attached Figure Description

[0043] Figure 1 This is a schematic diagram of the normal operating mode of a leading-edge flap drive device with emergency drive function according to one embodiment of this application;

[0044] Figure 2 This is a schematic diagram of the emergency working mode of a leading-edge flap drive device with emergency drive function according to one embodiment of this application;

[0045] Figure 3 This is a schematic diagram of the stroke position of a leading-edge flap drive device with emergency drive function according to one embodiment of this application;

[0046] Figure 4 This is a flowchart of an emergency working mode with emergency driving function according to one embodiment of this application;

[0047] Figure 5 This is an emergency SOV control logic diagram of one embodiment of this application;

[0048] Figure 6 This is an emergency SOV control logic diagram of one embodiment of this application;

[0049] Figure 7 This is a logic diagram of the working mode switching of a leading edge flap drive device with emergency drive function according to one embodiment of this application.

[0050] in:

[0051] 1-Hydraulic drive motor; 2-Brake; 3-Function conversion solenoid valve; 4-Function conversion valve; 5-Servo valve; 6-Emergency retraction solenoid valve; 7-Emergency release solenoid valve; 8-Emergency drive main control valve; 9-Controller; 10-Two-way valve; 11-Mutual exclusion conversion valve. Detailed Implementation

[0052] 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.

[0053] 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.

[0054] The following is in conjunction with the appendix Figures 1 to 7 This application will be described in further detail.

[0055] This application provides a leading-edge flap drive device with emergency drive function, including: a control surface control module, a servo control module, an emergency control module, and a controller 9.

[0056] The parameters in the diagram have the following meanings: PUBIT: Upper motor internal self-test, PBIT: Pre-flight internal self-test, IFBIT: Periodic internal self-test, MBIT: Maintenance internal self-test, SOV: Solenoid valve, RVDT: Angular displacement sensor, EHSV: Electro-hydraulic servo valve.

[0057] Specifically, such as Figure 1-2As shown, the control surface module includes a rotary actuator connected to the leading edge flap, a hydraulic drive motor 1, and a brake 2. An angular displacement sensor is arranged on the leading edge flap, and the hydraulic drive motor 1 is equipped with a speedometer. The servo control module includes a function conversion solenoid valve 3, a function conversion valve 4, and a servo valve 5. The function conversion solenoid valve 3 is connected to the function conversion valve 4 through a first pipeline and to the brake 2 through a second pipeline. The function conversion valve 4 is connected to the servo valve 5, and the servo valve 5 is connected to the hydraulic drive motor 1. Both the function conversion solenoid valve 3 and the function conversion valve 4 are connected to hydraulic oil lines. The emergency control module includes an emergency retraction solenoid valve 6 and an emergency release solenoid valve 6. Valve 7 and emergency drive main control valve 8, emergency retraction solenoid valve 6 are connected to emergency drive main control valve 8 through the third pipeline and to brake 2 through the fourth pipeline, emergency release solenoid valve 7 are connected to emergency drive main control valve 8 through the fifth pipeline and to brake 2 through the sixth pipeline, emergency drive main control valve 8 are connected to hydraulic drive motor 1, emergency retraction solenoid valve 6, emergency release solenoid valve 7 and emergency drive main control valve 8 are all connected to hydraulic oil pipeline, in emergency working mode, they have an independent emergency control circuit to drive the hydraulic motor output speed and torque; controller 9 is used to control function conversion solenoid valve 3, servo valve 5, emergency retraction solenoid valve 6 and emergency release solenoid valve 7.

[0058] The leading edge flap drive device with emergency drive function of this application also includes two two-way valves 10, a first two-way valve and a second two-way valve, wherein the fourth pipe and the sixth pipe are respectively connected to the two inlets of the first two-way valve, and the outlet of the first two-way valve is installed with a seventh pipe; 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 the brake 2 through an eighth pipe.

[0059] In the preferred embodiment of this application, such as Figure 3 As shown, in order to achieve position monitoring and control, microswitches are installed at the maximum upper deflection position and the maximum lower deflection position of the rotary actuator housing, respectively. The controller 9 is used to control the function switching solenoid valve 3, servo valve 5, emergency retraction solenoid valve 6 and emergency release solenoid valve 7 according to the feedback signal of the microswitches. When the rudder surface deflects to the position and triggers the microswitches, it sends a micro signal to the controller 9 to achieve trigger monitoring and control.

[0060] In a preferred embodiment of this application, a mutual exclusion switching valve 11 is provided between the servo valve 5 and the emergency drive main control valve 8. When the leading edge flap drive device receives both the normal operation command signal and the emergency operation command signal simultaneously due to a controller 9 malfunction, the drive device can remain in the normal operation mode. When the system simultaneously receives the controller 9 position command signal and the emergency drive command signal, the servo mode SOV and the emergency retract SOV / emergency release SOV are simultaneously signaled. The high-pressure control oil in the mutual exclusion switching valve 11 cuts off the emergency operation oil circuit. At the same time, under the action of the control oil, the function switching valve 4 switches to the open position, and the hydraulic brake is released. At this time, the servo valve 5EHSV outputs the corresponding flow to the hydraulic motor according to the controller 9 position command signal, thereby achieving synchronous drive of the leading edge flap deflection.

[0061] The leading-edge flap drive device with emergency drive function of this application has an emergency drive function. For example... Figure 4 As shown, in emergency operating mode, controller 9 issues an emergency drive command, the emergency retraction / deployment SOV in the drive device opens, the emergency drive main control valve 8 opens under the action of control oil, the hydraulic brake 2 is released, and the mutual exclusion conversion valve 11 switches to the emergency operating position; according to the emergency retraction / deployment SOV command signal, the hydraulic drive device controls the emergency drive main control valve 8 to open and drive the hydraulic motor 1 to output through the emergency retraction / deployment SOV. When the microswitch detects that the leading edge flap has retracted / deployed to the required position, controller 9 cuts off the emergency retraction / deployment SOV control signal, the emergency drive main control valve 8 switches to the closed position, the hydraulic brake 2 brakes, and the leading edge flap is in a holding state.

[0062] In a preferred embodiment of this application, the emergency drive commands are divided into: a primary control law emergency retraction / deployment signal, a backup control law emergency retraction / deployment signal, and a cockpit emergency deployment signal. When a two-channel electrical fault occurs in the leading edge flap servo system, the system automatically switches to emergency operating mode according to the fault status, controlling the leading edge flap to retract or deploy according to the control law commands. When the pilot maneuvers the aircraft for landing, the cockpit signal requires the pilot to manually control the emergency switch to put the leading edge flap into emergency deployment mode to ensure a safe and stable landing. The system uses certain monitoring logic to control the connection and disconnection of the SOV within the leading edge flap drive device. The emergency operating mode SOV control logic is as follows: Figure 5 , Figure 6 As shown.

[0063] The leading-edge flap drive device with emergency drive function of this application has a normal operation mode, a ground maintenance mode, a fault protection mode, and an emergency operation mode. The fault protection mode includes a fail-safe mode and a fault operation mode. Figure 7 As shown, the switching methods for each working mode are as follows:

[0064] After the system is powered on, it performs a self-test within the motor.

[0065] During the self-test within the upper motor:

[0066] If a single-channel fault is detected, the system will enter fault operation mode.

[0067] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0068] If the internal self-test of the upper motor passes, then perform the pre-flight internal self-test;

[0069] During pre-flight in-flight self-test:

[0070] If a single-channel fault is detected, the system will enter fault operation mode.

[0071] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0072] If the pre-flight in-flight self-test passes, the aircraft will enter normal operating mode.

[0073] In normal working mode:

[0074] According to the self-test command inside the cycle machine, the cycle machine performs a self-test. If a single-channel fault is detected, it enters the fault working mode. If a dual-channel fault is detected, it enters the fail-safe mode.

[0075] When the system is on the ground and receives a self-test command from the maintenance unit, it enters the ground maintenance mode.

[0076] In normal operating mode, both control channels can receive controller command signals to drive the leading edge flap drive device, and the system continuously performs IFBIT.

[0077] In ground maintenance mode:

[0078] If a single-channel fault is detected, the system will enter fault operation mode.

[0079] If a dual-channel fault is detected, the system will enter fail-safe mode.

[0080] If the machine passes the self-test during maintenance, it will enter normal working mode.

[0081] In fault operation mode:

[0082] According to the self-test command inside the cycle machine, perform a self-test inside the cycle machine. If a dual-channel fault is detected, enter the fail-safe mode.

[0083] Fault-based operation (redundancy degradation): When IFBIT detects a fault in one control channel of the product, it switches to the operation of another normal control channel. In this mode, the control current of the single-channel servo valve is doubled, ensuring that the product's performance does not degrade.

[0084] In fail-safe mode:

[0085] Upon receiving an emergency work order, enter emergency work mode;

[0086] Fail-safe (fail-handling): When IFBIT detects a fault in both control channels of the system, the system enters a fail-safe state. In this fail-safe state, the product's hydraulic drive control channel will disconnect the SOV power supply to the drive system.

[0087] In emergency work mode:

[0088] Once emergency response measures are in place, the system will enter fail-safe mode.

[0089] In a preferred embodiment of this application, when the system is in normal working mode, fault working mode or fault safe mode, and receives an emergency drive command, the system can enter the emergency working mode. The controller 9 sends a retract / delay signal according to the emergency drive command to control the opening and closing of the emergency retract / delay solenoid valve in the PDU, so as to control the leading edge flap to retract / delay to a predetermined position.

[0090] The leading-edge flap drive device of this application with emergency drive function receives a command signal from the controller 9 when the system needs to switch to emergency working mode during aircraft flight. It drives the rotary actuator through the hydraulic drive motor 1 to work, causing the leading-edge flap surface to deflect, thereby improving flight safety and reliability and ensuring the stability of aircraft landing. The improved mode switching method ensures the safe and reliable operation of the servo actuation system.

[0091] 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 leading-edge flap drive device with emergency drive function, characterized in that, include: The control surface module includes a rotary actuator connected to the leading edge flap, the rotary actuator being connected to a hydraulic drive motor (1) and a brake (2). The servo control module includes a function switching solenoid valve (3), a function switching valve (4), and a servo valve (5). The function switching solenoid valve (3) is connected to the function switching valve (4) through a first pipeline and to the brake (2) through a second pipeline. The function switching valve (4) is connected to the servo valve (5), and the servo valve (5) is connected to the hydraulic drive motor (1). An emergency control module is provided, comprising an emergency solenoid valve (6), an emergency solenoid valve (7), and an emergency drive main control valve (8). The emergency solenoid valve (6) is connected to the emergency drive main control valve (8) via a third pipeline and to the brake (2) via a fourth pipeline. The emergency solenoid valve (7) is connected to the emergency drive main control valve (8) via a fifth pipeline and to the brake (2) via a sixth pipeline. The emergency drive main control valve (8) is connected to the hydraulic drive motor (1). The controller (9) is used to control the function switching solenoid valve (3), the servo valve (5), the emergency take-off solenoid valve (6), and the emergency release solenoid valve (7). A mutual exclusion switching valve (11) is provided between the servo valve (5) and the emergency drive main control valve (8).

2. The leading-edge flap drive device with emergency drive function according to claim 1, characterized in that, The function switching solenoid valve (3), the function switching valve (4), the emergency take-up solenoid valve (6), the emergency release solenoid valve (7), and the emergency drive main control valve (8) are all connected to the hydraulic oil pipeline.

3. The leading-edge flap drive device with emergency drive function according to claim 2, characterized in that, It also includes two two-way valves (10), 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 (2) through the eighth pipeline.

4. The leading-edge flap drive device with emergency drive function according to claim 3, characterized in that, The maximum upper and lower positions of the rotary actuator housing are respectively equipped with micro switches. The controller (9) is used to control the function conversion solenoid valve (3), the servo valve (5), the emergency take-off solenoid valve (6), and the emergency release solenoid valve (7) according to the feedback signal of the micro switches.

5. The leading-edge flap drive device with emergency drive function according to claim 4, characterized in that, The leading edge flap drive device has a normal operation mode, a ground maintenance mode, a fault protection mode, and an emergency operation mode. The fault protection mode includes a fail-safe mode and a fail operation mode.

6. The leading-edge flap drive device with emergency drive function according to claim 5, characterized in that, The switching method for the various operating modes of the leading edge flap drive device is as follows: After the system is powered on, it performs a self-test within the motor. During the self-test within the upper motor: If a single-channel fault is detected, the system will enter fault operation mode. If a dual-channel fault is detected, the system will enter fail-safe mode. If the internal self-test of the upper motor passes, then perform the pre-flight internal self-test; During pre-flight in-flight self-test: If a single-channel fault is detected, the system will enter fault operation mode. If a dual-channel fault is detected, the system will enter fail-safe mode. If the pre-flight in-flight self-test passes, the aircraft will enter normal operating mode. In normal working mode: According to the self-test command inside the cycle machine, the cycle machine performs a self-test. If a single-channel fault is detected, it enters the fault working mode. If a dual-channel fault is detected, it enters the fail-safe mode. When the system is on the ground and receives a self-test command from the maintenance unit, it enters the ground maintenance mode. In ground maintenance mode: If a single-channel fault is detected, the system will enter fault operation mode. If a dual-channel fault is detected, the system will enter fail-safe mode. If the machine passes the self-test during maintenance, it will enter normal working mode. In fault operation mode: According to the self-test command inside the cycle machine, perform a self-test inside the cycle machine. If a dual-channel fault is detected, enter the fail-safe mode. In fail-safe mode: Upon receiving an emergency work order, enter emergency work mode; In emergency work mode: Once emergency response measures are in place, the system will enter fail-safe mode.

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