A distributed redundancy aircraft control surface servo actuation system

Abstract

The application belongs to the field of aircraft servo actuating system design, and particularly relates to a distributed multi-redundancy aircraft control surface servo actuating system. The system mainly comprises a controller and an actuator. The controller is divided into two controllers, namely, a No. 1 controller and a No. 2 controller, and the two controllers jointly control four actuators. The two controllers jointly constitute a four-redundancy controller architecture, the No. 1 controller is an A channel and a B channel, and the No. 2 controller is a C channel and a D channel. The four actuators control corresponding aircraft control surfaces respectively, control surface 1, control surface 2 and control surface 3 are electrical three-redundancy, and control surface 4 is electrical four-redundancy. Each channel of the two controllers has a communication management module and a servo module. The communication management module exchanges information with a flight tube system through an external bus. Each communication management module transmits cross-channel data link data through an internal bus. The application can improve the safety of the aircraft while ensuring the functional performance of the control system.

Description

Technical Field

[0001] This application belongs to the field of aircraft servo actuation system design, and specifically relates to a distributed redundant aircraft control surface servo actuation system. Background Technology

[0002] Servo actuation systems control the movement of aircraft control surfaces and are critical systems affecting flight safety. For redundant servo control systems with multiple control surfaces, traditional control systems often employ a "one-to-many" control approach, which is simple and straightforward. However, if a single point of failure occurs in the controller, causing the actuation of multiple control surfaces to fail, the entire control system will malfunction, severely impacting aircraft flight safety.

[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 distributed redundant aircraft control surface servo actuation system to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A distributed redundant aircraft control surface servo actuation system includes:

[0007] A first controller, comprising an A-channel control unit and a B-channel control unit;

[0008] The second controller includes a C-channel control unit and a D-channel control unit;

[0009] The A-channel control unit, the B-channel control unit, the C-channel control unit, and the D-channel control unit each have a communication management module and a servo module. The communication management modules interact with the flight control system via an external bus, and different communication management modules interact with each other via an internal bus.

[0010] The control surface actuator includes a first control surface actuator, a second control surface actuator, a third control surface actuator, and a fourth control surface actuator. The first control surface actuator, the second control surface actuator, and the third control surface actuator each have three redundancy control modules, and the fourth control surface actuator has four redundancy control modules. Each of the redundancy control modules is electrically connected to the servo module.

[0011] In at least one embodiment of this application,

[0012] The A-channel control unit includes a first communication management module, an A-channel first servo module, and an A-channel second servo module; the B-channel control unit includes a second communication module and a B-channel first servo module.

[0013] The C-channel control unit includes a third communication management module, a C-channel first servo module, and a C-channel second servo module, while the D-channel control unit includes a fourth communication management module, a D-channel first servo module, and a D-channel second servo module.

[0014] In at least one embodiment of this application, the first communication management module, the second communication management module, the third communication management module, and the fourth communication management module respectively interact with the flight control system via an external bus, and the four communication management modules interact with each other via an internal bus.

[0015] In at least one embodiment of this application,

[0016] The first redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel A, the second redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel B, and the third redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel C.

[0017] The first redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel A, the second redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel C, and the third redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel D.

[0018] The first redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel A, the second redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel C, and the third redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel D.

[0019] The first redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel A, the second redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel B, the third redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel C, and the fourth redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel D.

[0020] In at least one embodiment of this application, the aircraft control surfaces controlled by the first control surface actuator and the aircraft control surfaces controlled by the second control surface actuator are strongly correlated control surfaces.

[0021] In at least one embodiment of this application, the aircraft control surface controlled by the fourth control surface actuator is the most critical control surface affecting flight safety.

[0022] The invention has at least the following beneficial technical effects:

[0023] The distributed redundant aircraft control surface servo actuation system of this application, based on the aircraft's control surface layout and system redundancy configuration, and considering the miniaturization and weight reduction of controller products, splits the traditional controller into separate components. The controller and actuators form an intersecting "distributed" control architecture. The controller is internally divided into boards according to the controlled object and function, thereby forming a distributed redundant servo actuation system, which can improve aircraft safety while ensuring the functional performance of the control system. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of a distributed redundant aircraft control surface servo actuation system according to one embodiment of this application. Detailed Implementation

[0025] 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.

[0026] 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.

[0027] The following is in conjunction with the appendix Figure 1 This application will be described in further detail.

[0028] This application provides a distributed redundant aircraft control surface servo actuation system, including: a first controller, a second controller, and control surface actuators.

[0029] Specifically, the first controller includes an A-channel control unit and a B-channel control unit. The A-channel control unit includes a first communication management module, an A-channel first servo module, and an A-channel second servo module. The B-channel control unit includes a second communication management module and a B-channel first servo module. The second controller includes a C-channel control unit and a D-channel control unit. The C-channel control unit includes a third communication management module, a C-channel first servo module, and a C-channel second servo module. The D-channel control unit includes a fourth communication management module, a D-channel first servo module, and a D-channel second servo module. The first, second, third, and fourth communication management modules interact with the flight control system via an external bus, and the four communication management modules interact with each other via an internal bus.

[0030] The control surface actuator includes a first control surface actuator, a second control surface actuator, a third control surface actuator, and a fourth control surface actuator. The first, second, and third control surface actuators each have three redundant control modules, while the fourth control surface actuator has four redundant control modules. Specifically, the first redundant control module of the first control surface actuator is electrically connected to the first servo module of channel A; the second redundant control module of the first control surface actuator is electrically connected to the first servo module of channel B; and the third redundant control module of the first control surface actuator is electrically connected to the first servo module of channel C. Similarly, the first redundant control module of the second control surface actuator is electrically connected to the second servo module of channel A; and the second redundant control module of the second control surface actuator is electrically connected to the second servo module of channel C. Electrical connections are established as follows: the third redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel D; the first redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel A; the second redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel C; the third redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel D; the first redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel A; the second redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel B; the third redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel C; and the fourth redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel D.

[0031] This application presents a distributed redundant aircraft control surface servo actuation system, such as Figure 1As shown, it mainly consists of controllers and actuators. It adopts a distributed architecture, with two controllers, Controller 1 and Controller 2, jointly controlling four actuators. The two controllers together form a quadruple-redundant controller architecture, with Controller 1 controlling channels A and B, and Controller 2 controlling channels C and D. The four actuators control the corresponding aircraft control surfaces. Control surfaces 1, 2, and 3 are electrically triple-redundant, while control surface 4 is electrically quadruple-redundant. Each channel of the two controllers has a communication management module and a servo module. The communication management module interacts with the flight control system via an external bus, receiving commands from the flight control system and reporting information to the servo system. Each communication management module communicates with the system via an internal bus through cross-channel data links. The servo module controls the actuators on the control surfaces, outputting control signals to the actuators via electrical hardwired connections and receiving feedback from the actuators.

[0032] This application presents a distributed redundant aircraft control surface servo actuation system. First, the redundancy configuration is determined based on the aircraft's top-level requirements. Critical control surfaces are configured with quadruple electrical redundancy, while other control surfaces are configured with triple electrical redundancy, requiring a total of 13 electrical channels. The allocation of electrical redundancy channels is comprehensively considered based on the control surface layout on the aircraft and the cable routing. Due to aircraft space constraints, the controller must be designed for miniaturization. The 13 servo control electrical channels are allocated to quadruple-redundant controllers, with each controller controlling at least three different control surface electrical channels. If the servo amplification section were a single module, the board size would be too large to fit within the controller; if each electrical channel of each control surface were equipped with a servo module, the controller backplane would be too large, resulting in increased overall size and weight, and higher system redundancy. Therefore, each channel of the controller is configured with one communication management module and two servo modules, with each servo module controlling a maximum of two control surfaces. The communication management module receives commands from the flight control system, performs command voting, and issues commands to each servo module. It also receives feedback from the servo modules and sends the information back to the flight control system. The servo module is used to control the actuators of the control surfaces, sending command signals to the actuators and receiving feedback signals to perform servo closed-loop control.

[0033] In a preferred embodiment of this application, the control surfaces 1 and 2 controlled by the first and second control surface actuators are strongly correlated and must be assigned to different servo modules. The control surface 4 controlled by the fourth control surface actuator, being the most critical control surface affecting flight safety, is configured with electrical quadruple redundancy and prioritizes channel isolation, thus being fixed to servo module 1. Considering both power and cable layout, control surfaces 1 and 4 are assigned to servo module 1, while control surfaces 2 and 3 are assigned to servo module 2. With this controller layout, the servo system requires a total of 7 servo modules. Considering module interchangeability and the actuation forms and types of actuators, each servo module is interchangeable; that is, the hardware configuration of the boards is completely identical, and the software simultaneously has the function of controlling 4 actuators. The controller chassis has a channel number identification function. Each servo module determines its own channel number and the actuator object it controls based on the backplane wiring, thereby calling the corresponding control program.

[0034] The distributed redundant aircraft control surface servo actuation system of this application takes into account control surface correlation, the degree of influence of control surfaces on flight safety, power and cable layout, and also considers the miniaturization and weight reduction of controller products, which can improve aircraft safety while ensuring the functional performance of the control system.

[0035] 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 distributed redundant aircraft control surface servo actuation system, characterized in that, include: A first controller, the first controller including an A-channel control unit and a B-channel control unit; The second controller includes a C-channel control unit and a D-channel control unit; The A-channel control unit, the B-channel control unit, the C-channel control unit, and the D-channel control unit each have a communication management module and a servo module. The communication management modules interact with the flight control system via an external bus, and different communication management modules interact with each other via an internal bus. A control surface actuator, comprising a first control surface actuator, a second control surface actuator, a third control surface actuator, and a fourth control surface actuator, wherein the first control surface actuator, the second control surface actuator, and the third control surface actuator each have three redundant control modules, and the fourth control surface actuator has four redundant control modules, wherein each of the redundant control modules is electrically connected to the servo module; The A-channel control unit includes a first communication management module, an A-channel first servo module, and an A-channel second servo module; the B-channel control unit includes a second communication module and a B-channel first servo module. The C-channel control unit includes a third communication management module, a C-channel first servo module, and a C-channel second servo module; the D-channel control unit includes a fourth communication management module, a D-channel first servo module, and a D-channel second servo module. The first redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel A, the second redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel B, and the third redundancy control module of the first control surface actuator is electrically connected to the first servo module of channel C. The first redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel A, the second redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel C, and the third redundancy control module of the second control surface actuator is electrically connected to the second servo module of channel D. The first redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel A, the second redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel C, and the third redundancy control module of the third control surface actuator is electrically connected to the second servo module of channel D. The first redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel A, the second redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel B, the third redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel C, and the fourth redundancy control module of the fourth control surface actuator is electrically connected to the first servo module of channel D.

2. The distributed redundant aircraft control surface servo actuation system according to claim 1, characterized in that, The first communication management module, the second communication management module, the third communication management module, and the fourth communication management module interact with the flight control system via an external bus, and the four communication management modules interact with each other via an internal bus.

3. The distributed redundant aircraft control surface servo actuation system according to claim 2, characterized in that, The aircraft control surfaces controlled by the first control surface actuator and the aircraft control surfaces controlled by the second control surface actuator are strongly correlated control surfaces.

4. The distributed redundant aircraft control surface servo actuation system according to claim 3, characterized in that, The control surfaces of the aircraft controlled by the fourth control surface actuator are the most critical control surfaces affecting flight safety.

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