CN109850134B - Aircraft landing gear system - Google Patents

Abstract

The present application belongs to the technical field of aircraft landing gear control design, and in particular relates to an aircraft landing gear system. The control system includes an instruction output device for outputting a control signal, which has two main modal output states and an emergency modal output state. The main modal control system; the emergency modal control system; the actuator, connected with the landing gear; wherein, the command output device is in the main modal output state, and the main modal control system receives and outputs the main modal control system according to the control signal Command; the command output device is in the emergency modal output state, the emergency modal control system receives and outputs the emergency modal control command according to the control signal; the actuator receives and acts according to the main modal control command or receives and according to the emergency modal control command. , so that the landing gear can achieve related functions. The two states of the command output device can be switched between each other, with a certain safety margin, thereby improving the safety of the control system.

Description

An aircraft landing gear system

technical field

The present application belongs to the technical field of aircraft landing gear control design, and in particular relates to an aircraft landing gear system.

Background technique

The aircraft landing gear system is designed to control the aircraft landing gear to perform related actions, including braking, turning and retraction, etc. It controls the landing gear to achieve related functions during the taxiing, takeoff, and landing process of the aircraft, which is related to the safety of the aircraft. At present, the design of aircraft landing gear system is mainly based on mechanical control, supplemented by a small amount of electrical control, or part of mechanical control and part of analog electronic/digital control. The above control methods have the following disadvantages:

1) The mechanical system has complex structure, large volume, heavy weight and large nonlinearity;

2) It is difficult to synthesize information, and it is not easy to realize complex control laws;

3) The control boundary protection function cannot be realized, and the pilot has a heavy control burden;

4) The security is low.

Therefore, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art.

SUMMARY OF THE INVENTION

An object of the present application is to provide an aircraft landing gear system that overcomes or alleviates at least one of the above-mentioned problems.

The technical solution of the present application is: an aircraft landing gear system, comprising:

The command output device is used to output the control signal, which has two states: the main mode output state and the emergency mode output state;

main modal control system;

Emergency modal control system;

an actuator, connected to the landing gear; wherein,

When the command output device is in the main mode output state, the main mode control system receives the control signal, generates the main mode control command according to the received control signal, and outputs the main mode control command;

When the command output device is in the emergency modal output state, the emergency modal control system receives the control signal, generates the emergency modal control instruction according to the received control signal, and outputs the emergency modal control instruction;

The actuator receives the main mode control command and acts according to the main mode control command it receives, or receives the emergency mode control command and acts according to the emergency mode control command it receives, thereby driving the landing gear to move .

Optionally, the main modal control system includes:

The command sensor receives the control signal and converts the received control signal into the corresponding electrical signal output, and the output electrical signal is called the control electrical signal;

The controller receives the control electrical signal, generates a main mode control instruction according to the received control electrical signal, and outputs the main mode control instruction.

Optionally, the control signal includes: a braking control signal, a turning control signal, and a retracting control signal;

There are several command sensors, including:

The brake command sensor receives the brake control signal and outputs the corresponding control electrical signal. The output control electrical signal is called the brake control electrical signal;

The turning command sensor receives the turning control signal and outputs the corresponding control electrical signal. The output control electrical signal is called the turning control electrical signal;

The retraction and release command sensor receives the retraction and release control signal, and outputs the corresponding control electrical signal, and the output control electrical signal is called the retraction and release control electrical signal;

There are multiple controllers, including:

The brake controller receives the brake control electrical signal and outputs the corresponding main mode control command. The main mode control command it outputs is called the main mode brake control command;

The turning controller receives the electrical signal of turning control, and outputs the corresponding main mode control command. The main mode control command it outputs is called the main mode turning control command;

The retracting and releasing controller receives the retracting and discharging control electrical signal, and outputs the corresponding main mode control command, and the main mode control command it outputs is called the main mode retracting and discharging control command.

Optionally, the main modal control system further includes:

The wheel speed feedback sensor collects the wheel speed status information of the landing gear, and outputs the collected wheel speed status information of the landing gear;

The aircraft speed feedback sensor collects the speed state information of the aircraft, and outputs the collected speed state information of the aircraft;

The position lock feedback sensor collects the position status information of the landing gear, and outputs the position status information of the landing gear collected by it;

The brake controller receives the brake control electrical signal and the wheel speed status information of the landing gear, and outputs the main mode brake control command according to the received brake control electrical signal and the wheel speed status information of the landing gear;

The turning controller receives the turning control electrical signal and the speed state information of the aircraft, and outputs the main mode turning control command according to the turning control electrical signal and the speed state information of the aircraft;

The retraction controller receives the retraction control electrical signal and the position status information of the landing gear, and outputs the main mode retraction control command according to the retraction control electrical signal and the position status information of the landing gear.

Optionally, there are multiple brake command sensors, and each brake command sensor has two states: a working state and a standby state; wherein, one brake command sensor is in a working state, which can receive a brake control signal and output a brake control electrical signal, The rest of the brake command sensors are in standby state;

There are multiple turning command sensors, and each turning command sensor has two states: working state and standby state; among them, one turning command sensor is in working state, which can receive turning control signals and output turning control electrical signals, and the rest of the turning command sensors are in a working state. in a standby state;

There are multiple retractable command sensors, and each retractable command sensor has two states: a working state and a standby state; among them, one retracting command sensor is in a working state, which can receive the brake control signal and output the brake control electrical signal, and the rest The retraction command sensor is in standby.

Optionally, there are two brake controllers, and each brake controller has two states: a working state and a standby state; wherein, one brake controller is in a working state, which can receive the brake control electrical signal and the wheel speed state of the landing gear. information, and output the main mode brake control command, and the other brake controller is in the standby state;

There are two turning controllers, and each turning controller has two states: working state and standby state; among them, one turning controller is in working state, which can receive the turning control electrical signal and the speed state information of the aircraft, and output the main mode. state turn control command, the other turn controller is in standby state;

There are two retractable controllers, and each retractable controller has two states: working state and standby state; among them, one retractable controller is in the working state, which can receive the retractable control electrical signal and the position state information of the landing gear , and output the main mode retraction control command, and another retraction controller is in the standby state.

Optionally, there are multiple wheel speed feedback sensors, and each wheel speed feedback sensor has two states: a working state and a standby state; wherein, one wheel speed feedback sensor is in a working state, which can collect the wheel speed state information of the landing gear, And output the wheel speed status information of the landing gear collected by it, and the other wheel speed feedback sensors are in standby state;

There are multiple aircraft speed feedback sensors, and each aircraft speed feedback sensor has two states: a working state and a standby state; among them, one aircraft speed feedback sensor is in a working state, which can collect the speed state information of the aircraft, and use the collected information on the aircraft. The speed status information is output, and the other wheel speed feedback sensors are in standby state;

There are multiple position lock feedback sensors, and each position lock feedback sensor has two states: working state and standby state; among them, one position lock feedback sensor is in the working state, which can collect and output the position state information of the landing gear, and use it to The collected position status information of the landing gear is output, and the rest of the position lock feedback sensors are in standby status.

Optionally, the emergency modal control system includes:

The emergency modal brake control system receives the brake control signal, generates the corresponding emergency modal control command according to the received brake control signal, and outputs the generated emergency modal control command. The output emergency modal control command is called the emergency modal control command. It is the emergency modal brake control command;

The emergency modal turning control system receives the turning control signal, generates the corresponding emergency modal control command according to the received turning control signal, and outputs the generated emergency modal control command. The output emergency modal control command is called the emergency modal control command. It is the emergency modal turning control command;

The emergency modal turning control system receives the retractable control signal, generates corresponding emergency mode control instructions according to the retractable control signal it receives, and outputs the generated emergency mode control instructions, and the output emergency mode control instructions The command is called emergency modal retraction control command.

Optionally, there are multiple actuators, including:

The brake actuator receives the main modal brake control command and acts according to the main modal brake control command it receives, or receives the emergency modal brake control command and acts according to the emergency modal brake control command it receives, thereby Drive the landing gear to move, so that the landing gear can realize the braking function;

The turning actuator receives the main mode turning control command and acts according to the main mode turning control command it receives, or receives the emergency mode turning control command and acts according to the emergency mode turning control command it receives, thereby Drive the landing gear to move, so that the landing gear can realize the turning function;

The retractable actuator receives the main mode retraction control command, and acts according to the main mode retraction control command it receives, or receives the emergency mode retraction control command, and according to the emergency mode retraction control it receives Command action, so as to drive the landing gear to move, so that the landing gear can realize the retractable function.

Optionally, there are a plurality of brake actuators, and each brake actuator has two states: a working state and a standby state; wherein, one brake actuator is in a working state, which can receive and control the command according to the main mode brake or accept and Act according to the emergency modal brake control command, and the other brake actuators are in standby state;

There are multiple turning actuators, and each turning actuator has two states: a working state and a standby state; among them, one turning actuator is in a working state, which can receive and follow the main mode turning control command or receive and according to the emergency mode. The turning control command is in action, and the other turning actuators are in a standby state;

There are multiple retractable actuators, and each retractable actuator has two states: a working state and a standby state; among them, one retractable actuator is in a working state, which can receive and retract control instructions according to the main mode or receive and Acts according to the emergency mode retraction control command, and the rest retraction actuators are in standby state.

The present application has at least the following beneficial technical effects: an aircraft landing gear system is provided, wherein the command output device is used to output a control signal, and has two states: a main modal output state and an emergency modal output state, and one of the two states is It can be switched between, with a certain safety margin, thereby improving the safety of the control system.

Description of drawings

FIG. 1 is a schematic structural diagram of an aircraft landing gear system of the present application.

Detailed ways

In order to make the implementation purpose, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to be used to explain the present application, but should not be construed as a limitation to the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application. The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of this application, it should be understood that the terms "center", "portrait", "horizontal", "front", "rear", "left", "right", "vertical", "horizontal", The orientation or positional relationship indicated by "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying The device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.

The present application will be further described in detail below with reference to FIG. 1 .

An aircraft landing gear system, comprising:

The command output device 1 is used for outputting a control signal, which has two states of a main modal output state and an emergency modal output state;

main modal control system;

Emergency modal control system;

The actuator 5 is connected with the landing gear; wherein,

When the command output device 1 is in the main mode output state, the main mode control system receives the control signal, generates the main mode control command according to the received control signal, and outputs the main mode control command;

When the command output device 1 is in the emergency modal output state, the emergency modal control system receives the control signal, generates the emergency modal control instruction according to the received control signal, and outputs the emergency modal control instruction;

The actuator 5 receives the main mode control command and acts according to the main mode control command it receives, or receives the emergency mode control command and acts according to the emergency mode control command it receives, thereby driving the landing gear to carry out the operation. sports.

Further, the main mode control system includes: an instruction sensor 2, which receives a control signal, and converts the received control signal into a corresponding electrical signal for output, and the output electrical signal is called a control electrical signal; a controller 4, receives the control electrical signal. signal, and generate the main mode control command according to the control electrical signal it receives, and output the main mode control command.

Further, the control signal includes: a braking control signal, a turning control signal and a retracting control signal; there are multiple command sensors 2, including: a braking command sensor 21, which receives the braking control signal and outputs the corresponding control electrical signal, the output of which is The control electrical signal is called the brake control electrical signal; the turning command sensor 22 receives the turning control signal and outputs the corresponding control electrical signal, and the output control electrical signal is called the turning control electrical signal; the retraction command sensor 23 receives the retraction control signal , and output the corresponding control electrical signal, the output control electrical signal is called the retraction control electrical signal; the controller 4 has multiple, including: the brake controller 41, receives the brake control electrical signal, and outputs the corresponding main mode control signal command, the main mode control command it outputs is called the main mode brake control command; the turning controller 42 receives the turning control electrical signal, and outputs the corresponding main mode control command, and the output main mode control command is called the main mode control command. The main mode turning control command; the retraction controller 43 receives the retraction control electrical signal and outputs the corresponding main mode control command, and the output main mode control command is called the main mode retraction control command.

Further, the main mode control system also includes: a wheel speed feedback sensor 31, which collects the wheel speed state information of the landing gear, and outputs the collected wheel speed state information of the landing gear; an aircraft speed feedback sensor 32, which collects the wheel speed state information of the aircraft. speed status information, and output the collected speed status information of the aircraft; the position lock feedback sensor 33 collects the position status information of the landing gear, and outputs the collected position status information of the landing gear; the brake controller 41 receives The brake control electrical signal and the wheel speed status information of the landing gear, and output the main mode brake control command according to the received brake control electrical signal and the wheel speed status information of the landing gear; the turning controller 42 receives the turning control electrical signal and the aircraft's wheel speed status information. The speed state information, and output the main mode turn control command according to the turning control electrical signal and the speed state information of the aircraft; And the position state information of the landing gear output the main mode retraction control command.

Further, there are multiple brake command sensors 21, and each brake command sensor 21 has two states: a working state and a standby state; wherein, one brake command sensor 21 is in a working state, which can receive a brake control signal and output a brake control signal. signal, the other brake command sensors 22 are in standby state; there are multiple turning command sensors 22, and each turning command sensor 22 has two states: working state and standby state; wherein, one turning command sensor 22 is in working state, which can receive turning control signal, and output the turning control electrical signal, and the other turning command sensors 22 are in standby state; there are multiple retractable command sensors 23, and each retractable command sensor 23 has two states: working state and standby state; The command sensor 23 is in the working state, it can receive the brake control signal and output the brake control electrical signal, and the other retraction command sensors 23 are in the standby state.

Further, there are two brake controllers 41, and each brake controller 41 has two states: a working state and a standby state; wherein, one brake controller 41 is in a working state, which can receive the brake control electrical signal and the wheel of the landing gear. speed state information, and output the main mode brake control command, and the other brake controller 41 is in the standby state; there are two turning controllers 42, and each turning controller 42 has two states: working state and standby state; among them, one The turning controller 42 is in a working state, it can receive the turning control electrical signal and the speed state information of the aircraft, and output the main mode turning control command, and the other turning controller 42 is in a standby state; there are two retractable controllers 43, Each retractable controller 43 has two states: a working state and a standby state; wherein, one retractable controller 43 is in a working state, which can receive the retractable control electrical signal and the position state information of the landing gear, and output the main mode The retraction control command, the other retraction controller 43 is in a standby state.

Further, there are multiple wheel speed feedback sensors 31, and each wheel speed feedback sensor 31 has two states: a working state and a standby state; wherein, one wheel speed feedback sensor 31 is in a working state, which can collect the wheel speed state of the landing gear information, and output the wheel speed status information of the landing gear collected by it, and the other wheel speed feedback sensors 31 are in standby state; there are multiple aircraft speed feedback sensors 32, and each aircraft speed feedback sensor 32 has a working state and a standby state. state; wherein, an aircraft speed feedback sensor 32 is in a working state, it can collect the speed state information of the aircraft, and output the speed state information of the aircraft collected by it, and the other wheel speed feedback sensors 31 are in a standby state; the position lock feedback sensor 33 There are multiple, each position lock feedback sensor 33 has two states: working state and standby state; among them, one position lock feedback sensor 33 is in working state, which can collect and output the position state information of the landing gear, and collect the collected information. The position status information of the landing gear is output, and the other position lock feedback sensors 33 are in standby status.

The above belongs to the redundant configuration of the main mode control system. When one of its channels fails, it can automatically switch to another channel to work, so as to improve the safety performance of the control system. The functions of the three aspects are set up with relatively independent control channels, which reduces the mutual influence and ensures the control performance of the control system.

Further, the emergency modal control system includes: an emergency modal braking control system 61, which receives a braking control signal, generates a corresponding emergency modal control instruction according to the received braking control signal, and uses the generated emergency modal control instruction. output, the emergency modal control instruction outputted by it is called emergency modal braking control instruction; the emergency modal turning control system 62 receives the turning control signal, and generates the corresponding emergency modal control instruction according to the received turning control signal, and The generated emergency modal control instructions are output, and the output emergency modal control instructions are called emergency modal turning control instructions; the emergency modal turning control system 62 receives the retraction control signal, and controls the retraction and retraction according to the received retraction control instructions. The signal generates corresponding emergency modal control instructions, and the generated emergency modal control instructions are output, and the output emergency modal control instructions are called emergency modal retraction control instructions.

The control loop of the emergency modal control system is designed to be independent of the main modal control loop, and can switch to the emergency modal control system when the main modal control system fails. It can be understood by those skilled in the art that the emergency modal control system belongs to the supportive control system, which can adopt simple and direct control, such as the control method mentioned in the background art, which adopts the design of direct mechanical chain.

Further, there are multiple actuators 5, including: a brake actuator 51, which receives the main modal brake control command, and performs actions according to the main modal brake control command it receives, or receives the emergency modal brake control command, and according to The emergency modal braking control command received by it acts, thereby driving the landing gear to move, so that the landing gear can realize the braking function; the turning actuator 52 receives the main mode turning control command, and according to the main mode turning control command it receives Carry out actions, or receive emergency modal turning control instructions, and act according to the emergency modal turning control instructions received, thereby driving the landing gear to move, so that the landing gear can realize the turning function; retract the actuator 53 to receive the main mode The retractable and retractable control instructions, and act according to the main mode retraction and retraction control instructions received, or receive emergency mode retraction and retraction control instructions, and act according to the emergency mode retraction and retraction control instructions received, thereby driving the landing gear to carry out Movement, so that the landing gear realizes the retractable function.

Further, there are a plurality of brake actuators 51, and each brake actuator has two states: a working state and a standby state; wherein, one brake actuator 51 is in a working state, which can receive and according to the main mode brake control command or accept. And act according to the emergency modal brake control command, the other brake actuators 51 are in standby state; there are multiple turning actuators 52, and each turning actuator has two states: working state and standby state; among them, one turning actuator 52 In the working state, it can receive and act according to the main mode turning control command or receive and act according to the emergency mode turning control command, and the other turning actuators 52 are in a standby state; there are multiple retractable actuators 53, each retractable The actuator has two states: a working state and a standby state; among them, one retractable actuator 53 is in a working state, and it can receive and retract control instructions according to the main mode or receive and act according to the emergency mode retraction control instructions, The rest of the retractable actuators 53 are in a standby state.

The control system disclosed in this embodiment generally adopts the control configuration of "main modal control system + emergency modal control system", wherein each loop of the main modal control system is independent of each other and adopts "electrical signal transmission + digital control". +Redundant configuration" control method.

The control configuration of the above-mentioned "main mode control system + emergency mode control system" is mainly to ensure high safety, which includes two meanings: First, the control system of the main mode only needs to have appropriately high safety. , in this embodiment, an appropriate redundancy design is carried out. Second, the emergency modal control system only needs to ensure basic functions and does not require high performance. In this embodiment, a simple direct mechanical chain design is used.

The control method of "electrical signal transmission + digital control + redundant configuration" is to give full play to the advantages of convenient electrical signal transmission, reliable digital solution, and easy synthesis to ensure the excellent performance of the main mode control system; redundant configuration is to ensure Appropriate security and mission reliability. In order to ensure the excellent performance of the landing gear control system, the application of the above-mentioned control configuration and control method is comprehensive. Compared with the existing technology, the benefits are obvious, mainly reflected in the following aspects:

1) The redundant configuration method makes the security and mission reliability higher, and the survivability is higher;

2) Due to the advantages of digital control, it is easy to realize complex control laws and is not limited by the control object. In addition, the digital signal is not disturbed, there is no nonlinearity, the solution is reliable, and it is easy to achieve more advanced functions and better performance;

3) It can realize the protection function of the control boundary, effectively reduce the pilot's control burden, and is more conducive to the safety of the aircraft.

4) Small size, light weight, high power-to-weight ratio, and more convenient installation and arrangement, which are beneficial to improve the overall performance of the aircraft.

The above are only specific embodiments of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed in the present application, All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims (7)

1. An aircraft landing gear system, comprising:

the command output device (1) is used for outputting a control signal and has two states of a main mode output state and an emergency mode output state;

a master mode control system;

an emergency modality control system;

the actuating mechanism (5) is connected with the landing gear; wherein,

when the instruction output device (1) is in the master mode output state, the master mode control system receives the control signal, generates a master mode control instruction according to the received control signal, and outputs the master mode control instruction;

when the instruction output device (1) is in the emergency mode output state, the emergency mode control system receives the control signal, generates an emergency mode control instruction according to the received control signal and outputs the emergency mode control instruction;

the execution mechanism (5) receives the main mode control instruction and acts according to the main mode control instruction received by the execution mechanism, or receives the emergency mode control instruction and acts according to the emergency mode control instruction received by the execution mechanism, so that the landing gear is driven to move; the master mode control system includes:

the command sensor (2) receives the control signal and converts the received control signal into a corresponding electric signal to be output, and the output electric signal is called as a control electric signal;

the controller (4) receives the control electric signal, generates a main mode control command according to the received control electric signal, and outputs the main mode control command;

the control signal includes: a brake control signal, a turning control signal and a retraction control signal;

the instruction sensors (2) are multiple and comprise:

the brake command sensor (21) receives the brake control signal and outputs a corresponding control electric signal, wherein the output control electric signal is called a brake control electric signal;

the turning command sensor (22) receives the turning control signal and outputs a corresponding control electric signal, and the output control electric signal is called as a turning control electric signal;

the retraction instruction sensor (23) receives the retraction control signal and outputs a corresponding control electrical signal, and the output control electrical signal is called a retraction control electrical signal;

a plurality of said controllers (4) comprising:

the brake controller (41) receives the brake control electric signal and outputs a corresponding main mode control command, and the output main mode control command is called as a main mode brake control command;

the turning controller (42) receives the turning control electric signal and outputs a corresponding main mode control command, and the output main mode control command is called as a main mode turning control command;

the retraction controller (43) receives the retraction control electric signal and outputs a corresponding main mode control command, and the output main mode control command is called a main mode retraction control command; the master mode control system further comprises:

the wheel speed feedback sensor (31) is used for acquiring the wheel speed state information of the landing gear and outputting the acquired wheel speed state information of the landing gear;

an aircraft speed feedback sensor (32) for acquiring the speed state information of the aircraft and outputting the acquired speed state information of the aircraft;

a position lock feedback sensor (33) that collects position status information of the landing gear and outputs the collected position status information of the landing gear;

the brake controller (41) receives the brake control electrical signal and the wheel speed state information of the landing gear, and outputs the master mode brake control instruction according to the received brake control electrical signal and the wheel speed state information of the landing gear;

the turning controller (42) receives the turning control electric signal and the speed state information of the airplane and outputs the main-mode turning control instruction according to the turning control electric signal and the speed state information of the airplane;

and the retraction controller (43) receives the retraction control electrical signal and the position state information of the landing gear, and outputs the main mode retraction control instruction according to the retraction control electrical signal and the position state information of the landing gear.

2. The aircraft landing gear system of claim 1,

the number of the brake command sensors (21) is multiple, and each brake command sensor (21) has two states of a working state and a standby state; one of the brake command sensors (21) is in a working state, can receive the brake control signal and output the brake control electric signal, and the rest of the brake command sensors (21) are in a standby state;

a plurality of turning command sensors (22) are provided, and each turning command sensor (22) has two states of a working state and a standby state; wherein, one of the turn command sensors (22) is in a working state, can receive the turn control signal and output the turn control electric signal, and the other turn command sensors (22) are in a standby state;

the number of the deploying and retracting instruction sensors (23) is multiple, and each deploying and retracting instruction sensor (23) has two states of a working state and a standby state; one of the retraction command sensors (23) is in a working state and can receive the brake control signal and output the brake control signal, and the other retraction command sensors (23) are in a standby state.

3. An aircraft landing gear system according to claim 2,

the number of the brake controllers (41) is two, and each brake controller (41) has two states, namely a working state and a standby state; one of the brake controllers (41) is in a working state, and can receive the brake control electric signal and the wheel speed state information of the landing gear and output the main mode brake control command, and the other brake controller (41) is in a standby state;

the number of the turning controllers (42) is two, and each turning controller (42) has two states of a working state and a standby state; wherein one of the turning controllers (42) is in an operating state, capable of receiving the turning control electrical signal and the speed state information of the aircraft and outputting the main-mode turning control command, and the other turning controller (42) is in a standby state;

the number of the retraction controllers (43) is two, and each retraction controller (43) has two states, namely a working state and a standby state; one of the retraction controllers (43) is in a working state, and can receive the retraction control electric signal and the landing gear position state information and output the main mode retraction control instruction, and the other retraction controller (43) is in a standby state.

4. An aircraft landing gear system according to claim 3,

the number of the wheel speed feedback sensors (31) is multiple, and each wheel speed feedback sensor (31) has two states of a working state and a standby state; one wheel speed feedback sensor (31) is in a working state, can acquire wheel speed state information of the landing gear and output the acquired wheel speed state information of the landing gear, and the other wheel speed feedback sensors (31) are in a standby state;

a plurality of aircraft speed feedback sensors (32) are provided, and each aircraft speed feedback sensor (32) has two states of a working state and a standby state; one airplane speed feedback sensor (32) is in a working state, can acquire the speed state information of the airplane and output the acquired speed state information of the airplane, and the other wheel speed feedback sensors (31) are in a standby state;

the position lock feedback sensors (33) are multiple, and each position lock feedback sensor (33) has two states of a working state and a standby state; wherein, one position lock feedback sensor (33) is in a working state, can collect and output the position state information of the landing gear, and output the collected position state information of the landing gear, and the other position lock feedback sensors (33) are in a standby state.

5. An aircraft landing gear system according to claim 4, wherein the emergency mode control system comprises:

the emergency modal brake control system (61) receives the brake control signal, generates a corresponding emergency modal control command according to the received brake control signal, and outputs the generated emergency modal control command, wherein the output emergency modal control command is called as an emergency modal brake control command;

the emergency mode turning control system (62) receives the turning control signal, generates a corresponding emergency mode control command according to the turning control signal received by the turning control system, and outputs the generated emergency mode control command, wherein the output emergency mode control command is called as an emergency mode turning control command;

and the emergency modal turning control system (62) receives the retraction control signal, generates a corresponding emergency modal control instruction according to the retraction control signal received by the retraction control system, and outputs the generated emergency modal control instruction, wherein the output emergency modal control instruction is called an emergency modal retraction control instruction.

6. Aircraft landing gear system according to claim 5, wherein there are a plurality of actuators (5) comprising:

the brake actuating mechanism (51) receives the main mode brake control command and acts according to the main mode brake control command received by the brake actuating mechanism, or receives the emergency mode brake control command and acts according to the emergency mode brake control command received by the brake actuating mechanism, so that the landing gear is driven to move, and the landing gear realizes a brake function;

the turning execution mechanism (52) receives the main mode turning control instruction and acts according to the main mode turning control instruction received by the turning execution mechanism, or receives an emergency mode turning control instruction and acts according to the emergency mode turning control instruction received by the turning execution mechanism, so that the landing gear is driven to move, and the landing gear realizes a turning function;

and the retraction executing mechanism (53) receives the main mode retraction control instruction and acts according to the received main mode retraction control instruction, or receives an emergency mode retraction control instruction and acts according to the received emergency mode retraction control instruction, so that the landing gear is driven to move, and the landing gear realizes the retraction function.

7. The aircraft landing gear system of claim 6,

the number of the brake actuating mechanisms (51) is multiple, and each brake actuating mechanism has two states of a working state and a standby state; one of the brake actuating mechanisms (51) is in a working state, can receive and act according to the main mode brake control instruction or the emergency mode brake control instruction, and the rest of the brake actuating mechanisms (51) are in a standby state;

a plurality of turning actuating mechanisms (52) are provided, and each turning actuating mechanism has two states of an operating state and a standby state; wherein, one of the turning executing mechanisms (52) is in a working state, can receive and act according to the main mode turning control command or receive and act according to the emergency mode turning control command, and the rest of the turning executing mechanisms (52) are in a standby state;

the number of the retractable executing mechanisms (53) is multiple, and each retractable executing mechanism has two states of a working state and a standby state; one of the deploying and retracting execution mechanisms (53) is in a working state, can receive and retract control instructions according to the main mode or receive and act according to the emergency mode deploying and retracting control instructions, and the other deploying and retracting execution mechanisms (53) are in a standby state.

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