Aircraft braking and turning comprehensive integrated control system based on signal sharing

Abstract

The invention belongs to the technical field of airplane braking and turning control, and relates to an airplane braking and turning comprehensive integrated control system based on signal sharing, which comprises a control computer, a turning execution mechanism and a braking execution mechanism, and is characterized in that the control computer comprises a control module, a driving module and an interface module; the interface module is connected with the control module, the control module is connected with the driving module, the driving module is connected with the brake executing mechanism and the turning executing mechanism, the brake executing mechanism drives and controls a main airplane wheel to brake, and the turning executing mechanism drives and controls a front airplane wheel to deflect. According to the invention, maneuvering coordination of ground course control during taxiing of the aircraft is realized, and reliable braking and flexible turning of the aircraft are ensured.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft braking and turning control, relates to the design of an aircraft braking and turning integrated control system based on signal sharing, relates to the integrated design of an aircraft braking system and a turning system, and specifically relates to an aircraft braking and turning integrated control system based on signal sharing. Background Art

[0002] Braking and turning are two core technologies of aircraft ground control. The differential braking function and turning function have certain functional complexities in aircraft heading control, and they are mutually redundant in function. They have outstanding effects in correcting the aircraft heading and improving the aircraft ground safety. At present, the aircraft braking system and turning system are mostly controlled by independent systems, and most of them adopt the electric control system. The braking system is operated by the pilot in the cockpit to operate the pedals, and the control instructions are transmitted through electrical signals. The control box processes the transmitted electrical signals, and outputs electrical signals to control the brake valve to output the brake pressure to control the brake. The differential brake is controlled by outputting different brake pressures on the left and right. The turning system is operated by the pilot in the cockpit to operate the pedals, and the control instructions are transmitted through electrical signals. The control box processes the transmitted electrical signals, and outputs electrical signals to control the actuator to deflect the front wheel to complete the turn. Since the braking system and the turning system are independently controlled, each control accessory is independent of each other, and there are a large number of cross leads for the related control signals to be sent to the two systems respectively, which will occupy a lot of wiring and installation space on the aircraft, occupy the weight of the aircraft, and is also not conducive to the coordinated control of the aircraft heading. Summary of the invention

[0003] Purpose of the present invention:

[0004] In order to achieve coordinated control of braking and turning during aircraft heading control, reduce cross-wires in aircraft signal information transmission, realize computer software and hardware resource sharing, and meet aircraft weight reduction requirements and safety requirements, the present invention proposes an aircraft braking and turning integrated control system based on signal sharing, which realizes maneuverable coordination of ground heading control during aircraft taxiing and ensures reliable braking and flexible turning of the aircraft.

[0005] The technical solution of the present invention:

[0006] A signal-sharing-based integrated control system for aircraft braking and turning comprises a control computer, a turning actuator and a brake actuator. The control computer comprises a control module, a drive module and an interface module. The interface module is connected to the control module, which is connected to the drive module. The drive module is respectively connected to the brake actuator and the turning actuator. The brake actuator drives and controls the braking of the aircraft's main wheels, and the turning actuator drives and controls the deflection of the front wheels.

[0007] Furthermore, the control computer also includes a power module, which supplies power to the control module, the drive module and the interface module respectively.

[0008] Furthermore, the interface module is internally provided with an interconnected main acquisition unit and a backup acquisition unit to realize dual-redundancy acquisition of signals.

[0009] Furthermore, the power module is internally provided with an interconnected main power supply unit and a backup power supply unit to realize dual-redundancy power supply.

[0010] Furthermore, the control module is internally provided with an interconnected main control board and a backup control board to realize dual-redundancy control.

[0011] Furthermore, the driving module is internally provided with an interconnected main driving board and a backup driving board to realize dual-redundancy driving.

[0012] Furthermore, the interface module receives external flight control status, electromechanical status, inertial navigation, aircraft braking and turning control signals.

[0013] Furthermore, the interface module is connected to a brake command sensor disposed on the main engine wheel, and the brake command sensor sends the main engine wheel load and wheel speed signals to the interface module.

[0014] The interface module is connected to a turning command sensor arranged on the front wheel, and the turning command sensor sends a front wheel load and turning angle signal to the interface module.

[0015] Beneficial effects of the present invention:

[0016] The present invention proposes an aircraft braking and turning integrated control system based on signal sharing, which can realize aircraft braking and turning integrated control, realize aircraft flight control state, electromechanical state, inertial navigation, wheel load and wheel speed signal sharing and distribution in a signal sharing manner, wherein the flight control state and electromechanical state signals communicate with the control computer through the bus, realize the integrated control of braking and turning, effectively ensure the maneuvering and coordination performance of the aircraft in heading control, and reduce the pilot's operating burden. This braking and turning integrated control system has been successfully used in a certain type of aircraft, and has achieved good social and economic benefits. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a system principle diagram of the present invention. DETAILED DESCRIPTION

[0018] The present invention is based on the design and use requirements of a certain type of aircraft. During the taxiing process of the aircraft, the braking function and the turning function of the aircraft are basically used together. In particular, during the turning process, differential braking and turning are used simultaneously to realize rapid heading control of the aircraft. A comprehensive integrated control system for braking and turning is adopted, which can collect aircraft heading control data in real time and realize coordinated control of braking and turning. At the same time, both the braking system and the turning system will use aircraft signal information such as flight control status, electromechanical status, inertial navigation, wheel load and wheel speed. A comprehensive integrated control system for braking and turning is adopted to realize computer module and signal sharing, avoid waste of control system software and hardware resources, reduce aircraft heading control related accessories, reduce aircraft wiring, and reduce aircraft weight.

[0019] The invention discloses an aircraft braking and turning integrated control system based on signal sharing, which mainly comprises a control computer, a braking actuator, a turning actuator, a command sensor, a wheel speed sensor and the like.

[0020] For a certain type of aircraft design, the following problems are mainly solved:

[0021] 1. Adopt a comprehensive integrated control system for braking and turning to realize signal information sharing and distribution inside the computer, realize computer hardware module and signal sharing, avoid waste of control system software and hardware resources, reduce aircraft heading control related accessories, reduce aircraft wiring, and reduce aircraft weight.

[0022] 2. A dual-redundancy control computer is used to complete the integrated control of braking and turning, receive the braking and turning control instructions on the aircraft, and comprehensively process the relevant signals in combination with the input or collected flight control status, electromechanical status, inertial navigation, wheel load and wheel speed signals. According to the current status of the aircraft, the comprehensive control signal of aircraft braking and turning is output, and the aircraft heading control is associated with the aircraft attitude. After the control computer receives the aircraft status signal, it outputs different differential braking pressures and front wheel turning deflection signals to maximize the maneuverability and coordination performance of the aircraft in heading control.

[0023] Specifically, Figure 1 As shown in the figure, the control system mainly realizes the integrated control of braking and turning through a dual-redundancy computer. The control computer is composed of a power module, a control module, a drive module and an interface module. The external signals mainly include flight control status, electromechanical status, inertial navigation, wheel load and wheel speed signals. The flight control status and electromechanical status signals communicate with the control computer through the bus. The interface module is connected to the control module, the control module is connected to the drive module, and the drive module is connected to the brake actuator and the turn actuator respectively. The brake actuator drives and controls the aircraft main wheel brakes, and the turn actuator drives and controls the front wheel deflection; the power module, the power module is connected to the control module, the drive module and the interface module respectively.

[0024] Among them, the power module is used to supply power to the control module, drive module and interface module; the control module is used to realize signal integration and control signal output; the drive module is used to receive control signals and drive the braking and turning actuators; the interface module is used for control signal, aircraft status signal and feedback signal collection and distribution.

[0025] When the aircraft is taxiing, the brake control signal is input through the brake command sensor installed under each pedal of the front and rear pilots, which senses the pilot's braking force and outputs an electrical signal proportional to the pedal force to the control computer; the turn control signal is input to the control computer through the switch signal in the cockpit and the bus communication receiving the turn control command signal issued by the electromechanical management computer and the flight control management computer.

[0026] The control computer makes a comprehensive judgment based on the size of the above instructions, combined with signals such as the flight control status, electromechanical status, inertial navigation, wheel load and wheel speed, and controls the output signals to the braking and turning drive modules. Ultimately, the actuator controls the braking pressure and turning output to ensure that the aircraft heading control matches the aircraft status, thereby achieving higher braking efficiency and turning efficiency, and ultimately completing the aircraft braking and turning control.

Claims

1. An integrated control system for aircraft braking and turning based on signal sharing, characterized in that: It includes a control computer, a turning actuator, and a braking actuator. The control computer includes a control module, a driving module and an interface module. The interface module is connected to the control module, the control module is connected to the driving module, the driving module is respectively connected to the braking actuator and the turning actuator. The braking actuator drives and controls the braking of the main wheels of the aircraft, and the turning actuator drives and controls the deflection of the front wheels.

2. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The control computer also includes a power supply module, which supplies power to the control module, the drive module and the interface module respectively.

3. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The interface module is internally provided with an interconnected main acquisition unit and a backup acquisition unit to realize dual-redundancy acquisition of signals.

4. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The power module is internally provided with an interconnected main power unit and a backup power unit to realize dual-redundancy power supply.

5. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The control module is internally provided with an interconnected main control board and a backup control board to realize dual-redundancy control.

6. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The driving module is internally provided with an interconnected main driving board and a backup driving board to realize dual-redundancy driving.

7. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The interface module receives external flight control status, electromechanical status, inertial navigation, aircraft brake and turn control signals.

8. The aircraft braking and turning integrated control system based on signal sharing according to claim 1 is characterized in that: The interface module is connected to the brake command sensor set on the main engine wheel, and the brake command sensor sends the main engine wheel load and wheel speed signal to the interface module. The interface module is connected to a turning command sensor arranged on the front wheel, and the turning command sensor sends a front wheel load and turning angle signal to the interface module.

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