An integrated control system for aircraft braking and turning based on signal sharing

Abstract

This invention belongs to the field of aircraft braking and turning control technology, and relates to an integrated control system for aircraft braking and turning based on signal sharing. The system includes a control computer, a turning actuator, and a braking actuator. The control computer includes a control module, a drive module, and an interface module. 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 both the braking actuator and the turning actuator. The braking actuator drives and controls the main aircraft wheel to brake, and the turning actuator drives and controls the nose wheel to deflect. This invention achieves coordinated maneuvering of ground heading control during aircraft taxiing, ensuring reliable braking and agile turning.

Description

Technical Field

[0001] This invention belongs to the field of aircraft braking and turning control technology, and relates to the design of an integrated control system for aircraft braking and turning based on signal sharing. It relates to the integrated design of the aircraft's braking system and turning system, and specifically to an integrated control system for aircraft braking and turning based on signal sharing. Background Technology

[0002] Braking and turning are two core technologies in aircraft ground control. Differential braking and turning functions have a certain degree of functional overlap in aircraft heading control, providing redundancy between each other and playing a significant role in correcting aircraft heading and improving ground safety. Currently, most aircraft braking and turning systems are controlled independently, primarily using fly-by-wire systems. The braking system is controlled by the pilot operating pedals in the cockpit, transmitting control commands via electrical signals. The control box processes these signals and outputs signals to control the brake valves, controlling the braking pressure. Differential braking controls braking by outputting different braking pressures to the left and right sides. Similarly, the turning system is controlled by the pilot operating pedals in the cockpit, transmitting control commands via electrical signals. The control box processes these signals and outputs signals to control the actuators to deflect the nose wheel, completing the turn. Because the braking and turning systems are controlled independently, and the control accessories are independent of each other, numerous cross-wires are sent to both systems, consuming significant wiring and installation space, increasing aircraft weight, and hindering coordinated heading control. Summary of the Invention

[0003] The purpose of this invention:

[0004] To achieve coordinated control of braking and turning during aircraft heading maneuvers, reduce the number of crossover leads in aircraft signal information transmission, realize the sharing of computer software and hardware resources, and simultaneously meet the requirements of aircraft weight reduction and safe use, this invention proposes an integrated control system for aircraft braking and turning based on signal sharing. This system enables coordinated maneuvering of ground heading maneuvers during aircraft taxiing, ensuring reliable braking and flexible turning of the aircraft.

[0005] The technical solution of this invention:

[0006] An integrated control system for aircraft braking and turning based on signal sharing includes a control computer, a turning actuator, and a braking actuator. The control computer includes a control module, a drive module, and an interface module. 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 both the braking actuator and the turning actuator. The braking actuator drives and controls the main aircraft wheel to brake, and the turning actuator drives and controls the nose wheel to deflect.

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

[0008] Furthermore, the interface module is internally configured with an interconnected main acquisition unit and a backup acquisition unit to achieve dual-redundancy signal acquisition.

[0009] Furthermore, the power module is internally equipped with interconnected main power supply units and backup power supply units to achieve dual redundancy power supply.

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

[0011] Furthermore, the drive module internally includes an interconnected main drive board and a backup drive board to achieve dual-redundancy drive.

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

[0013] Furthermore, the interface module connects to a brake command sensor mounted on the main wheel, and the brake command sensor sends the wheel load and wheel speed signals of the main wheel to the interface module.

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

[0015] The beneficial effects of this invention are:

[0016] This invention proposes an integrated control system for aircraft braking and turning based on signal sharing. This system enables integrated control of aircraft braking and turning by sharing and distributing signals related to flight control status, electromechanical status, inertial navigation, wheel load, and wheel speed. The flight control and electromechanical status signals communicate with the control computer via a bus, achieving integrated control of braking and turning. This effectively ensures the aircraft's maneuverability and coordination in heading control, reducing the pilot's workload. This integrated braking and turning control system has been successfully applied to a certain type of aircraft, achieving significant social and economic benefits. Attached Figure Description

[0017] Figure 1 This is a system schematic diagram of the present invention. Detailed Implementation

[0018] Based on the design and usage requirements of a certain type of aircraft, this invention addresses the fact that during taxiing, the aircraft's braking and turning functions are essentially used simultaneously. Particularly during turning, differential braking and turning are employed concurrently to achieve rapid heading control. This invention utilizes an integrated braking and turning control system that can acquire aircraft heading control data in real time, enabling coordinated control of braking and turning. Furthermore, both the braking and turning systems utilize aircraft signal information such as flight control status, electromechanical status, inertial navigation, wheel load, and wheel speed. The integrated braking and turning control system achieves computer module and signal sharing, avoiding waste of control system software and hardware resources, reducing aircraft heading control-related accessories, minimizing aircraft wiring, and reducing aircraft weight.

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

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

[0021] 1. The system adopts an integrated braking and turning control system, which realizes signal information sharing and distribution within the computer, and enables computer hardware modules and signal sharing. This avoids waste of control system software and hardware resources, reduces aircraft heading control accessories, reduces aircraft wiring, and reduces aircraft weight.

[0022] 2. A single dual-redundant control computer is used to complete the integrated control of braking and turning. It receives braking and turning control commands from the aircraft, and combines them with input or acquired signals such as flight control status, electromechanical status, inertial navigation, wheel load, and wheel speed. It performs comprehensive processing on the relevant signals and outputs integrated control signals for braking and turning based on the current state of the aircraft. It links the aircraft heading control with the aircraft attitude. After receiving the aircraft status signals, the control computer outputs different differential braking pressures and nose wheel turning deflection signals to maximize the aircraft's maneuverability coordination performance in heading control.

[0023] Specifically, such as Figure 1 As shown, this control system mainly uses a dual-redundant computer to achieve integrated control of braking and turning. The control computer consists of a power supply module, a control module, a drive module, and an interface module. External signals mainly include flight control status, electromechanical status, inertial navigation, wheel load, and wheel speed signals. Among them, the flight control status and electromechanical status signals communicate with the control computer via a 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 both the braking and turning actuators. The braking actuator drives and controls the main aircraft wheel to brake, and the turning actuator drives and controls the nose wheel to deflect. The power supply module is connected to the control module, drive module, and interface module.

[0024] The power supply module supplies power to the control module, drive module, and interface module. The control module is used to integrate signals and output control signals. The drive module is used to receive control signals and drive the braking and turning actuators. The interface module is used to collect and distribute control signals, aircraft status signals, and feedback signals.

[0025] When the aircraft is taxiing, the brake control signal is input through brake command sensors installed under each pedal of the pilots at the front and rear, which sense the pilots' braking force and output an electrical signal proportional to the pedal force to the control computer; the turn control signal is input to the control computer through cockpit switch signals and bus communication to receive turn control command signals issued by the electromechanical management computer and the flight control management computer.

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

Claims

1. An integrated control system for aircraft braking and turning based on signal sharing, characterized in that, The system includes a control computer, a turning actuator, and a braking actuator. The control computer comprises a control module, a drive module, and an interface module. 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 both the braking and turning actuators. The braking actuator drives the main aircraft wheel to brake, and the turning actuator drives the nose wheel to deflect. The control computer also includes a power module that supplies power to the control module, drive module, and interface module. The interface module internally houses interconnected main and backup acquisition units to achieve dual-redundancy signal acquisition. The power module internally houses interconnected main and backup acquisition units. The system includes an interconnected main power supply unit and a backup power supply unit to achieve dual-redundant power supply; the control module internally includes interconnected main control boards and backup control boards to achieve dual-redundant control; the drive module internally includes interconnected main drive boards and backup drive boards to achieve dual-redundant drive; the interface module receives external flight control status, electromechanical status, inertial navigation, aircraft braking, and turn control signals; the interface module is connected to a brake command sensor mounted on the main engine wheel, which sends the main engine wheel load and wheel speed signals to the interface module; the interface module is also connected to a turn command sensor mounted on the nose wheel, which sends the nose wheel load and turn angle signals to the interface module. When the aircraft is taxiing, the brake control signal is input through brake command sensors installed under each pedal of the pilots at the front and rear, which sense the pilots' braking force and output an electrical signal proportional to the pedal force to the control computer; the turn control signal is input to the control computer through cockpit switch signals and bus communication to receive turn control command signals issued by the electromechanical management computer and the flight control management computer. The control computer, based on the magnitude of the aforementioned instructions and combined with flight control status, electromechanical status, inertial navigation, wheel load, and wheel speed signals, makes a comprehensive judgment and controls the output signals to the braking and turning drive modules. Ultimately, the actuators control the braking pressure and turning output to ensure that the aircraft's heading control matches the aircraft's status, thus completing the aircraft's braking and turning control.

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