Aircraft dual-source redundant pressure supply brake valve and control method

Abstract

This invention relates to an aircraft dual-source redundant pressure supply brake valve and control method. The main pressure supply source is connected to the supply port of the main oil source switching valve; the return port of the main oil source switching valve is connected to the main pressure supply return port; the return port of the main oil source switching valve is connected to the main return port of the return oil switching valve; the backup return port of the return oil switching valve is connected to the return port of the backup oil source switching valve; the brake return port of the return oil switching valve is connected to the brake return port; the return port of the backup oil source switching valve is connected to the backup pressure supply return port; the backup pressure supply source is connected to the supply port of the backup oil source switching valve; the control port of the return oil switching valve is connected to the working port of the backup oil source switching valve; the working port of the backup oil source switching valve is connected to a state switching valve via two pipelines, one of which is connected to the control port of the state switching valve, and the other is connected to the backup pressure supply port of the state switching valve; the working port of the main oil source switching valve is connected to the main pressure supply port of the state switching valve; and the working port of the state switching valve is connected to the wheel brake.

Description

Technical Field

[0001] This invention belongs to the field of aircraft system design technology and relates to an aircraft dual-source redundant pressure supply brake valve and its control method. Background Technology

[0002] The wheel braking system is a crucial aircraft system, vital for safe takeoff and landing. It adjusts the aircraft's course and provides braking support under varying runway conditions. The pressure supplied by the brake source directly impacts the system's functionality. Currently, aircraft wheel braking systems typically use single hydraulic or accumulator brakes, resulting in insufficient brake redundancy or limited brake usage, increasing the burden on pilots. Existing brake source control valves can only achieve single-on / off control, lacking the ability to automatically switch between redundancy brake sources. Therefore, multiple independent brake source configurations are generally employed, with some using pneumatic brakes as a supplement, and others using accumulator brakes. These methods not only complicate the system and require more onboard space but also increase aircraft weight and cost, introduce system isolation issues, and further increase the pilot's braking workload. Summary of the Invention

[0003] The purpose of this invention:

[0004] This invention provides a dual-source redundant pressurized brake valve and control method for aircraft, enabling switching between dual-source hydraulic brake redundancy at the same pressure level, improving brake system reliability, enhancing handling performance, and improving aircraft takeoff and landing brake safety. This dual-source redundant pressurized brake valve features high integration, small size and weight, and reliable operation.

[0005] The technical solution of this invention:

[0006] A dual-source redundant pressure supply brake valve for aircraft includes a main oil source switching valve, a backup oil source switching valve, a return oil switching valve, and a state switching valve. The main oil source is connected to the supply port of the main oil source switching valve. The return oil port of the main oil source switching valve is connected to the main oil supply return oil. The return oil port of the main oil source switching valve is connected to the main return oil port of the return oil switching valve. The backup return oil port of the return oil switching valve is connected to the return oil port of the backup oil source switching valve. The brake return oil port of the return oil switching valve is connected to the brake return oil. The return oil port of the backup oil source switching valve is connected to the backup supply pressure return oil. The backup oil source is connected to the supply port of the backup oil source switching valve. The control port of the return oil switching valve is connected to the working port of the backup oil source switching valve. The working port of the backup oil source switching valve is connected to the state switching valve through two pipelines, one of which is connected to the control port of the state switching valve, and the other is connected to the backup supply pressure port of the state switching valve. The working port of the main oil source switching valve is connected to the main supply pressure port of the state switching valve. The working port of the state switching valve is connected to the wheel brake.

[0007] Furthermore, the return port of the main oil source switching valve is connected to the main pressure return port through the main check valve.

[0008] Furthermore, the return port of the backup oil source switching valve is connected to the backup pressure return port through a backup one-way valve.

[0009] Furthermore, a pressure sensor is installed on the working port of the state switching valve.

[0010] Furthermore, it also includes a housing, and the main oil source switching valve, backup oil source switching valve, return oil switching valve and state switching valve are disposed inside the housing.

[0011] Furthermore, the main one-way valve, the backup one-way valve, and the pressure sensor are all housed within the housing.

[0012] Furthermore, the main oil source switching valve and the backup oil source switching valve are electrically controlled valves, controlled by an external circuit.

[0013] The control method of the aircraft dual-source redundant pressure supply brake valve is as follows: when the wheel brake is not operated, there is no brake pressure output, the main and backup oil source switching valves are both in the de-energized state, the brake return oil communicates with the main pressure supply return oil pipeline through the return oil switching valve and the main one-way valve, and the brake return oil communicates with the backup pressure supply return oil pipeline through the return oil switching valve and the backup one-way valve, and the main and backup pressure supply sources are both disconnected.

[0014] When the system return oil pressure changes abnormally, the main one-way valve has a reverse blocking function to block the main pressure source from entering the system and prevent the system from overpressure causing abnormal brake pressure.

[0015] During ground operations and taxiing, when the aircraft operates the wheel brakes, under normal circumstances, the main fuel supply switching valve is powered on, and the high-pressure fuel from the main pressure source enters the state switching valve through the main fuel supply switching valve. The state switching valve then supplies pressure to the wheel brakes, and the brake return fuel enters the main pressure return fuel through the return fuel switching valve and the main one-way valve. When the main pressure source fails, the main fuel supply switching valve is de-energized, and the backup fuel supply switching valve is energized. The high-pressure fuel from the backup pressure source is split into two paths through the backup fuel supply switching valve. One path enters the state switching valve and supplies pressure to the wheel brakes, while the other path switches the return fuel switching valve, and the brake return fuel enters the backup pressure return fuel through the return fuel switching valve and the backup one-way valve.

[0016] The beneficial effects of this invention are:

[0017] This invention provides a novel multi-functional integrated brake valve for aircraft wheel braking systems, relating to the design of aircraft brake pressure supply and control, and is currently in use. This invention designs a dual-source redundant brake valve, increasing brake pressure backup, achieving high integration, reducing external connection pipelines involved in control, lowering aircraft weight, and improving the reliability of the aircraft wheel braking system.

[0018] The dual-source redundant pressure supply brake valve has the following functions: hydraulic brake source connection control, automatic switching, brake source pressure supply isolation, brake source return oil isolation, and self-status monitoring. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the dual-source redundant pressure supply brake valve for aircraft of the present invention;

[0020] Figure 2 This is a structural diagram of the aircraft dual-source redundant pressure supply brake valve of the present invention. Detailed Implementation

[0021] One embodiment of the present invention is:

[0022] The dual-source redundant pressure-supply brake valve proposed in this invention includes functions such as hydraulic brake source connection control, automatic switching, brake source pressure supply isolation, brake source oil return isolation, and self-status monitoring. The principle of the dual-source redundant pressure-supply brake valve is as follows: Figure 1 As shown, an oil source switching valve is used for pressure control, and a state switching valve, a return oil switching valve, a one-way valve, and a pressure sensor are integrated.

[0023] Specifically, the aircraft dual-source redundant pressure supply brake valve of the present invention includes a main oil source switching valve, a backup oil source switching valve, a return oil switching valve, a main one-way valve, a backup one-way valve, a state switching valve, and a pressure sensor.

[0024] The main pressure source is connected to the pressure port of the main oil source switching valve. The return port of the main oil source switching valve is connected to the main pressure return oil through the main check valve. The return port of the main oil source switching valve is connected to the main return port of the return oil switching valve. The backup return port of the return oil switching valve is connected to the return port of the backup oil source switching valve. The brake return port of the return oil switching valve is connected to the brake return oil. The return port of the backup oil source switching valve is connected to the backup pressure return oil through the backup check valve. The backup pressure source is connected to the pressure port of the backup oil source switching valve. The control port of the return oil switching valve is connected to the working port of the backup oil source switching valve. The working port of the backup oil source switching valve is connected to the state switching valve through two pipelines, one of which is connected to the control port of the state switching valve, and the other is connected to the backup pressure supply port of the state switching valve. The working port of the main oil source switching valve is connected to the main pressure supply port of the state switching valve. The working port of the state switching valve is connected to the wheel brake. A pressure sensor is installed on the working port of the state switching valve.

[0025] Among them, the main oil source switching valve and the backup oil source switching valve are electrically controlled valves, controlled by an external circuit.

[0026] The second embodiment of the present invention provides a control method for an aircraft dual-source redundant pressure supply brake valve. Specifically, when the wheel brakes are not operated, there is no brake pressure output, the oil source switching valves are all de-energized, the brake return oil is connected to the main pressure supply return oil pipeline, and the pressure supply sources are all disconnected. When the system return oil pressure undergoes an abnormal sudden change, the one-way valve (main) has a reverse blocking function to prevent system overpressure from causing abnormal brake pressure.

[0027] During aircraft ground handling and taxiing, the wheel brakes are operated. Under normal circumstances, the main oil supply switching valve is powered on, and high-pressure oil from the main pressure source enters the state transition valve through the main oil supply switching valve, supplying pressure to the wheel brakes. Brake return oil enters the main pressure return oil via the return oil switching valve and a one-way valve (main). When the main pressure source fails, the main oil supply switching valve is de-energized, and the backup oil supply switching valve is powered on. High-pressure oil from the backup pressure source is split into two paths through the backup oil supply switching valve. One path enters the state transition valve, supplying pressure to the wheel brakes, while the other path switches the return oil switching valve, allowing brake return oil to enter the backup pressure return oil via the return oil switching valve and a one-way valve (backup). To prevent abnormal brake pressure output caused by sudden changes in system return oil pressure, one-way valves are installed at both the main and backup pressure return oil points. The dual-source redundant pressure supply brake valve has a significant impact on aircraft takeoff and landing safety; therefore, pressure sensors are used to monitor the status of the dual-source redundant pressure supply brake valve.

[0028] Figure 2 This is an external structural diagram of a dual-source redundant pressure-supply brake valve for a certain aircraft model. This valve highly integrates two oil source switching valves, two one-way valves, one state transition valve, one pressure sensor, and one return oil switching valve, significantly reducing onboard installation space and eliminating external connecting pipelines and part of the housing, thus reducing aircraft weight. The pressure sensor is located at the outlet of the state transition valve, monitoring the operating status of the dual-source redundant pressure-supply brake valve in real time. When abnormal brake pressure is detected, the valve can automatically switch to ensure normal operation of the braking system. The hydraulic brake source connection control is achieved electronically through the oil source switching valve. This allows for both high-pressure oil connection during power supply and oil depressurization and system return oil capability during power failure, while also isolating the dual-source redundant pressure supply. It is applicable to different or the same hydraulic brake sources, and the independent control of the oil source switching valve (main / backup) for brake source pressure has a wide range of applications. The return oil switching valve is located on the brake return oil line and upstream of the check valve. It uses a mechanical method to automatically switch the oil source, ensuring accurate return oil and isolating the return oil from the main pressure source and the backup pressure source. The status switching valve is located downstream of the oil source switching valve. It uses a mechanical method to automatically switch, ensuring accurate pressure supply and isolating the pressure supply from the main pressure source and the backup pressure source.

Claims

1. A control method for an aircraft dual-source redundant pressure-supply brake valve, characterized in that, The aircraft dual-source redundant pressure supply brake valve includes a main oil source switching valve, a backup oil source switching valve, a return oil switching valve, and a state switching valve. The main pressure source is connected to the supply port of the main oil source switching valve. The return oil port of the main oil source switching valve is connected to the main supply pressure return oil. The return oil port of the main oil source switching valve is connected to the main return oil port of the return oil switching valve. The backup return oil port of the return oil switching valve is connected to the return oil port of the backup oil source switching valve. The brake return oil port of the return oil switching valve is connected to the brake return oil. The return oil port of the backup oil source switching valve is connected to the backup supply pressure return oil. The backup pressure source is connected to the supply port of the backup oil source switching valve. The control port of the return oil switching valve is connected to the working port of the backup oil source switching valve. The working port of the backup oil source switching valve is connected to the state switching valve through two pipelines, one of which is connected to the control port of the state switching valve, and the other is connected to the backup supply pressure port of the state switching valve. The working port of the main oil source switching valve is connected to the main supply pressure port of the state switching valve. The working port of the state switching valve is connected to the wheel brake. The control method for the dual-source redundant pressure supply brake valve of an aircraft is as follows: When the wheel brake is not operated, there is no brake pressure output. The main and backup oil source switching valves are both de-energized. The brake return oil communicates with the main pressure return oil pipeline through the return oil switching valve and the main check valve, and the brake return oil communicates with the backup pressure return oil pipeline through the return oil switching valve and the backup check valve. The main and backup pressure sources are both disconnected. When the system return oil pressure changes abnormally, the main one-way valve has a reverse blocking function to block the main pressure source from entering the system and prevent the system overpressure from causing abnormal brake pressure. During ground operations and taxiing, when the aircraft operates the wheel brakes, under normal circumstances, the main fuel supply switching valve is powered on, and the high-pressure fuel from the main pressure source enters the state switching valve through the main fuel supply switching valve. The state switching valve then supplies pressure to the wheel brakes, and the brake return fuel enters the main pressure return fuel through the return fuel switching valve and the main one-way valve. When the main pressure source fails, the main fuel supply switching valve is de-energized, and the backup fuel supply switching valve is energized. The high-pressure fuel from the backup pressure source is split into two paths through the backup fuel supply switching valve. One path enters the state switching valve and supplies pressure to the wheel brakes, while the other path switches the return fuel switching valve, and the brake return fuel enters the backup pressure return fuel through the return fuel switching valve and the backup one-way valve.

2. The control method for an aircraft dual-source redundant pressure-supply brake valve according to claim 1, characterized in that, The return port of the main oil source switching valve is connected to the main pressure return port through the main check valve.

3. The control method for an aircraft dual-source redundant pressure-supply brake valve according to claim 2, characterized in that, The return port of the backup oil source switching valve is connected to the backup pressure return port through a backup one-way valve.

4. The control method for an aircraft dual-source redundant pressure-supply brake valve according to claim 3, characterized in that, A pressure sensor is installed on the working port of the state switching valve.

5. The control method for an aircraft dual-source redundant pressure-supply brake valve according to claim 4, characterized in that, The aircraft dual-source redundant pressure supply brake valve also includes a housing, and the main oil source switching valve, backup oil source switching valve, return oil switching valve and status switching valve are disposed within the housing.

6. The control method for an aircraft dual-source redundant pressure-supply brake valve according to claim 5, characterized in that, The main one-way valve, backup one-way valve, and pressure sensor are all housed inside the housing.

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