Aircraft double-source redundancy pressure supply brake valve and control method

Abstract

The invention relates to an airplane double-source redundancy pressure supply brake valve and a control method, a main pressure supply source is connected with a pressure supply port of a main oil source switching valve, an oil return port of the main oil source switching valve is communicated with main pressure supply return oil, and an oil return port of the main oil source switching valve is communicated with a main oil return port of an oil return switching valve; a backup oil return opening of the oil return conversion valve is communicated with an oil return opening of the backup oil source switching valve, a brake oil return opening of the oil return conversion valve is communicated with brake return oil, an oil return opening of the backup oil source switching valve is communicated with backup pressure supply return oil, and the backup pressure supply source is connected with a pressure supply opening of the backup oil source switching valve. A control port of the oil return change-over valve is communicated with a working port of the backup oil source change-over valve, the working port of the backup oil source change-over valve is communicated with the state change-over valve through two pipelines, one pipeline is communicated with a control port of the state change-over valve, and the other pipeline is communicated with a backup pressure supply port of the state change-over valve. A working port of the main oil source switching valve is communicated with a main pressure supply port of the state switching valve, and a working port of the state switching valve is communicated with the airplane wheel brake.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft system design, and relates to an aircraft dual-source redundant pressure supply brake valve and a control method. Background Art

[0002] The wheel brake system is an important system of the aircraft. It is extremely important for the safe takeoff and landing of the aircraft. It brakes to adjust the aircraft's heading and brake the aircraft in different runway conditions. The brake source supply pressure directly affects the realization of the wheel brake system function. At present, the brake source supply pressure of the aircraft wheel brake system is generally a single hydraulic source brake or an accumulator brake. The brake margin is insufficient or the number of brake uses is limited, which increases the burden of brake operation. The existing brake source control valve can only achieve single on-off control and cannot complete the automatic switching function of the redundant brake source. Therefore, an independent configuration of multiple brake sources is generally adopted. Some use air source brakes as a supplement, and some use accumulator source brakes as a supplement. These methods not only make the system complex and the installation space on the aircraft large, but also increase the weight and cost of the aircraft, bring about system isolation problems, and increase the burden of pilot braking operation. Summary of the invention

[0003] Purpose of the present invention:

[0004] The present invention provides an aircraft dual-source redundant pressure supply brake valve and a control method, which are used to realize the switching of dual-source hydraulic brake redundancy with the same pressure level, improve the reliability of the brake system, improve the control performance, and enhance the safety of aircraft take-off and landing brake use. The dual-source redundant pressure supply brake valve has high integration, small size and weight, and reliable operation.

[0005] The technical solution of the present invention:

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

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

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

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

[0010] Furthermore, it also includes a shell, and the main oil source switching valve, backup oil source switching valve, return oil switching valve and state switching valve are arranged in the shell.

[0011] Furthermore, the main one-way valve, the backup one-way valve and the pressure sensor are all arranged in the shell.

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

[0013] The control method of the dual-source redundant pressure supply brake valve of the 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 in a power-off state, the brake return oil is communicated with the main pressure supply return oil pipeline through the return oil conversion valve and the main one-way valve, and the brake return oil is communicated with the backup pressure supply return oil pipeline through the return oil conversion 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 suddenly changes abnormally, the main one-way valve has a reverse blocking function to block the main supply pressure source from entering the system to prevent the system overpressure from causing abnormal brake pressure;

[0015] When the aircraft is on the ground and during taxiing, the wheel brakes are operated. Under normal circumstances, the main oil source switching valve is powered on, and the high-pressure oil from the main supply pressure source enters the state conversion valve through the main oil source switching valve, and the state conversion valve supplies pressure to the wheel brakes. The brake return oil enters the main supply pressure return oil through the return oil conversion valve and the main one-way valve; when the main supply pressure source fails, the main oil source switching valve is controlled to cut off the power, and the backup oil source switching valve is powered on. The backup pressure source high-pressure oil is divided into two paths through the backup oil source switching valve, one path enters the state conversion valve, and the state conversion valve supplies pressure to the wheel brakes, and the other path switches the return oil conversion valve, and the brake return oil enters the backup supply pressure return oil through the return oil conversion valve and the backup one-way valve.

[0016] Beneficial effects of the present invention:

[0017] The present invention provides a novel multifunctional integrated brake valve in an aircraft wheel brake system, which involves the aircraft brake source pressure supply and control design, and is put into use. The present invention designs a dual-source redundant brake valve, increases the brake pressure supply redundancy backup, has high integration, reduces the external connection pipelines involved in the control, reduces the aircraft weight, and improves the reliability of the aircraft wheel brake system.

[0018] The functions of the dual-source redundant pressure supply brake valve include hydraulic brake source connection control function, automatic switching function, brake source pressure supply isolation function, brake source oil return isolation function and self-status monitoring function. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0020] Figure 2 The present invention is a structural diagram of the appearance of an aircraft dual-source redundant pressure supply brake valve. DETAILED DESCRIPTION

[0021] An embodiment of the present invention is:

[0022] The dual-source redundant pressure supply brake valve proposed in the present invention includes the hydraulic brake source connection control function, automatic switching function, brake source pressure supply isolation function, brake source oil return isolation function and self-state monitoring function. Figure 1 As shown, an oil source switching valve is used to control the supply pressure, and a state conversion valve, an oil return conversion 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, an oil return switching valve, a main one-way valve, a backup one-way valve, a state switching valve and a pressure sensor;

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

[0025] Among them, the main oil source switching valve and the backup oil source switching valve are electrical control valves, which are controlled by external circuits.

[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 brake is not operated, there is no brake pressure output, the oil source switching valve is in a power-off state, the brake return oil is communicated with the main pressure supply return oil pipeline, and the pressure supply source is disconnected. When the system return oil pressure changes abnormally, the one-way valve (main) has a reverse blocking function to prevent the system overpressure from causing abnormal brake pressure.

[0027] During the ground and taxiing process of the aircraft, the wheel brake is operated. Under normal circumstances, the oil source switching valve (main) is powered on, and the high-pressure oil of the main supply pressure source enters the state conversion valve through the oil source switching valve (main), and the state conversion valve supplies pressure to the wheel brake. The brake return oil enters the main supply pressure return oil through the return oil conversion valve through the one-way valve (main). When the main supply pressure source fails, the oil source switching valve (main) is controlled to be powered off, and the oil source switching valve (backup) is powered. The backup supply pressure source high-pressure oil is divided into two paths through the oil source switching valve (backup). One path enters the state conversion valve, and the state conversion valve supplies pressure to the wheel brake. The other path switches the return oil conversion valve, and the brake return oil enters the backup supply pressure return oil through the return oil conversion valve through the one-way valve (backup). In order to avoid abnormal brake pressure output caused by sudden changes in the system return oil pressure, one-way valves are set at the main supply pressure return oil and the backup supply pressure return oil. The dual-source redundant supply pressure brake valve has a great impact on the safety of aircraft takeoff and landing. A pressure sensor is used to monitor the status of the dual-source redundant supply pressure brake valve.

[0028] Figure 2 This is the external structure diagram of a dual-source redundant pressure supply brake valve of a certain aircraft model. The valve is highly integrated with 2 oil source switching valves, 2 one-way valves, 1 state conversion valve, 1 pressure sensor, and 1 oil return conversion valve, which greatly reduces the installation space on the aircraft, and at the same time eliminates the external connection pipeline and part of the shell, reducing the weight of the aircraft. The pressure sensor is set at the outlet of the state conversion valve to monitor the working status of the dual-source redundant pressure supply brake valve in real time. When the brake pressure is found to be abnormal, the valve can be automatically controlled to switch to ensure the normal use of the brake system. The hydraulic brake source connection control can be completed by the oil source switching valve in an electronically controlled manner, which can not only realize the connection of high-pressure oil when power is supplied, but also realize the oil pressure relief and system oil return capacity when power is off, and complete the isolation of the dual-source redundant pressure supply; at the same time, it is applicable to different or the same hydraulic brake sources, and the use of oil source switching valve (main / standby) to independently control the brake source pressure supply pressure has a wide range of applications. The oil return conversion valve is set on the brake oil return line and upstream of the one-way valve. It is automatically switched by the oil source in a mechanical way to ensure the accuracy of the oil return and the isolation of the oil return from the main pressure supply source and the backup pressure supply source. The state conversion valve is set downstream of the oil source conversion valve and is automatically switched by a mechanical way to ensure the accuracy of the pressure supply and the isolation of the pressure supply from the main pressure supply source and the backup pressure supply source.

Claims

1. An aircraft dual-source redundant pressure supply brake valve, characterized in that: It includes a main oil source switching valve, a backup oil source switching valve, an oil return conversion valve and a state conversion valve, the main supply pressure source is connected to the pressure supply port of the main oil source switching valve, the oil return port of the main oil source switching valve is connected to the main supply pressure return oil, the oil return port of the main oil source switching valve is connected to the main oil return port of the return oil conversion valve, the backup oil return port of the return oil conversion valve is connected to the oil return port of the backup oil source switching valve, the brake oil return port of the return oil conversion valve is connected to the brake return oil, the oil return port of the backup oil source switching valve is connected to the backup supply pressure return oil, the backup supply pressure source is connected to the pressure supply port of the backup oil source switching valve, the control port of the return oil conversion 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 conversion valve through two pipelines, one of which is connected to the control port of the state conversion valve, and the other is connected to the backup supply pressure port of the state conversion valve, the working port of the main oil source switching valve is connected to the main supply pressure port of the state conversion valve, and the working port of the state conversion valve is connected to the wheel brake.

2. The aircraft dual-source redundant pressure supply brake valve according to claim 1, characterized in that: The return oil port of the main oil source switching valve is connected to the main supply pressure return oil through the main one-way valve.

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

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

5. The aircraft dual-source redundant pressure supply brake valve according to claim 4, characterized in that: It also includes a shell, and the main oil source switching valve, backup oil source switching valve, return oil switching valve and state switching valve are arranged in the shell.

6. The aircraft dual-source redundant pressure supply brake valve according to claim 5, characterized in that: The main one-way valve, the backup one-way valve and the pressure sensor are all arranged in the shell.

7. The aircraft dual-source redundant pressure supply brake valve according to claim 1, characterized in that: The main oil source switching valve and the backup oil source switching valve are electrical control valves, which are controlled by external circuits.

8. The control method of the aircraft dual-source redundant pressure supply brake valve according to any one of claims 1 to 7, characterized in that: 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 power-off state, the brake return oil is communicated with the main pressure return oil pipeline through the return oil conversion valve and the main one-way valve, and the brake return oil is communicated with the backup pressure return oil pipeline through the return oil conversion valve and the backup one-way valve, and the main and backup pressure sources are disconnected; When the system return oil pressure suddenly changes abnormally, the main one-way valve has a reverse blocking function to block the main supply pressure source from entering the system to prevent the system overpressure from causing abnormal brake pressure; When the aircraft is on the ground and during taxiing, the wheel brakes are operated. Under normal circumstances, the main oil source switching valve is powered on, and the high-pressure oil from the main supply pressure source enters the state conversion valve through the main oil source switching valve, and the state conversion valve supplies pressure to the wheel brakes. The brake return oil enters the main supply pressure return oil through the return oil conversion valve and the main one-way valve; when the main supply pressure source fails, the main oil source switching valve is controlled to cut off the power, and the backup oil source switching valve is powered on. The backup pressure source high-pressure oil is divided into two paths through the backup oil source switching valve, one path enters the state conversion valve, and the state conversion valve supplies pressure to the wheel brakes, and the other path switches the return oil conversion valve, and the brake return oil enters the backup supply pressure return oil through the return oil conversion valve and the backup one-way valve.

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