Aircraft brake cooling device and brake cooling method

Abstract

The invention belongs to the technical field of airplane wheel design, and particularly relates to an airplane brake cooling device and a brake cooling method. The brake cooling device comprises a pressure tank (5), an electromagnetic valve (6), an air leakage connector (7) and a control box (9), the air leakage connector (7) is fixed in a wheel shaft (4) of an aircraft landing gear, a cavity is formed in the air leakage connector (7), and a plurality of through holes are distributed along the circumference of a disc structure so as to lead to a brake heat reservoir (2); the pressure tank (5) is fixed at a side channel of the air leakage joint (7); the electromagnetic valve (6) is fixed on the air leakage connector (7) through a channel on the other side surface of the air leakage connector (7), and a valve core of the electromagnetic valve (6) can block the opening of the pressure tank (5); and the control box (9) is electrically connected with the electromagnetic valve (6) and the temperature sensor (8) and controls the electromagnetic valve (6) to be opened or closed according to the temperature fed back by the temperature sensor (8). The temperature control device is accurate in temperature control, low in economic cost and good in adaptability.

Description

Technical Field

[0001] The present application belongs to the technical field of wheel design, and in particular relates to an aircraft brake cooling device and a brake cooling method. Background Art

[0002] Take the brake temperature monitoring system used in aircraft as an example. Its main function is to monitor the brake temperature and feed it back to the pilot. After receiving the information, the pilot turns on the brake cooling fan to reduce the brake temperature. The biggest advantage of this type of brake temperature monitoring system is that it can monitor the brake temperature in real time and then take the time to cool down the brake cooling fan according to the brake temperature. However, its main disadvantage is that the system covers the collaborative work of multiple disciplines such as structural hardware, software, and electrical, with low reliability and poor maintainability, and high economic cost. Summary of the invention

[0003] In order to solve the above problems, the present application provides an aircraft brake cooling device and a brake cooling method, so that when the brake temperature exceeds the design value, the air relief valve opens the cooling medium pressure tank under the control of the control box to release the cooling medium, thereby achieving the effect of forced cooling of the brake. When the brake temperature is lower than the design value, the air relief valve closes the cooling medium pressure tank under the control of the control box to stop forced cooling of the brake.

[0004] The first aspect of the present application provides an aircraft brake cooling device, which mainly includes:

[0005] The air release joint is a disc structure, fixed inside the wheel axle of the aircraft landing gear, with a cavity inside the air release joint, and a plurality of through holes connected to the cavity are distributed along the circumference of the disc structure, and an annular groove connected to the air release joint is provided on the inner annular surface of the wheel axle, and the annular groove has a plurality of channels leading to the brake heat storage along the circumferential direction;

[0006] A pressure tank having a cooling medium therein, wherein an opening of the pressure tank is fixed at a side channel of the air release joint, wherein the side channel is connected to a cavity of the air release joint;

[0007] The solenoid valve is fixed on the air-release joint through the other side channel of the air-release joint, and the valve core of the solenoid valve can block the opening of the pressure tank;

[0008] The control box is electrically connected to the solenoid valve and the temperature sensor. The temperature sensor is fixed on the brake housing and is used to monitor the temperature of the brake disc. When the temperature reaches a set value, the solenoid valve is controlled to open the valve core.

[0009] Preferably, an annular groove is provided on the outer annular surface of the disc of the air release joint, and the annular groove is butted with the groove on the inner annular surface of the wheel shaft to form an annular cavity.

[0010] Preferably, the air release joint is connected to the inner annular surface of the wheel axle via threads.

[0011] Preferably, the annular groove on the inner annular surface of the wheel shaft is provided with three channels along the circumferential direction.

[0012] Preferably, the three channels are evenly distributed along the circumference of the annular groove.

[0013] Preferably, the pressure tank opening is connected to the side channel of the air release joint by threading.

[0014] Preferably, the cooling medium in the pressure tank includes dry ice.

[0015] Preferably, the cooling medium in the pressure tank comprises liquid nitrogen.

[0016] Preferably, the solenoid valve is connected to the other side channel of the air release joint through threads.

[0017] A second aspect of the present application provides an aircraft brake cooling method, using the aircraft brake cooling device as described above, the method comprising:

[0018] The brake disc temperature is collected through the temperature sensor;

[0019] When the brake disc temperature exceeds the set value, the solenoid valve is opened, and when the brake disc temperature is lower than the set value, the solenoid valve is closed.

[0020] The present application can effectively reduce the brake temperature and avoid the hazards caused by excessively high brake temperature, such as tire deflation and tire blowout, and can also effectively extend the ground taxiing distance of the aircraft and shorten the continuous take-off time. The present application has precise temperature control, low economic cost and good adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is an axial view of a test piece of a preferred embodiment of the aircraft brake cooling device of the present application.

[0022] Figure 2 This application Figure 1 A schematic diagram of the structure of the vent joint of the illustrated embodiment.

[0023] Among them, 1-wheel, 2-brake heat storage, 3-brake housing, 4-axle, 5-pressure tank, 6-solenoid valve, 7-air release connector, 8-temperature sensor, 9-control box, 10-channel. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the implementation of this application will be described in more detail in combination with the drawings in the implementation of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described implementation is a part of the implementation of this application, not all of the implementations. The implementation described below with reference to the drawings is exemplary and is intended to be used to explain this application, and cannot be understood as a limitation on this application. Based on the implementation in this application, all other implementations obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The implementation of this application is described in detail below in combination with the drawings.

[0025] The first aspect of the present application provides an aircraft brake cooling device, such as Figure 1-Figure 2 As shown, it mainly includes:

[0026] The air release joint 7 is a disc structure, fixed inside the wheel axle 4 of the aircraft landing gear, the air release joint 7 has a cavity inside, and a plurality of through holes connected to the cavity are distributed along the circumference of the disc structure, and an annular groove connected to the air release joint 7 is provided on the inner annular surface of the wheel axle 4, and the annular groove has a plurality of channels 10 leading to the brake heat storage 2 along the circumferential direction;

[0027] A pressure tank 5, which contains a cooling medium, wherein the opening of the pressure tank 5 is fixed at a side channel of the air relief joint 7, and the side channel is connected to the cavity of the air relief joint 7;

[0028] The solenoid valve 6 is fixed on the air-release joint 7 through the other side channel of the air-release joint 7, and the valve core of the solenoid valve 6 can block the opening of the pressure tank 5;

[0029] The control box 9 is electrically connected to the solenoid valve 6 and the temperature sensor 8. The temperature sensor 8 is fixed on the brake housing 3 and is used to monitor the temperature of the brake disc. When the temperature reaches a set value, the solenoid valve 6 is controlled to open the valve core.

[0030] After the wheel 1 and the brake device are installed on the axle 4 of the aircraft landing gear, the pressure tank 5 is sealed by the valve core of the solenoid valve 6. When the solenoid valve 6 is closed, the valve core extends close to the pressure tank 5 and the opening is sealed by the conical surface seal. The control box 9 is connected to the solenoid valve 6 by a cable, so that the control box 9 can supply power to the solenoid valve 6 and control the opening and closing of the solenoid valve 6.

[0031] The control box 9 is connected to the temperature sensor 8 via a cable, so that the collected brake temperature data is fed back to the control box 9 .

[0032] Assume that the brake temperature limit temperature is designed to be T. When the brake temperature is higher than T, it needs to be cooled down, and when it is lower than T, it stops cooling down. When the aircraft brakes, the friction of the brake heat reservoir generates a large amount of heat energy, and the instantaneous temperature can reach several hundred degrees Celsius. The temperature sensor 8 on the brake housing 3 collects the brake temperature and transmits the temperature data to the landing gear control box 9. The control box 9 converts the collected temperature data from analog to digital and compares it with the designed limit temperature T. When the collected brake temperature is greater than T, the control box 9 transmits an opening instruction to the solenoid valve 6, the solenoid valve opens, the valve core of the solenoid valve 6 retreats, the mouth of the pressure tank 5 opens, and the cooling medium in the pressure tank 5 is instantly released under the action of the internal pressure. The cooling medium reaches the brake heat reservoir 2 through the channels 10 distributed on the brake housing 3, the wheel axle 4 and the air release joint 7, which can immediately reduce the brake temperature. When the temperature drops to less than the limit temperature T, the control box 9 transmits a closing instruction to the solenoid valve 6, the solenoid valve closes, the valve core of the solenoid valve 6 moves forward, the cone surface of the mouth of the pressure tank 5 is sealed, and the cooling medium in the pressure tank 5 stops releasing, and stops reducing the brake temperature.

[0033] In some optional embodiments, an annular groove is provided on the outer annular surface of the disc of the air release joint 7, and the annular groove is connected with the groove of the inner annular surface of the wheel shaft 4 to form an annular cavity.

[0034] like Figure 2 As shown, in the present application, the annular groove of the air vent joint 7 is connected with the groove of the inner annular surface of the wheel axle 4 to form an annular cavity, and the cooling gas can fill the entire annular cavity and then flow to the brake heat storage 2 through the channel 10.

[0035] In some optional embodiments, the air release joint 7 is connected to the inner annular surface of the wheel axle 4 via threads.

[0036] In some optional embodiments, the annular groove on the inner annular surface of the wheel shaft 4 is provided with three channels 10 along the circumferential direction.

[0037] In some optional embodiments, the three channels 10 are evenly distributed along the circumference of the annular groove.

[0038] In some optional embodiments, the opening of the pressure tank 5 is connected to the side channel of the air release joint 7 by threading.

[0039] In some optional embodiments, the cooling medium in the pressure tank 5 includes dry ice.

[0040] In some optional embodiments, the cooling medium in the pressure tank 5 includes liquid nitrogen.

[0041] In some optional embodiments, the solenoid valve 6 is connected to the other side channel of the air relief joint 7 by means of threads.

[0042] A second aspect of the present application provides an aircraft brake cooling method, using the aircraft brake cooling device as described above, the method comprising:

[0043] The brake disc temperature is collected by the temperature sensor 8;

[0044] When the brake disc temperature exceeds the set value, the solenoid valve 6 is opened, and when the brake disc temperature is lower than the set value, the solenoid valve 6 is closed.

[0045] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An aircraft brake cooling device, characterized in that: include: The air release joint (7) is a disc structure, fixed inside the wheel axle (4) of the aircraft landing gear, the air release joint (7) has a cavity inside, and a plurality of through holes connected to the cavity are distributed along the circumference of the disc structure, and an annular groove connected to the air release joint (7) is arranged on the inner annular surface of the wheel axle (4), and the annular groove has a plurality of channels (10) leading to the brake heat storage (2) along the circumferential direction; A pressure tank (5) having a cooling medium therein, wherein the opening of the pressure tank (5) is fixed at a side channel of the air relief joint (7), and the side channel is connected to the cavity of the air relief joint (7); The solenoid valve (6) is fixed to the air release joint (7) through the other side channel of the air release joint (7), and the valve core of the solenoid valve (6) can block the opening of the pressure tank (5); The control box (9) is electrically connected to the electromagnetic valve (6) and the temperature sensor (8). The temperature sensor (8) is fixed on the brake housing (3) and is used to monitor the temperature of the brake disc and control the electromagnetic valve (6) to open the valve core when the temperature reaches a set value.

2. The aircraft brake cooling device according to claim 1, characterized in that: An annular groove is provided on the outer annular surface of the disc of the air release joint (7), and the annular groove is butted against the groove on the inner annular surface of the wheel shaft (4) to form an annular cavity.

3. The aircraft brake cooling device according to claim 1, characterized in that: The air release joint (7) is connected to the inner annular surface of the wheel shaft (4) via threads.

4. The aircraft brake cooling device according to claim 1, characterized in that: The annular groove on the inner annular surface of the wheel shaft (4) is provided with three channels (10) along the circumferential direction.

5. The aircraft brake cooling device according to claim 4, characterized in that: The three channels (10) are evenly distributed along the circumference of the annular groove.

6. The aircraft brake cooling device according to claim 1, characterized in that: The opening of the pressure tank (5) is connected to the side channel of the air release joint (7) through threads.

7. The aircraft brake cooling device according to claim 1, characterized in that: The cooling medium in the pressure tank (5) includes dry ice.

8. The aircraft brake cooling device according to claim 1, characterized in that: The cooling medium in the pressure tank (5) includes liquid nitrogen.

9. The aircraft brake cooling device according to claim 1, characterized in that: The solenoid valve (6) is connected to the other side channel of the air release joint (7) through threads.

10. A method for cooling aircraft brakes, characterized in that: Using the aircraft brake cooling device according to any one of claims 1 to 9, the method comprises: Collecting the brake disc temperature through a temperature sensor (8); When the temperature of the brake disc exceeds the set value, the electromagnetic valve (6) is opened, and when the temperature of the brake disc is lower than the set value, the electromagnetic valve (6) is closed.

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