An aircraft brake cooling device and a brake cooling method

Abstract

The application belongs to the technical field of 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), a gas leakage joint (7) and a control box (9). The gas leakage joint (7) is fixed in the wheel shaft (4) of the airplane landing gear. The gas leakage joint (7) has a cavity inside and a plurality of through holes distributed along the circumference of the disc structure to open to the brake heat sink (2). The pressure tank (5) is fixed at the side channel of the gas leakage joint (7). The electromagnetic valve (6) is fixed on the gas leakage joint (7) through the other side channel of the gas leakage joint (7). The valve core of the electromagnetic valve (6) can block the opening of the pressure tank (5). The control box (9) is electrically connected with the electromagnetic valve (6) and a temperature sensor (8). The electromagnetic valve (6) is controlled to open or close according to the temperature feedback by the temperature sensor (8). The application has the advantages of accurate temperature control, low economic cost and good adaptability.

Description

Technical Field

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

[0002] For example, the brake temperature monitoring system used on aircraft monitors brake temperature and provides feedback to the pilot, who then activates the brake cooling fan to reduce the temperature. The greatest advantage of this type of brake temperature monitoring system is its ability to monitor brake temperature in real time and adjust the timing of the brake cooling fan based on the temperature. However, its main disadvantage is that the system involves the coordinated work of multiple disciplines, including structural hardware, software, and electrical systems. This results in low reliability and maintenance, as well as high economic costs. 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 release 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 release 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 bleed connector is a disc structure fixed inside the wheel axle of the aircraft landing gear. The bleed connector has a cavity inside and multiple through holes distributed along the circumference of the disc structure that communicate with the cavity. The inner annular surface of the wheel axle is provided with an annular groove that docks with the bleed connector. The annular groove has multiple channels along the circumference leading to the brake heat reservoir.

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

[0007] The solenoid valve is fixed to the air bleed joint through the other side channel of the air bleed 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 the 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 docked 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 includes liquid nitrogen.

[0016] Preferably, the solenoid valve is connected to the other side channel of the air bleed joint through a thread.

[0017] A second aspect of the present application provides an aircraft brake cooling method using the aircraft brake cooling device 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] This application can effectively reduce the brake temperature and avoid the hazards caused by excessive brake temperature, such as tire deflation and blowout. At the same time, it can effectively extend the aircraft's ground taxiing distance and shorten the continuous take-off time. This application has precise temperature control, low economic cost and good adaptability. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This 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 Schematic diagram of the structure of the vent joint of the embodiment shown.

[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 solutions and advantages of the implementation of this application clearer, the technical solutions in the implementation of this application will be described in more detail below in conjunction with the drawings in the implementation of this application. In the drawings, the same or similar numbers 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 should not 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 conjunction 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 vent connector 7 is a disc structure fixed inside the wheel axle 4 of the aircraft landing gear. The vent connector 7 has a cavity inside and a plurality of through holes distributed along the circumference of the disc structure and connected to the cavity. The inner annular surface of the wheel axle 4 is provided with an annular groove that docks with the vent connector 7. The annular groove has a plurality of channels 10 along the circumference leading to the brake heat reservoir 2.

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

[0028] The solenoid valve 6 is fixed to the air release joint 7 through the other side channel of the air release joint 7. 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] In this application, 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 sealing of the conical surface. 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 the brake temperature limit is set to T. Cooling is required when the brake temperature exceeds T, and cooling ceases when it falls below T. When the aircraft brakes, friction in the brake heat reservoir generates a significant amount of heat energy, with the instantaneous temperature reaching several hundred degrees Celsius. Temperature sensor 8 on brake housing 3 detects the brake temperature and transmits the data to landing gear control box 9, which converts the acquired temperature data from analog to digital and compares it with the designed limit temperature T. When the acquired brake temperature exceeds T, control box 9 transmits an open command to solenoid valve 6, causing the valve core of solenoid valve 6 to retract, opening the outlet of pressure tank 5. Under the action of internal pressure, the coolant in pressure tank 5 is instantly released. The coolant flows through channels 10 distributed through brake housing 3, axle 4, and bleed connector 7 to the brake heat reservoir 2, immediately reducing the brake temperature. When the temperature drops below the limit temperature T, control box 9 transmits a close command to solenoid valve 6, causing the valve core of solenoid valve 6 to advance, sealing the conical surface at the outlet of pressure tank 5. The coolant in pressure tank 5 ceases to be released, thus stopping the reduction of 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 docked with the groove on the inner annular surface of the wheel shaft 4 to form an annular cavity.

[0034] like Figure 2 As shown, in this application, the annular groove of the air vent joint 7 is connected with the groove of the inner annular surface of the wheel shaft 4 to form an annular cavity. 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 shaft 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 through threads.

[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 release joint 7 through threads.

[0042] A second aspect of the present application provides an aircraft brake cooling method using the aircraft brake cooling device 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 description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection 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. The inner annular surface of the wheel axle (4) is provided with an annular groove docking with the air release joint (7). The annular groove has a plurality of channels (10) leading to the brake heat storage (2) along the circumference. A pressure tank (5) having a cooling medium therein, wherein the opening of the pressure tank (5) is fixed to a side channel of the air relief joint (7), wherein 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, wherein: 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 a thread.

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

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

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

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 via a temperature sensor (8); When the temperature of the brake disc exceeds a 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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