CN117902039A - Cooling control architecture of aircraft brake device - Google Patents
Cooling control architecture of aircraft brake device Download PDFInfo
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- CN117902039A CN117902039A CN202311860561.4A CN202311860561A CN117902039A CN 117902039 A CN117902039 A CN 117902039A CN 202311860561 A CN202311860561 A CN 202311860561A CN 117902039 A CN117902039 A CN 117902039A
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- cooling
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- brake device
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- 238000001816 cooling Methods 0.000 title claims abstract description 51
- 238000012423 maintenance Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The application belongs to the field of cooling of aircraft brake devices, and relates to an aircraft brake device cooling control architecture which comprises a brake device, a cooling fan, a fan motor, a fan driver and an electromechanical system. The cooling fan is arranged at the tail end of the brake device and is arranged coaxially with the wheel, the fan motor is arranged in the wheel shaft and is mechanically connected with the cooling fan, the fan driver is arranged on the aircraft and is electrically connected with the fan motor, the electromechanical system is electrically connected with the fan driver, and the electromechanical system can provide high-voltage direct current or high-voltage alternating current for the fan driver. When the temperature at any position in the aircraft brake device is too high, a cooling instruction is sent to the fan driver through the electromechanical system, the fan driver controls the fan motor to work through the cooling instruction, the fan motor works to drive the cooling fan to rotate, wind energy is provided for the brake device to cool down, and the aircraft brake device is simple in structure and stable in control.
Description
Technical Field
The application belongs to the field of cooling of aircraft brake devices, and particularly relates to a cooling control architecture of an aircraft brake device.
Background
In the field of aviation, a safe landing temperature is set at the departure line of an aircraft to limit the aircraft from taking off at a safe temperature in consideration of the safety of use and the risk of fire. However, as civil aircraft weight increases and speed increases, the energy absorption of the brakes increases as the aircraft lands, the braking temperature increases, and as the airport scale expands, the taxiing distance increases, resulting in an increase in taxiing energy, which tends to result in a higher braking temperature, and easily exceeding the safe landing temperature, which in turn affects the normal dispatch of the aircraft.
How to cool the aircraft brake effectively is a problem to be solved.
Disclosure of Invention
The application aims to provide a cooling control framework of an aircraft brake device, which aims to solve the problem that the brake device of an aircraft is difficult to effectively cool in the prior art.
The technical scheme of the application is as follows: an aircraft brake cooling control architecture comprises a brake, a cooling fan, a fan motor, a fan driver and an electromechanical system; the cooling fan is arranged at the tail end of the brake device and is coaxially arranged with the wheel, the fan motor is arranged in the wheel shaft and is mechanically connected with the cooling fan, the fan driver is arranged on the aircraft and is electrically connected with the fan motor, the electromechanical system is electrically connected with the fan driver, and the electromechanical system can provide high-voltage direct current or high-voltage alternating current for the fan driver.
Preferably, the system further comprises a cabin fan starting switch and a ground fan closing switch, wherein the cabin fan starting switch is arranged in the cockpit, and the cabin fan starting switch can be started manually in a aircrew manner; the ground fan closing switch is arranged on the ground maintenance panel, and when the ground maintenance is carried out, ground staff can press the ground fan closing switch to close the cooling fan.
Preferably, a power supply system and an electromechanical integrated management system are arranged in the electromechanical system, and the electromechanical system can provide high-voltage direct current or high-voltage alternating current for the fan driver; the electromechanical integrated management system is internally provided with a set temperature, and can collect the temperature in the brake system and judge whether to start the cooling fan or not through the set temperature.
Preferably, the cooling control logic of the braking device of the electromechanical integrated management system is as follows:
When the aircraft is in an air state, the brake fan does not work;
under the stop state of the airplane, the ground service controls the fan to stop working through the ground fan closing switch.
Preferably, in the aircraft taxiing process, when the temperature of any brake device is more than or equal to the set temperature, the fan is started; in the aircraft taxiing process, the aircraft service operates the cabin fan start switch, and the fan cabin start switch is manually pressed to start the fan.
Preferably, a tire pressure sensor is arranged on a machine wheel of the braking device, and the tire pressure sensor is communicated with a machine wheel air cavity and can collect tire pressure information and transmit the tire pressure information to an electromechanical system.
The application relates to an aircraft brake cooling control architecture, which comprises a brake device, a cooling fan, a fan motor, a fan driver and an electromechanical system. The cooling fan is arranged at the tail end of the brake device and is arranged coaxially with the wheel, the fan motor is arranged in the wheel shaft and is mechanically connected with the cooling fan, the fan driver is arranged on the aircraft and is electrically connected with the fan motor, the electromechanical system is electrically connected with the fan driver, and the electromechanical system can provide high-voltage direct current or high-voltage alternating current for the fan driver. When the temperature at any position in the aircraft brake device is too high, a cooling instruction is sent to the fan driver through the electromechanical system, the fan driver controls the fan motor to work through the cooling instruction, the fan motor works to drive the cooling fan to rotate, wind energy is provided for the brake device to cool down, and the aircraft brake device is simple in structure and stable in control.
Drawings
In order to more clearly illustrate the technical solution provided by the present application, the following description will briefly refer to the accompanying drawings. It will be apparent that the figures described below are merely some embodiments of the application.
FIG. 1 is a schematic diagram of the overall structure of the present application.
1. A brake device; 2. a cooling fan; 3. a fan motor; 4. a fan driver; 5. an electromechanical system; 6. a cabin fan start switch; 7. the floor fan turns off the switch.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
An aircraft brake cooling control architecture, as shown in FIG. 1, includes a brake 1, a cooling fan 2, a fan motor 3, a fan drive 4, and an electromechanical system 5. The cooling fan 2 is mounted at the end of the brake device 1 and is arranged coaxially with the wheel, the fan motor 3 is mounted in the wheel shaft and the fan motor 3 is mechanically connected with the cooling fan 2, the fan driver 4 is arranged on the aircraft and the fan driver 4 is electrically connected with the fan motor 3, the electromechanical system 5 is electrically connected with the fan driver 4, and the electromechanical system 5 can provide high-voltage direct current or high-voltage alternating current to the fan driver 4.
When the temperature at any position in the aircraft brake device 1 is too high, a cooling instruction is sent to the fan driver 4 through the electromechanical system 5, the fan driver 4 controls the fan motor 3 to work through the cooling instruction, the fan motor 3 works to drive the cooling fan 2 to rotate, wind energy is provided for the brake device 1 to cool down, and the structure is simple and the control is stable.
Preferably, the cooling fan 2 is provided in plurality, the fan driver 4 supplies power to one or more fan motors 3 on the aircraft, and in order to avoid instantaneous spikes to the on-board power grid caused by the simultaneous operation of the plurality of fan motors 3, each fan motor 3 needs to be set to start in batches.
Preferably, the cabin fan starting switch 6 and the ground fan closing switch 7 are also included, the cabin fan starting switch 6 is arranged in the cockpit, and the cabin fan starting switch 6 can be started manually in the presence of aircrew; the floor fan closing switch 7 is provided on the floor maintenance panel, and the cooling fan 2 can be turned off by the ground crew pressing the floor fan closing switch 7 when performing floor maintenance.
Preferably, a power supply system and an electromechanical integrated management system are arranged in the electromechanical system 5, and the electromechanical system 5 can provide high-voltage direct current or high-voltage alternating current for the fan driver 4; the electromechanical integrated management system is internally provided with a set temperature, and can collect the temperature in the brake system and judge whether to start the cooling fan 2 or not through the set temperature.
Preferably, the cooling control logic of the braking device 1 of the electromechanical integrated management system is:
When the aircraft is in an air state, the brake fan does not work;
in the stop state of the airplane, the ground service controls the fan to stop working through the ground fan closing switch 7.
In the process of airplane sliding, when the temperature of any brake device 1 is more than or equal to the set temperature, the fan is started;
during the taxiing process of the aircraft, the cabin fan starting switch 6 is operated by the aircrew, and the fan is started by manually pressing the fan cabin starting switch.
Preferably, a tire pressure sensor is arranged on the machine wheel of the braking device 1, and the tire pressure sensor is communicated with the air cavity of the machine wheel, can collect tire pressure information and transmit the tire pressure information to the electromechanical system 5 for the electromechanical integrated management system to carry out logic judgment.
Finally, it should be noted that: in the drawings of the disclosed embodiments, only the structures related to the embodiments of the present disclosure are referred to, and other structures can refer to the common design, so that the same embodiment and different embodiments of the present disclosure can be combined with each other under the condition of no conflict;
Finally: the foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and principles of the invention are intended to be included within the scope of the invention.
Claims (6)
1. An aircraft brake cooling control architecture, characterized in that: comprises a braking device (1), a cooling fan (2), a fan motor (3), a fan driver (4) and an electromechanical system (5); the cooling fan (2) is arranged at the tail end of the brake device (1) and is coaxially arranged with the machine wheel, the fan motor (3) is arranged in the wheel shaft, the fan motor (3) is mechanically connected with the cooling fan (2), the fan driver (4) is arranged on the airplane, the fan driver (4) is electrically connected with the fan motor (3), the electromechanical system (5) is electrically connected with the fan driver (4), and the electromechanical system (5) can provide high-voltage direct current or high-voltage alternating current for the fan driver (4).
2. The aircraft brake cooling control architecture of claim 1, wherein: the novel cabin fan control system is characterized by further comprising a cabin fan starting switch (6) and a ground fan closing switch (7), wherein the cabin fan starting switch (6) is arranged in the cockpit, and the cabin fan starting switch (6) can be manually started in a duty; the ground fan closing switch (7) is arranged on the ground maintenance panel, and when the ground maintenance is carried out, the ground staff can press the ground fan closing switch (7) to close the cooling fan (2).
3. The aircraft brake cooling control architecture of claim 2, wherein: a power supply system and an electromechanical integrated management system are arranged in the electromechanical system (5), and the electromechanical system (5) can provide high-voltage direct current or high-voltage alternating current for the fan driver (4); the electromechanical integrated management system is internally provided with a set temperature, and can collect the temperature in the brake system and judge whether to start the cooling fan (2) or not through the set temperature.
4. An aircraft brake cooling control architecture as claimed in claim 3, wherein: the cooling control logic of the brake device (1) of the electromechanical integrated management system is as follows:
When the aircraft is in an air state, the brake fan does not work;
In the stop state of the airplane, the ground service controls the fan to stop working through a ground fan closing switch (7).
5. The aircraft brake cooling control architecture of claim 4, wherein:
in the process of airplane sliding, when the temperature of any brake device (1) is more than or equal to the set temperature, the fan is started;
In the aircraft taxiing process, the cabin fan starting switch (6) is operated by the aircrew, and the fan is started by manually pressing the fan cabin starting switch.
6. An aircraft brake cooling control architecture as claimed in claim 3, wherein: the tyre pressure sensor is arranged on the machine wheel of the braking device (1), is communicated with the air cavity of the machine wheel, and can collect tyre pressure information and transmit the tyre pressure information to the electromechanical system (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311860561.4A CN117902039A (en) | 2023-12-31 | 2023-12-31 | Cooling control architecture of aircraft brake device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311860561.4A CN117902039A (en) | 2023-12-31 | 2023-12-31 | Cooling control architecture of aircraft brake device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117902039A true CN117902039A (en) | 2024-04-19 |
Family
ID=90688199
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311860561.4A Pending CN117902039A (en) | 2023-12-31 | 2023-12-31 | Cooling control architecture of aircraft brake device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117902039A (en) |
-
2023
- 2023-12-31 CN CN202311860561.4A patent/CN117902039A/en active Pending
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