CN109305148B - Temperature-based aircraft brake air-cooling control system and design method thereof - Google Patents
Temperature-based aircraft brake air-cooling control system and design method thereof Download PDFInfo
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- CN109305148B CN109305148B CN201811245088.8A CN201811245088A CN109305148B CN 109305148 B CN109305148 B CN 109305148B CN 201811245088 A CN201811245088 A CN 201811245088A CN 109305148 B CN109305148 B CN 109305148B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- B60T5/00—Vehicle modifications to facilitate cooling of brakes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
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Abstract
An aircraft on-board brake air-cooling control system based on temperature and a design method thereof are provided, wherein a relay power supply is communicated with one end of a fan control circuit protection automatic switch; the other end of the fan control circuit protection automatic switch is communicated with the input end of the right brake wheel floor switch, the output end of the right brake wheel floor switch is communicated with the input end of the left brake wheel floor switch, and the output end of the left brake wheel floor switch is communicated with the input end of the brake fan switch. When the input end a of the brake fan switch is communicated with the disconnection end c, the brake fan switch is disconnected; when the input end a of the brake fan switch is communicated with the input end b of the working contact of the relay, the brake fan switch is communicated with the working contact of the relay connected with the power supply. When the temperature of the brake wheel reaches the condition of high temperature, the invention can timely and reliably cool the brake wheel after the aircraft lands, shortens the take-off and landing period of the aircraft from 60-90 min to 30min, shortens the take-off and landing time of the aircraft, and improves the take-off and landing frequency of the aircraft. Meanwhile, the energy is saved, and the labor intensity of ground staff is reduced.
Description
Technical Field
The invention relates to an aircraft airborne brake air cooling system, in particular to an aircraft airborne brake air cooling control system and a design method thereof.
Background
The modern aircraft has higher take-off speed, larger landing weight and higher braking speed, so that the aircraft has higher braking energy, the temperature of a braking wheel braking device is greatly increased, and forced cooling of the braking device is necessary to ensure the quick take-off of the aircraft. Modern aircraft brake wheel cooling devices become a necessary device for aircraft brake wheel and brake system design.
The second generation and third generation of active aircraft mostly adopt metal-based powder alloy brake materials, and in order to ensure the quick movement of the aircraft, a ground forced water cooling or air cooling method is adopted to ensure the quick movement of the aircraft. The C/C, C/Si composite brake material with the advantages of good friction characteristic, strong heat absorption capacity, small material density, long service life and the like overcomes the defects of a metal-based powder alloy brake material, can better meet the requirements of an airplane on a brake wheel and is widely used, but the C/C, C/Si composite brake material has poor oxidation resistance, so that the brake device cannot be cooled by water and can only be cooled by air.
The electric schematic diagram of the airborne brake air cooling system of the Su 27 aircraft is shown in fig. 1. The onboard braking air cooling system of the Su 27 aircraft consists of a fan power supply circuit automatic protection switch 1, a fan control circuit automatic protection switch 3, a left braking wheel cooling fan motor 4, a right braking wheel cooling fan motor 5, a left fan power-on contactor 6, a right fan power-on contactor 7, a landing gear lowering position end point switch 8, a braking wheel cooling change-over switch 9, a motor power supply 18 and a relay power supply 2; the brake wheel cooling fan control system adopts manual control. The brake wheel cooling conversion switch 9 arranged on the front cabin door of the left landing gear has two states of on/off, and the brake wheel cooling conversion switch is in the off state before each flight of the aircraft. When the aircraft engine works, namely, the aircraft runs on-off, slides and decelerates, the brake wheel cooling fan control system is powered by the motor power supply 18 and the relay power supply 2; when the aircraft is stopped on the parking apron, namely the aircraft engine stops working, the brake wheel cooling fan control system is powered by an airport power supply, and ground staff manually opens a brake wheel cooling conversion switch 9 of the front cabin door of the left landing gear according to the cooling requirement of the brake wheel after each landing of the aircraft, so that the motor of the airborne brake air cooling system rotates at a high speed to strongly cool and dissipate heat for a brake wheel braking device. The total working time of the brake wheel cooling motor is not longer than 25min, and the brake wheel cooling conversion switch 9 of the left landing gear front cabin door is manually disconnected after the temperature of the brake wheel braking device is reduced, so that the 'on-board brake air cooling system motor' is operated to stop rotating, and ground staff can manually operate the brake wheel cooling fan to rotate according to the cooling requirement of the brake wheel.
The control logic of the air cooling system for the airborne brake in the prior art realizes the rotation/stop of the air cooling system for the airborne brake by adopting a manual operation mode by ground staff after the aircraft finishes landing, so that the aim of rapidly cooling the wheel of the aircraft brake is fulfilled, but the air cooling system for the airborne brake has no automatic control function, and the working intensity of the ground staff is increased.
According to the method, a brake cooling fan is arranged on each brake wheel, so that the stop passing time can be shortened by cooling the brake at a high speed, which is mentioned in a Min's machine brake system development study published in Shanghai in Zhang Xiangjian of a brake system chamber of a hydraulic part of an aircraft design institute of Shanghai, 10 months in Shanghai, which is recorded in science and technology vision, by searching Chinese paper net; however, this paper does not describe the control logic of the brake cooling fan, and does not describe the brake cooling fan having an automatic control function.
Through searching, the invention with the publication number of CN106005379A discloses a cooling method and an air cooling device for an aircraft brake wheel. The invention creates a cooling method and an air cooling device of an aircraft brake wheel, wherein the cooling method and the air cooling device comprise a cooling disc and an air inlet connector, the cooling disc is communicated with the air inlet connector through a flexible ventilation pipe, and an air outlet nozzle matched with the aircraft brake wheel is arranged on the cooling disc; fixing a cooling disc on the side surface of the aircraft brake wheel, wherein an air outlet nozzle of the cooling disc corresponds to a vent hole of the aircraft brake wheel; the air inlet joint is communicated with a cold air source, cold air enters the cooling disc through the air inlet joint and the ventilation pipe, and then the cooling effect is implemented to the air vent of the brake wheel of the airplane through the air outlet nozzle.
However, the invention disclosed in the publication No. CN106005379A is that cooling air is led into the air vent of the aircraft brake wheel by adopting the cooling disc and the air inlet connector to perform cooling action, and the structural strength of the aircraft brake wheel is reduced by punching holes on the aircraft brake wheel, and meanwhile, the aircraft brake wheel is cooled by adopting an external air source, so that the labor intensity of workers is increased, and the cooling time of the aircraft brake wheel is delayed. The invention creates specific reasonable numerical values which do not explicitly indicate the temperature warning value setting and specific requirements for automatic starting and stopping of the air cooling system.
Disclosure of Invention
In order to overcome the defects that the structural strength of an aircraft brake wheel is reduced, the aircraft brake wheel is cooled by an external air source in the prior art, and the cooling time of the aircraft brake wheel is delayed, the invention provides a temperature-based aircraft brake air cooling control system and a design method thereof.
The invention comprises a main wheel temperature monitoring unit, a brake fan switch, a relay power supply and a power supply, wherein the brake wheel cooling fan motor, a left brake wheel floor switch, a right brake wheel floor switch and a motor contact are connected; the two automatic protection switches of the fan power supply circuit are respectively positioned in the airborne brake air-cooling control system of the left brake wheel and the airborne brake air-cooling control system of the right brake wheel. The fan control circuit automatic protection switch is provided with one; the relay power supply is communicated with one end of the fan control circuit automatic protection switch; the other end of the fan control circuit automatic protection switch is communicated with the input end of the right brake wheel floor switch, the output end of the right brake wheel floor switch is communicated with the input end of the left brake wheel floor switch, and the output end of the left brake wheel floor switch is communicated with the input end of the brake fan switch. When the input end a of the brake fan switch is communicated with the output end c of the brake fan switch, the brake fan switch is disconnected; when the input end a of the brake fan switch is communicated with the output end b of the brake fan switch, the brake fan switch is communicated with the working contact of the relay connected with the power supply.
The input point of the temperature signal of the main wheel temperature monitoring unit is communicated with the output point of the temperature signal of the temperature sensor, and the two brake wheels of the main wheel temperature monitoring unit are in temperature states T WD The signal output points are respectively communicated with the input ends of the control contacts of the two relays, and the working contact of the relay connecting load is communicated with the input end of the control contact of the alternating current contactor; the output end of the control contact of the alternating current contactor is communicated with the control contact of the cooling fan motor of the brake wheel, and the working contact of the cooling fan motor of the brake wheel is communicated with a motor power supply through a circuit protection automatic switch. The motor power supply is three-phase 115V,400Hz.
The brake air-cooling control system of the right wheel of the airplane is the same as that of the left wheel of the airplane. In the brake air-cooling control system of the right wheel of the airplane, a relay power supply is communicated with one end of an automatic protection switch of a fan control circuit in the brake air-cooling control system of the right wheel; the other end of the fan control circuit automatic protection switch is communicated with the input end of the right brake wheel floor switch, the output end of the right brake wheel floor switch is communicated with the input end of the left brake wheel floor switch, and the output end of the left brake wheel floor switch is communicated with the input end of the brake fan switch.
The control process of the temperature-based aircraft on-board brake air-cooling control system provided by the invention is as follows:
And determining a temperature threshold acquired by the temperature sensor. The determined temperature threshold is divided into a high signal threshold T WD1 Sum low signal threshold T WD2 。
According to the determined high signal threshold T WD1 Sum low signal threshold T WD2 Determining the temperature state T of the brake wheel by adopting a temperature state identification method with hysteresis comparison characteristics WD . Temperature state T of the brake wheel WD The method is divided into a high temperature state and a low temperature state.
The determined high signal threshold T WD1 Is 300 ℃, low signal threshold T WD2 The temperature of (2) was 90 ℃.
The high temperature state and the low temperature state are respectively:
after the aircraft brakes, before the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the temperature sensor is smaller than the threshold T WD1 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is smaller than the threshold T WD2 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, before the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the temperature sensor is greater than the threshold T WD1 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is greater than a threshold T WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state.
the air/ground state of the aircraft is determined jointly by the on-off of the left brake wheel landing switch and the right brake wheel landing switch.
When the air/ground state of the aircraft is determined jointly by the on-off of the left brake wheel landing switch and the right brake wheel landing switch:
when the aircraft is in the air, the brake wheel landing switch is disconnected; when the aircraft is on the ground, the brake wheel landing switch is turned on. The left brake wheel landing switch determines that the air/ground state of the aircraft is J LD1 The right brake wheel landing switch determines that the air/ground state of the aircraft is J LD2 The air/ground state of the plane is J LD ；
When the left brake wheel landing switch and the right brake wheel landing switch are both in the ground state, the air/ground state J of the aircraft LD Is in a ground state; when one of the left brake wheel landing switch and the right brake wheel landing switch is in an air state, the air/ground state J of the airplane LD Is in an air state.
according to the temperature state signal T of the brake wheel WD And aircraft air/ground status signal J LD And determining an automatic control logic of the on-board brake air cooling system.
After the aircraft is braked, before the cooling fan motor of the braking wheel starts to rotate, the braking fan switch of the aircraft is switched on, and the aircraft is in the ground and braking wheel temperature state T WD The relay is in a high-temperature state, the control contact of the relay is switched on, and the working contact of the relay is switched on; the left motor is connected with the contact, and the brake wheel cooling fan motor rotates at a high speed.
After the aircraft is braked, before the cooling fan motor of the braking wheel starts to rotate, the braking fan switch of the aircraft is switched on, and the aircraft is in the ground and braking wheel temperature state T WD The relay is in a low-temperature state, the control contact of the relay is disconnected, and the working contact of the relay is disconnected; the left motor is powered on and powered off, and the brake wheel cooling fan motor is prohibited from rotating.
After the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature t detected by the main wheel temperature monitoring unit is greater than a thresholdT WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state; the brake wheel cooling fan motor continues to rotate at a high speed.
After the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is smaller than the threshold T WD2 Temperature state T of brake wheel WD The output is 0, i.e. the low temperature state. The brake wheel cooling fan motor stops rotating.
When the aircraft is in the air, the relay is powered off, so that the contact of the left motor is powered off, and the brake wheel cooling fan motor is prohibited from rotating.
The temperature of a braking device of the braking wheel reaches the highest value within 10-15 min after the aircraft brakes, the temperature state of the braking wheel is high at the moment, and a cooling fan motor of the braking wheel arranged in a landing gear shaft rotates at a high speed to forcefully cool the braking wheel; when the temperature state of the brake wheel is changed into low temperature, the cooling fan motor of the brake wheel arranged in the landing gear shaft is forbidden to rotate, and the cooling work of the brake wheel is finished.
Thus, the control process of the air cooling system of the aircraft on-board brake is completed.
The determined automatic control logic of the on-board brake air cooling system is as follows:
temperature state T of brake wheel WD The output is 0, i.e. the low temperature state. Temperature state T of brake wheel WD The output is 1, namely, the high temperature state;
temperature state T of brake wheel WD Output is "0", aircraft air/ground status signal J LD When the vehicle is in the air, the vehicle-mounted brake control signal is in the forbidden operation.
Temperature state T of brake wheel WD Output is "0", aircraft air/ground status signal J LD When the vehicle is on the ground, the on-board brake control signal is on the disabled.
Temperature state T of brake wheel WD Output is "1", aircraft air/ground status signal J LD When the vehicle is in the air, the vehicle-mounted brake control signal is in the forbidden operation.
Temperature state T of brake wheel WD Output is 1, aircraft air/ground state signal J LD When the vehicle is on the ground, the vehicle-mounted brake control signal is on.
When the temperature state of the brake wheel is 0, representing the low temperature state of the brake wheel; when the temperature state of the brake wheel is 1, the high temperature state of the brake wheel is represented.
The control of the brake wheel cooling fan is automatic control of the two-wheel aircraft cooling fan, and after the aircraft lands, a brake wheel landing switch arranged on a left landing gear and a brake wheel landing switch arranged on a right landing gear are respectively contacted under the action of external force, so that an aircraft ground state signal is sent out.
The invention utilizes the left main landing gear brake wheel landing switch and the right main landing gear brake wheel landing switch to determine the air/ground state of the aircraft; the main wheel temperature monitoring unit determines the temperature state of a brake device of the brake wheel; and determining the automatic control logic of the on-board brake air cooling system through the air/ground state of the aircraft and the temperature state of the brake wheel brake device.
The positive pole of the relay power supply is communicated with one end of the automatic protection switch of the fan control circuit, the other end of the automatic protection switch of the fan control circuit is communicated with the input end of the ground switch power supply of the right brake wheel, the output end of the ground switch power supply of the right brake wheel is communicated with the input end of the ground switch power supply of the left brake wheel, the output end of the ground switch power supply of the left brake wheel is communicated with the input end of the brake fan switch,
when the input end a of the brake fan switch is communicated with the output end c of the brake fan switch, the brake fan switch is disconnected; when the input end a of the brake fan switch is communicated with the output end b of the brake fan switch, the brake fan switch is communicated with a working contact of a relay connected with a power supply; the input point of the temperature signal of the main wheel temperature monitoring unit is communicated with the output point of the temperature signal of the temperature sensor, and the temperature states T of the two brake wheels of the main wheel temperature monitoring unit WD The signal output points are respectively communicated with the input ends of the control contacts of the two relays, the working contacts of the two relay connecting loads are respectively communicated with the input ends of the control contacts of the alternating current contactor, and the output ends of the control contacts of the alternating current contactor are respectively communicated withAnd the control contact of the brake wheel cooling fan motor is communicated with the working contact of the brake wheel cooling fan motor, and the working contact of the brake wheel cooling fan motor is communicated with a motor power supply through a circuit protection automatic switch.
The aircraft brake fan switch controls the power supply of the airborne brake air cooling system. According to the invention, the ground switching signals of the brake wheels on the left landing gear and the ground switching signals of the brake wheels on the right landing gear are combined and calculated with the temperature state signals of the brake wheel brake devices detected by the main wheel temperature monitoring unit, so that the automatic control of the airborne brake air cooling system is realized, as the ground switching signals of the brake wheels on the left landing gear and the ground switching signals of the brake wheels on the right landing gear are all in the ground state when the aircraft starts to brake, the aircraft engine is switched into a slow-running state, the landing braking time of the aircraft is not more than 1 minute, the aircraft running speed is not more than 50km/h when the aircraft is automatically started to cool the brake wheels, but the temperature of a brake wheel hot bank can reach the highest value only about 10-15 minutes after the aircraft is landed, meanwhile, the high temperature signal and the low temperature signal are set, when the temperature output by the temperature sensor is more than the high temperature signal threshold, the relay control contact is on, the working contact of the relay is connected with the power supply and the working contact of the load are on, the control contact of the AC contactor is on, and the brake wheel cooling fan motor is automatically started when the brake wheels are automatically started; after cooling lasts for a certain time, when the temperature output by the temperature sensor is less than the temperature low signal threshold, the relay control contact is disconnected, the working contact of the relay power supply and the working contact of the load are disconnected, the control contact of the alternating current contactor is disconnected, the cooling fan motor of the brake wheel is forbidden to rotate, the airborne brake air cooling system is automatically closed, and cooling of the brake wheel is stopped.
Meanwhile, the invention adopts the relay to control the cooling fan motor of the brake wheel, if the temperature output by the temperature sensor is smaller than the temperature low signal threshold, the working contact of the relay connected with the power supply and the working contact of the relay connected with the load are automatically disconnected, the cooling fan motor of the brake wheel is forbidden to rotate, and the temperature of the brake wheel is stopped.
Because the temperature state of each brake wheel is not completely consistent, in order to enable each brake wheel to meet the cooling requirement, the aircraft airborne brake air cooling system adopts a method for independently controlling the cooling fan motors of two brake wheels, namely when any one brake wheel meets the cooling condition, the corresponding brake wheel cooling fan motor rotates to cool, and when any brake wheel meets the cooling completion condition, the corresponding brake wheel cooling fan motor stops rotating, and the corresponding brake wheel stops cooling.
According to the invention, the brake wheel landing switch signal on the left landing gear, the brake wheel landing switch signal on the right landing gear and the brake wheel brake device temperature state signal detected by the main wheel temperature monitoring unit are combined and operated, so that the automatic control of the airborne brake air cooling system is realized together, and the labor intensity of ground staff is reduced.
The temperature-based aircraft brake air cooling system can automatically cool the brake wheel after the aircraft lands, the temperature state of the brake wheel is determined by adopting the temperature state identification method with the hysteresis comparison characteristic, the absolute reliability of high and low temperature signals is ensured, and when the temperature of the brake wheel reaches the condition of high temperature, the brake wheel can be cooled timely and reliably after the aircraft lands, the take-off and landing period of the aircraft can be shortened from 60-90 min to 30min, so that the take-off and landing time of the aircraft is shortened, and the take-off and landing frequency of the aircraft is improved. Meanwhile, the energy is saved, and the labor intensity of ground staff is reduced.
Drawings
FIG. 1 is an electrical schematic diagram of a prior art brake wheel cooling fan control system;
FIG. 2 is a schematic diagram of an aircraft on-board brake air cooling system according to the present invention. In the figure:
1. the fan power supply circuit automatically protects the switch; 2. a relay power supply; 3. the fan control circuit automatically protects the switch; 4. left-way brake wheel cooling fan motor; 5. a right-way brake wheel cooling fan motor; 6. the left motor is connected with a contact; 7. the right motor is connected with a contact; 8. landing gear down position end point switch; 9. a brake wheel cooling change-over switch; 10. a left brake wheel floor switch; 11. a right brake wheel floor switch; 12. a brake fan switch; 13. a relay; 14. a main wheel temperature monitoring unit; 15. a temperature sensor; 16. a brake wheel cooling fan motor; 17. an alternating current contactor; 18. and a motor power supply.
Detailed Description
The embodiment is an aircraft airborne brake air-cooling control system based on temperature, which is used for controlling cooling of a left brake wheel and a right brake wheel of an aircraft.
The aircraft airborne brake air-cooling control system comprises a main wheel temperature monitoring unit 14, a brake fan switch 12, a relay power supply 2 and a power supply 18, and a left brake wheel landing switch 10; a right brake wheel floor switch 11; and the two fan control circuit automatic protection switches 3 are respectively positioned in the airborne brake air-cooling control system of the left brake wheel and the airborne brake air-cooling control system of the right brake wheel. The aircraft airborne brake air-cooling control system also comprises a fan control circuit automatic protection switch 1, two relays 13, two temperature sensors 15, two alternating current contactors and two brake wheel cooling fan motors 16 which are respectively positioned in the left brake wheel airborne brake air-cooling control system and the right brake wheel airborne brake air-cooling control system.
In this embodiment, a brake air cooling control system of a left wheel of an aircraft is described in detail as an example.
One end of the relay power supply 2 is communicated with the fan control circuit automatic protection switch 3; the other end of the fan control circuit automatic protection switch 3 is communicated with the input end of a right brake wheel landing switch 11, the output end of the right brake wheel landing switch 11 is communicated with the input end of a left brake wheel landing switch 10, and the output end of the left brake wheel landing switch 10 is communicated with the input end of a brake fan switch 12.
The brake fan switch 12 is a single pole double throw switch. When the input end a of the brake fan switch 12 is communicated with the output end c of the brake fan switch, the brake fan switch 12 is disconnected; when the input end a of the brake fan switch 12 is communicated with the output end b of the brake fan switch 12, the brake fan switch 12 is connected with the relay 13The working contact of the power supply is communicated; the input point of the temperature signal of the main wheel temperature monitoring unit 14 is communicated with the output point of the temperature signal of the temperature sensor 15, and the two brake wheel temperature states T of the main wheel temperature monitoring unit 14 WD The signal output points are respectively communicated with the input ends of control contacts of two relays 13, and the working contact of the relay 13 connected with a load is communicated with the input end of the control contact of an alternating current contactor 17; the control contact output end of the alternating current contactor 17 is communicated with the control contact of the brake wheel cooling fan motor 16, and the working contact of the brake wheel cooling fan motor 16 is communicated with a motor power supply 18 through the circuit protection automatic switch 1. The motor power supply 18 is three-phase 115v,400hz.
In this embodiment, the brake air-cooling control system of the right wheel of the aircraft is the same as the brake air-cooling control system of the left wheel of the aircraft. In the brake air-cooling control system of the right wheel of the airplane, a relay power supply 2 is communicated with one end of an automatic protection switch 3 of a fan control circuit in the brake air-cooling control system of the right wheel; the other end of the fan control circuit automatic protection switch 3 is communicated with the input end of a right brake wheel landing switch 11, the output end of the right brake wheel landing switch 11 is communicated with the input end of a left brake wheel landing switch 10, and the output end of the left brake wheel landing switch 10 is communicated with the input end of a brake fan switch 12.
In the embodiment, taking a two-wheel aircraft airborne brake air cooling system as an example, a control method of the aircraft airborne brake air cooling system is provided.
The specific process is as follows:
And determining a temperature threshold acquired by the temperature sensor. The determined temperature threshold is divided into a high signal threshold T WD1 Sum low signal threshold T WD2 In this embodiment, the high signal threshold T WD1 Is 300 ℃, low signal threshold T WD2 The temperature of (2) was 90 ℃.
According to the determined high signal threshold T WD1 Sum low signal threshold T WD2 A conventional temperature state identification method with hysteresis comparison characteristics is adopted to determine a brake machineTemperature state T of wheel WD . Temperature state T of the brake wheel WD The method is divided into a high temperature state and a low temperature state:
after the aircraft brakes, the temperature sensor 15 detects a temperature T less than a threshold T before the braking wheel cooling fan motor 16 begins to rotate WD1 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, after the braking wheel cooling fan motor 16 begins to rotate, the temperature sensor 15 detects that the temperature T is less than the threshold T WD2 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, the temperature sensor 15 detects a temperature T greater than a threshold T before the braking wheel cooling fan motor 16 begins to rotate WD1 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state;
after the aircraft is braked, the temperature sensor 15 measures a temperature T greater than a threshold T after the brake wheel cooling fan motor 16 begins to rotate WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state.
The air/ground state of the aircraft is determined jointly by the on-off of the left brake wheel landing switch 10 and the right brake wheel landing switch 11.
When the aircraft is in the air, the brake wheel landing switch is disconnected; when the aircraft is on the ground, the brake wheel landing switch is turned on. The left brake wheel landing switch 10 determines the air/ground condition of the aircraft as J LD1 The right brake wheel landing switch 11 determines the air/ground state of the aircraft as J LD2 The air/ground state of the plane is J LD The method comprises the steps of carrying out a first treatment on the surface of the When the left brake wheel landing switch 10 and the right brake wheel landing switch 11 are both in the ground state, the aircraft air/ground state J LD Is in a ground state; when only one of the left brake wheel landing switch 10 and the right brake wheel landing switch 11 is in an air state, the aircraft is in an air/ground state J LD Is in an air state. The air/ground state of the aircraft is specifically shown in table 1 for air/ground state control of the aircraftLogic table.
TABLE 1 aircraft air/ground State control logic
| JLD1 | JLD2 | JLD |
| Ground surface | Ground surface | Ground surface |
| Ground surface | In the air | In the air |
| In the air | Ground surface | In the air |
| In the air | In the air | In the air |
In this embodiment, the mechanical brake wheel-down switch QLK-3 is mounted at a position determined by the left landing gear and the right landing gear of the aircraft. The air/ground state of the aircraft was determined according to the control logic of table 1, and the performance parameters of the mechanical brake wheel-to-ground switch QLK-3 are shown in table 2:
table 2 QLK-3 mechanical brake wheel floor switch performance
The air/ground state identification of the aircraft is realized according to the control logic of the table 1, the aircraft is in the air, and the brake wheel landing switch is disconnected; the ground switch of the brake wheel is switched on when the aircraft is on the ground.
according to the temperature state signal T of the brake wheel WD And aircraft air/ground status signal J LD Determining the automatic control logic of the on-board brake air cooling system, and specifically, see table 3:
table 3 automatic control logic of on-board brake air cooling system
| TWD | JLD | Onboard brake control signal |
| 0 | In the air | Inhibit work |
| 0 | Ground surface | Inhibit |
| 1 | In the air | Inhibit |
| 1 | Ground surface | Work of |
Description: the 0 in the table represents the low temperature state of the brake wheel; "1" represents the high temperature state of the brake wheel.
After the aircraft is braked, before the brake wheel cooling fan motor 16 begins to rotate, the aircraft brake fan switch 12 is turned on, and the aircraft is in the ground and brake wheel temperature state T WD In a high temperature state, the relay 13 is controlled to be contacted, and the working contact of the relay 13 is contacted; the left motor contact 6 is on and the brake wheel cooling fan motor 16 rotates at high speed.
After the aircraft is braked, before the brake wheel cooling fan motor 16 begins to rotate, the aircraft brake fan switch 12 is turned on, and the aircraft is in the ground and brake wheel temperature state T WD In a low-temperature state, the relay 13 controls the contacts to be opened, and the working contacts of the relay 13 are opened; the left motor on contact 6 is de-energized and the brake wheel cooling fan motor 16 is inhibited from rotating.
After the aircraft is braked, and after the brake wheel cooling fan motor 16 begins to rotate, the main wheel temperature monitoring unit 14 detects a temperature T greater than a threshold T WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state; the brake wheel cooling fan motor 16 continues to rotate at high speed.
After the aircraft is braked, and after the brake wheel cooling fan motor 16 begins to rotate, the main wheel temperature monitoring unit 14 detects a temperature T less than a threshold T WD2 Temperature state T of brake wheel WD The output is 0, i.e. the low temperature state. The brake wheel cooling fan motor 16 stops rotating.
The aircraft is in the sky, and relay 13 outage makes left way motor switch-on contact 6 outage, prohibits brake wheel cooling fan motor 16 rotation.
The embodiment realizes the automatic control of the cooling fans of the two-wheeled aircraft. The brake wheel landing switch arranged on the left landing gear and the brake wheel landing switch QLK-3 on the right landing gear are contacted and connected under the action of external force after the aircraft lands, and an aircraft ground state signal is sent out. The temperature of the braking device of the braking wheel reaches the highest value after the aircraft brakes for 10-15 min, the temperature state of the braking wheel is high at the moment, and the cooling fan motor 16 of the braking wheel arranged in the landing gear shaft rotates at a high speed to forcefully cool the braking wheel; when the temperature state of the brake wheel becomes low, the brake wheel cooling fan motor 16 mounted in the landing gear shaft is prohibited from rotating, and the brake wheel cooling operation is ended.
Thus, the control process of the air cooling system of the aircraft on-board brake is completed.
Claims (7)
1. The temperature-based aircraft brake air-cooling control system is characterized by comprising a main wheel temperature monitoring unit, a brake fan switch, a relay power supply and a motor power supply, wherein a brake wheel cooling fan motor, a left brake wheel floor switch, a right brake wheel floor switch and a motor contact are connected; the two automatic protection switches of the fan power supply circuit are respectively positioned in the airborne brake air-cooling control system of the left brake wheel and the airborne brake air-cooling control system of the right brake wheel; the fan control circuit automatic protection switch is provided with one; one end of the relay power supply is communicated with one end of the fan control circuit protection automatic switch; the other end of the fan control circuit protection automatic switch is communicated with the input end of the right brake wheel floor switch, the output end of the right brake wheel floor switch is communicated with the input end of the left brake wheel floor switch, and the output end of the left brake wheel floor switch is communicated with the input end of the brake fan switch; when the input end a of the brake fan switch is communicated with the output end c of the brake fan switch, the brake fan switch is disconnected; when the input end a of the brake fan switch is communicated with the output end b of the brake fan switch, the brake fan switch is communicated with a working contact of a relay connected with a power supply;
the input point of the temperature signal of the main wheel temperature monitoring unit is communicated with the output point of the temperature signal of the temperature sensor, and the two brake wheels of the main wheel temperature monitoring unit are in temperature states T WD The signal output points are respectively communicated with the input ends of two relay control contacts, and the relay is connected with a loadThe working contact of the alternating current contactor is communicated with the control contact input end of the alternating current contactor; the output end of a control contact of the alternating current contactor is communicated with a control contact of a brake wheel cooling fan motor, and a working contact of the brake wheel cooling fan motor is communicated with a motor power supply through a circuit protection automatic switch; the motor power supply is three-phase 115V and 400Hz;
the brake air-cooling control system of the right wheel of the airplane is the same as that of the left wheel of the airplane; in the brake air-cooling control system of the right wheel of the airplane, a relay power supply is communicated with one end of a fan control circuit protection automatic switch in the brake air-cooling control system of the right wheel; the other end of the fan control circuit protection automatic switch is communicated with the input end of the right brake wheel floor switch, the output end of the right brake wheel floor switch is communicated with the input end of the left brake wheel floor switch, and the output end of the left brake wheel floor switch is communicated with the input end of the brake fan switch.
2. A control method of the temperature-based aircraft on-board brake air-cooling control system as claimed in claim 1, characterized by comprising the following specific steps:
step 1, determining the temperature state T of a brake wheel WD ：
Determining a temperature threshold acquired by a temperature sensor; the determined temperature threshold is divided into a high signal threshold T WD1 Sum low signal threshold T WD2 ；
According to the determined high signal threshold T WD1 Sum low signal threshold T WD2 Determining the temperature state T of the brake wheel by adopting a temperature state identification method with hysteresis comparison characteristics WD The method comprises the steps of carrying out a first treatment on the surface of the Temperature state T of the brake wheel WD The method is divided into a high temperature state and a low temperature state;
step 2, determining the air/ground state of the aircraft according to the ground switch state of the brake wheel:
the air/ground state of the aircraft is determined jointly by the on-off of the left brake wheel landing switch and the right brake wheel landing switch;
step 3, determining a control process of the airborne brake air cooling system:
according to the temperature state signal T of the brake wheel WD And aircraft air/ground status signal J LD Determining an automatic control logic of an on-board brake air cooling system;
after the aircraft is braked, before the cooling fan motor of the braking wheel starts to rotate, the braking fan switch of the aircraft is switched on, and the aircraft is in the ground and braking wheel temperature state T WD The relay is in a high-temperature state, the control contact of the relay is switched on, and the working contact of the relay is switched on; the left motor is connected with a contact, and the brake wheel cooling fan motor rotates at a high speed;
after the aircraft is braked, before the cooling fan motor of the braking wheel starts to rotate, the braking fan switch of the aircraft is switched on, and the aircraft is in the ground and braking wheel temperature state T WD The relay is in a low-temperature state, the control contact of the relay is disconnected, and the working contact of the relay is disconnected; the left motor is powered on and powered off, and the cooling fan motor of the brake wheel is forbidden to rotate;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is greater than a threshold T WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state; the brake wheel cooling fan motor continues to rotate at a high speed;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is smaller than the threshold T WD2 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state; stopping the rotation of the cooling fan motor of the brake wheel;
when the aircraft is in the air, the relay is powered off, so that the contact of the left motor is powered off, and the rotation of the brake wheel cooling fan motor is forbidden;
the temperature of a braking device of the braking wheel reaches the highest value within 10-15 min after the aircraft brakes, the temperature state of the braking wheel is high at the moment, and a cooling fan motor of the braking wheel arranged in a landing gear shaft rotates at a high speed to forcefully cool the braking wheel; when the temperature state of the brake wheel is changed into low temperature, a brake wheel cooling fan motor arranged in the landing gear shaft is forbidden to rotate, and the brake wheel cooling work is finished;
thus, the control process of the air cooling system of the aircraft on-board brake is completed.
3. The method of claim 2, wherein the high signal threshold T determined in step 1 is WD1 Is 300 ℃, low signal threshold T WD2 The temperature of (2) was 90 ℃.
4. The control method of an aircraft on-board brake air-cooling control system based on temperature according to claim 2, wherein the temperature state T of the brake wheel WD The method is divided into a high temperature state and a low temperature state:
after the aircraft brakes, before the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the temperature sensor is smaller than the threshold T WD1 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is smaller than the threshold T WD2 Temperature state T of brake wheel WD The output is 0, namely, the low temperature state;
after the aircraft brakes, before the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the temperature sensor is greater than the threshold T WD1 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state;
after the aircraft brakes, after the cooling fan motor of the braking wheel begins to rotate, the temperature T detected by the main wheel temperature monitoring unit is greater than a threshold T WD2 Temperature state T of brake wheel WD The output is 1, namely, the high temperature state.
5. The control method of an aircraft on-board brake air-cooling control system based on temperature according to claim 2, wherein when the air/ground state of the aircraft is determined by the on-off of the left brake wheel landing switch and the right brake wheel landing switch together:
when the aircraft is in the air, the brake wheel landing switch is disconnected; when the aircraft is on the ground, the brake wheel fallsThe ground switch is turned on; the left brake wheel landing switch determines that the air/ground state of the aircraft is J LD1 The right brake wheel landing switch determines that the air/ground state of the aircraft is J LD2 The air/ground state of the plane is J LD ；
When the left brake wheel landing switch and the right brake wheel landing switch are both in the ground state, the air/ground state J of the aircraft LD Is in a ground state; when one of the left brake wheel landing switch and the right brake wheel landing switch is in an air state, the air/ground state J of the airplane LD Is in an air state.
6. The method for controlling an aircraft on-board brake and air-cooling control system based on temperature as set forth in claim 2, wherein the automatic control logic of the on-board brake and air-cooling system determined in step 3 is:
temperature state T of brake wheel WD The output is 0, namely, the low temperature state; stopping the rotation of the cooling fan motor of the brake wheel; temperature state T of brake wheel WD The output is 1, namely, the high temperature state;
temperature state T of brake wheel WD Output is "0", aircraft air/ground status signal J LD When the vehicle-mounted brake control signal is in the air, the vehicle-mounted brake control signal is in the forbidden operation;
temperature state T of brake wheel WD Output is "0", aircraft air/ground status signal J LD When the vehicle-mounted brake control signal is 'ground', the vehicle-mounted brake control signal is 'forbidden operation';
temperature state T of brake wheel WD Output is "1", aircraft air/ground status signal J LD When the vehicle-mounted brake control signal is in the air, the vehicle-mounted brake control signal is in the forbidden operation;
temperature state T of brake wheel WD Output is 1, aircraft air/ground state signal J LD When the ground is "ground", the on-board brake control signal is "work";
when the temperature state of the brake wheel is 0, representing the low temperature state of the brake wheel; when the temperature state of the brake wheel is 1, the high temperature state of the brake wheel is represented.
7. The control method of the temperature-based aircraft on-board brake air-cooling control system according to claim 2, wherein in the step 3, the control of the brake wheel cooling fan is automatic control of a two-wheel aircraft cooling fan, and when the aircraft lands, a brake wheel landing switch respectively mounted on a left landing gear and a brake wheel landing switch mounted on a right landing gear are contacted under the action of external force, and an aircraft ground state signal is sent.
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| CN201811245088.8A CN109305148B (en) | 2018-10-24 | 2018-10-24 | Temperature-based aircraft brake air-cooling control system and design method thereof |
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| CN109305148B true CN109305148B (en) | 2023-06-20 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110597320A (en) * | 2019-10-08 | 2019-12-20 | 西安航空制动科技有限公司 | Temperature controller with automatic cooling function and control method thereof |
| CN110562443B (en) * | 2019-10-08 | 2022-10-14 | 西安航空制动科技有限公司 | Cooling controller and control method for airplane brake wheel |
| GB2601790A (en) | 2020-12-10 | 2022-06-15 | Airbus Operations Ltd | Aircraft brake temperature control system |
| CN112937516B (en) * | 2021-03-04 | 2023-09-12 | 中国商用飞机有限责任公司 | Aircraft brake fan control method and aircraft brake fan control system |
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| GB936086A (en) * | 1960-04-28 | 1963-09-04 | Gordon Winston Yarber | Improvements in and relating to control systems for aircraft wheel brakes |
| US5687573A (en) * | 1996-06-06 | 1997-11-18 | Shih; Ping-Ho | Thermal control device for cooling or heating parked vehicles |
| DE202018101460U1 (en) * | 2018-03-15 | 2018-09-17 | Conductix-Wampfler Gmbh | Cleaning device for a conductor rail and conductor rail system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7596434B2 (en) * | 2005-04-22 | 2009-09-29 | Safe Flight Instrument Corporation | Aircraft brake temperature monitoring system and method |
| GB2550364A (en) * | 2016-05-16 | 2017-11-22 | Airbus Operations Ltd | Aircraft brake temperature measurement |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB936086A (en) * | 1960-04-28 | 1963-09-04 | Gordon Winston Yarber | Improvements in and relating to control systems for aircraft wheel brakes |
| US5687573A (en) * | 1996-06-06 | 1997-11-18 | Shih; Ping-Ho | Thermal control device for cooling or heating parked vehicles |
| DE202018101460U1 (en) * | 2018-03-15 | 2018-09-17 | Conductix-Wampfler Gmbh | Cleaning device for a conductor rail and conductor rail system |
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