CN209196016U - Six train main airplane wheel brake cooling systems - Google Patents
Six train main airplane wheel brake cooling systems Download PDFInfo
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- CN209196016U CN209196016U CN201821813094.4U CN201821813094U CN209196016U CN 209196016 U CN209196016 U CN 209196016U CN 201821813094 U CN201821813094 U CN 201821813094U CN 209196016 U CN209196016 U CN 209196016U
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Abstract
A kind of six train main airplane wheel brake cooling systems, including six brake cooling components and a temperature monitor and control box.Temperature sensor in each brake cooling component is inserted into brake shell respectively in each temperature sensor fixing hole, and the signal input part of each temperature sensor together cut-in temperature is monitored to the temperature socket of control box, each power input for braking cooling motor is connected to the motor socket of temperature detecting unit together.The output bus of temperature monitor and control box is connected to aircraft cockpit instrument board；With aircraft power supply as the power supply of temperature monitor and control box.The both ends of cooling switch are connect with temperature monitor and control box input terminal and electromechanical source respectively.The utility model can cool down in advance during aircraft taxi, and improve aircraft goes out dynamic frequency, reduce the aging speed of brake gear and its spare part, improve the whole service life of brake gear, improve economic index.
Description
Technical field
The present invention relates to aircraft brake field of cooling, specifically a kind of six trains main airplane wheel brake cooling system
System.
Background technique
When aircraft executes various tasks, there is the demand for waiting the long range such as scheduling, transition, sliding for a long time.Continuous
Due to that frequently brake gear temperature can be made excessively high using brake in taxiing procedures, aircraft is influenced more than the limit temperature that takes off and is gone out again
It is dynamic.Wheel cooling method mainly has the mode of natural cooling, air-conditioned coach blowing and nitrogen cylinder at present.The natural cooling time is too unrestrained
It is long, it is unable to satisfy attack time requirement again；Air-conditioned coach blowing or nitrogen cylinder cooling can only use after a shutdown, and operate non-
Often inconvenient, aspect of blowing efficiency is low, cooling time is longer, to cooling effect without monitoring, only relies on ground crew's manual measurement, drops
The low maintainability of aircraft.
A kind of aircraft brake cooling system and method are proposed in the innovation and creation of Publication No. CN105752053A.The hair
Bright create cools down to brake gear using compressed gas, different from applying working condition of the present invention.The compressed gas cylinder that such method uses
It is suitble to aircraft utilization small-sized, that wheel quantity is few, temperature fall time length, low efficiency are not able to satisfy more trains, more pillar undercarriages
The aircraft of structure, which cools down, to be required, and needs timing supplement nitrogen, and maintenance cost is high.
Summary of the invention
In order to overcome cooling low efficiency existing in the prior art, it is not able to satisfy more trains, more pillar landing gear structures
Aircraft cooling requires, and the deficiency that maintenance cost is high, and the invention proposes a kind of six train main airplane wheel brake cooling systems.
Brake cooling system of the present invention includes six brake cooling components and a temperature monitor and control box.It is each described
Brake cooling component respectively includes temperature sensor, fan and the cooling motor that brakes.The test lead of each temperature sensor point
Cha Ru not be in brake shell in each temperature sensor fixing hole, and the signal input part of each temperature sensor is passed through into data line one
And access the temperature socket of the temperature monitor and control box, by the power input of each cooling motor that brakes by cable together with
The motor socket of the temperature detecting unit is connected to.The output bus and aircraft cockpit instrument board of the temperature monitor and control box
Connection；With aircraft power supply as the power supply of the temperature monitor and control box；Undercarriage " aerial/ground " status signal passes through
Data line is connected to " aerial/ground " state signal input terminal of temperature monitor and control box；Aircraft cockpit " cooling switch " letter
It number is connected to by the signal input part of " the cooling switch " of data line and temperature monitor and control box.
Input terminal on temperature monitor and control box is connect with a terminals of cooling switch；The cooling switch another
Terminals are connect with aircraft power supply.It is used to control the power supply to the cooling motor of 6 tunnels brake by relay.
The mounting disc of each temperature sensor is fixed on the outer surface of cylinder block.
Temperature sensor fixing hole in the brake shell is located on the outer end face of the brake shell, and each temperature passes
The centerline parallel of sensor mounting hole is in the center line of the brake shell.
The cooling motor of the brake is placed in main landing gear wheel shaft by fixed wheel nut；The main gear wheels
Inner surface is the flank with the fixed wheel nut outer surfaces cooperation at shaft end mouthful；It brakes on cooling electric machine casing circumference
In the convex key insertion convex key keyway for being located at fixed wheel nut inner surface, to limit the radial rotating for the cooling motor that brakes；
The fixation wheel nut and the cooling motor that brakes are connected.
External peripheral surface at the cooling electric machine casing outer end port of the brake has the annular stopper of radially protruding, works as brake
After cooling motor is packed into main landing gear wheel shaft, it is bonded the inner face of the annular stopper and the outer end face of fixed wheel nut,
To limit the axial jump for the cooling motor that brakes.
The leaf dish of the fan is fixedly mounted on the output shaft for the cooling motor that brakes.The signal output end of temperature sensor
It is connected to by data line with a signal input part of temperature monitor and control box.The power inlet of the cooling motor of brake passes through electricity
Cable is connected to the power output of the temperature monitor and control box.
The inner cavity of the temperature monitor and control box is divided into light current chamber and forceful electric power chamber, and Temperature Treatment module is enclosed in this
Light current is intracavitary, and it is intracavitary that the cooling motor control module that brakes is enclosed in forceful electric power.6 road forceful electric power circuits are furnished with the forceful electric power is intracavitary, respectively
It is simultaneously the cooling motor power supply of 6 tunnels brake.6 signal input parts are placed in the light current chamber, receive each temperature sensing respectively
The output signal of device.
The outer surface of wheel fixture nut one end is circle segments, and the outer surface of the circle segments is and main landing gear wheel shaft
The screw thread of port interior surface linkage section；The outer surface of the wheel fixture nut other end is six sides section.In the circle segments and six
Square section diameter has the positioning plate of radially protruding, and the inner face of the positioning plate is bonded with the end face of main landing gear axis.In six side
The circumferential surface of section is uniformly distributed there are three radial screw hole, for by screw by the wheel fixture nut and the cooling motor that brakes
It fastens.
The present invention can be reached for the purpose that more train landing gear structure aircrafts are quickly cooled down cooling.Its function is system prison
Wheel braking temperature is surveyed, when temperature is higher than limit temperature, flight-control computer issues warning information, by opening cockpit
" cooling switch ", the cooling motor of starting brake, so that driving fan high-speed rotation generates air-flow, air-flow is subtracted by main airplane wheel
Light holes is blown into inside brake gear, is carried out heat exchange, is taken away brake heat, realize the rapid cooling of brake temperature.
The technical solution adopted by the present invention to solve the technical problems is: including temperature monitor and control box, temperature sensor,
Brake cooling motor, fan.Temperature sensor is installed on main wheel, acquires brake temperature signal；The cooling motor that brakes is installed
In in undercarriage axis, the fan high speed rotation on the outside of wheel is driven；Temperature monitor and control box is mounted on airplane equipment cabin, passes through electricity
Cable connects temperature sensor and the cooling motor that brakes.
Temperature sensor acquires main wheel brake temperature in real time, and temperature monitor and control box receives temperature signal, and is shown in
On Landing Gear System interface.Aircraft maintenance personnel open depending on feelings and brake in conjunction with aircraft taxi operating condition according to real-time temperature data
Cooling system, cooling motor-driven fan high-speed rotation of braking generate air-flow, and air-flow is blown into brake by main airplane wheel lightening hole
Inside vehicle device, heat exchange is carried out, brake heat is taken away, realizes the rapid cooling of brake temperature.
The beneficial effects of the present invention are: the combination of aircraft brake temperature monitoring and the cooling system that brakes, makes original experience
The inefficient cooling down work of artificial hypothermia's cooling, only ground shutdown status, changes into and is supervised by temperature sensor real time temperature
It surveys, when temperature is higher than limit temperature, starting brake cooling system cools down, and cooling efficiency, effect intuitively show reading, and
It can be cooled down in advance during aircraft taxi, the time that aircraft is set out again not only can be improved, while can also drop
Brake gear and its spare part aging speed, improve the whole service life of brake gear caused by the low height because of brake temperature, from
On the other hand it says, improves economic index.
In the present invention, to ensure flight safety, when aircraft is in " aerial " state, the cooling motor of all brakes stops
Work.
Main airplane wheel, which is installed, has carried out verification test after this system, under test result such as table 1:
Table 1
Detailed description of the invention
Fig. 1 is temperature sensor schematic view of the mounting position；
Fig. 2 is the cooling mounting position of motor schematic diagram that brakes；
Fig. 3 is the cooling electric machine structure schematic diagram that brakes；
Fig. 4 is the cooling motor part logic control schematic diagram that brakes；
Fig. 5 is temperature sensor schematic diagram；
Fig. 6 is the right view of Fig. 5；
Fig. 7 is the cooling electric machine structure schematic diagram that brakes；
Fig. 8 is wheel fixture nut schematic diagram；
Fig. 9 is the left view of Fig. 8.
In figure: 1. temperature sensors；2. cylinder block；3. brake shell；4. fan；5. brake cooling motor；6. fixed machine
Take turns nut；7. main landing gear axis；8. temperature monitor and control box；9. aircraft 115V power supply；10. aircraft 28V power supply；11. open circuit
Device；12. cooling switch；13. relay；14. mounting disc；15. threaded hole；16. convex key；17. annular stopper.
Specific embodiment
The present embodiment is the brake cooling system with six train main airplane wheel of Mr. Yu's type.
The brake cooling system is made of six brake cooling components and a temperature monitor and control box 8.The brake
Vehicle cooling component includes including temperature sensor 1, fan 4 and the cooling motor 5 that brakes.By the temperature in six cooling components of braking
Sensor obtains the temperature socket that signal input part accesses the temperature monitor and control box by data line together, and six brakes are cold
But the power input of motor is connected to the motor socket of the temperature detecting unit together by cable.
Its technical characteristic is described in detail by taking wherein one group of brake cooling component as an example in the present embodiment.
The brake cooling component includes temperature sensor 1, fan 4 and the cooling motor 5 that brakes, in which: by temperature sensing
The mounting disc of device 1 is packed into the mounting hole for 2 outer surface of cylinder block being located on main airplane wheel, and makes the survey of the temperature sensor
It tries in the temperature sensor fixing hole in end insertion brake shell 3.Temperature sensor fixing hole in the brake shell 3 is located at
On the outer end face of the brake shell 3；The centerline parallel of the temperature sensor fixing hole is in the center of the brake shell 3
Line.
The outer surface of described 6 one end of wheel fixture nut is circle segments, and the outer surface of the circle segments is and main gear wheels
The screw thread of axis port interior surface linkage section；At this.The outer surface of the wheel fixture nut other end is six sides section.In the circle
The side's Duan Yuliu section diameter has the positioning plate of radially protruding, and the inner face of the positioning plate is bonded with the end face of main landing gear axis 7.Institute
The circumferential surface for stating six sides section is evenly distributed with there are three radial screw hole, for by screw that the wheel fixture nut and brake is cold
But motor 5 fastens.
The cooling motor 5 of the brake is placed in main landing gear wheel shaft 7 by wheel fixture nut 6；The master rises and falls
Inner surface is the flank cooperated with wheel fixture nut outer surface at frame wheel shaft port；Brake cooling 5 shell of motor circle
Convex key 16 on week is inserted into the convex key keyway for being located at wheel fixture nut inner surface, to limit the cooling motor 5 that brakes
Radial rotating；The wheel fixture nut and the cooling motor that brakes are connected by screw.At the cooling 5 shell outer end end of motor of the brake
External peripheral surface at mouthful has the annular stopper 17 of radially protruding, and when braking, cooling motor 5 is packed into the main landing gear wheel shaft 7
Afterwards, it is bonded the inner face of the annular stopper and the outer end face of wheel fixture nut 6, to limit the axis for the cooling motor 5 that brakes
To jumping.Screw is passed through to the threaded hole being reserved on 6 circumference of wheel fixture nut, screws in the screw to brake on cooling motor 5
In hole 15.The leaf dish of the fan 4 is fixedly mounted on the output shaft for the cooling motor 5 that brakes, and passes through stop washer and nut
It is fixed.The signal output end of temperature sensor 1 is connected to by data line with a signal input part of temperature monitor and control box 8.
The power inlet of the cooling motor 5 of brake is connected to by cable with the power output of the temperature monitor and control box.
The temperature sensor 1 uses K-type thermocouple, and temperature-measuring range is 0 DEG C~1000 DEG C.To be easy for installation, at this
One end of temperature sensor adds mounting disc 14, the gas being fixed on temperature sensor by the mounting disc on main airplane wheel
In the mounting hole of 2 outer surface of cylinder seat.
The output bus of the temperature monitor and control box 8 is connected to aircraft cockpit instrument board；With aircraft power supply as institute
State the power supply of temperature monitor and control box 8；Undercarriage " aerial/ground " status signal passes through data line and temperature monitor and control
" aerial/ground " state signal input terminal connection of box 8；Aircraft cockpit " cooling switch " signal is supervised by data line and temperature
The signal input part connection of " the cooling switch " of observing and controlling box.
The fan 4 uses the prior art, which has 5 blades, be all made of FJZX10 aerofoil profile.The fan leaf dish
The aperture of centre bore is identical as the cooling outer diameter of 5 output shaft of motor that brakes.4 revolving speed of fan is 11000r/min, air quantity 1m3/ s,
Wind pressure 400Pa.
The cooling motor 5 of the brake uses three-phase alternating-current motor, voltage 115V, frequency 400Hz, and revolving speed is
11000r/min.Processing one radial convex key 16 on the external peripheral surface of cooling 5 shell of motor of brake, in the outer circle weekly form of shell
Face convex key symmetric position processes a threaded hole 15；External peripheral surface at cooling 5 outer end port of motor of braking has radial convex
Annular stopper 17 out.
The temperature monitor and control box is used to acquire the output signal of each temperature sensor 1.The temperature monitor and control box
8 are obtained after improving to the temperature monitor and control box of standard.Described thes improvement is that:
The inner cavity of temperature monitor and control box 8 is divided into light current chamber and forceful electric power chamber, and Temperature Treatment module is enclosed in this
Light current is intracavitary, and it is intracavitary that the cooling motor control module that brakes is enclosed in forceful electric power.6 road forceful electric power circuits are furnished with the forceful electric power is intracavitary, point
Not power simultaneously for the cooling motor 5 of 6 tunnels brake.6 signal input parts are placed in the light current chamber, each temperature is received respectively and passes
The output signal of sensor 1.
Input terminal on temperature monitor and control box is connect with a terminals of cooling switch 12；The cooling switch 12 it is another
One terminals is connect with aircraft 28V power supply 10, for controlling the actuation of relay 13.The relay 13 is for controlling to 6
The power supply of the cooling motor 5 of road brake.
At work, six brake cooling components are separately mounted on six main airplane wheels for the present embodiment.It will acquisition
Six road main airplane wheel brake temperature signal of Dao is transmitted separately to temperature monitor and control box 8, and passes through temperature monitor and control box 8
The temperature that each temperature signal is converted to respective host wheel, by data bus interface real-time display in Landing Gear System circle
On face.Aircraft maintenance personnel open cockpit " cooling switch ", the temperature prison according to temperature data on Landing Gear System interface
Observing and controlling box 8 carries out the cockpit received " cooling to switch " signal and undercarriage " aerial/ground " status signal comprehensive
Close judgement, only when aircraft be in " ground " state and " cooling switch " opens, six tunnels brake cooling motor 5 just can sequentially according to
Secondary starting, cooling 5 driving fan of motor, 4 high-speed rotation of braking generate air-flow, and air-flow is blown into brake by main airplane wheel lightening hole
Inside vehicle device, heat exchange is carried out, brake heat is taken away, realizes the rapid cooling of brake temperature.
8 control logic of temperature monitor and control box is shown in Table 2.
Table 2
Claims (8)
1. a kind of six train main airplane wheel brake cooling systems, which is characterized in that the brake cooling system includes six brakes
Vehicle cooling component and a temperature monitor and control box；Each brake cooling component respectively includes temperature sensor, fan and brake
Vehicle cools down motor；The test lead of each temperature sensor is inserted into respectively in brake shell in each temperature sensor fixing hole, and
The temperature socket that the signal input part of each temperature sensor is accessed to the temperature monitor and control box together by data line, will be each
The power input of the cooling motor of brake is connected to the motor socket of the temperature detecting unit together by cable；The temperature
The output bus of monitoring control box is connected to aircraft cockpit instrument board；With aircraft power supply as the temperature monitor and control box
Power supply；" aerial/ground " state that undercarriage " aerial/ground " status signal passes through data line and temperature monitor and control box
Signal input part connection；" cooling to switch " that aircraft cockpit " cooling switch " signal passes through data line and temperature monitor and control box
Signal input part connection；Input terminal on temperature monitor and control box is connect with a terminals of cooling switch；The cooling is opened
Another terminals closed are connect with aircraft power supply；It is used to control the power supply to the cooling motor of 6 tunnels brake by relay.
2. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that each temperature sensor
Mounting disc be fixed on the outer surface of cylinder block.
3. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that in the brake shell
Temperature sensor fixing hole is located on the outer end face of the brake shell, and the centerline parallel of each temperature sensor fixing hole in
The center line of the brake shell.
4. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that the cooling motor of the brake
It is placed in main landing gear wheel shaft by fixed wheel nut；At the main landing gear axle end mouth inner surface be with it is described solid
Determine the flank of wheel nut outer surfaces cooperation；Braking, the convex key insertion on cooling electric machine casing circumference is described to be located at fixed wheel
In the convex key keyway of nut inner surface, to limit the radial rotating for the cooling motor that brakes；The fixation wheel nut and brake cool down
Motor is connected.
5. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that in the cooling motor of the brake
External peripheral surface at the port of shell outer end has the annular stopper of radially protruding, and when braking, cooling motor is packed into main landing gear wheel shaft
Afterwards, it is bonded the inner face of the annular stopper and the outer end face of fixed wheel nut, to limit the axial direction for the cooling motor that brakes
It jumps.
6. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that the leaf dish of the fan is solid
Dingan County is on the output shaft for braking cooling motor；The signal output end of temperature sensor passes through data line and temperature monitor and control
One signal input part of box is connected to；The power inlet of the cooling motor of brake passes through cable and the temperature monitor and control box
Power output connection.
7. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that the temperature monitor and control
The inner cavity of box is divided into light current chamber and forceful electric power chamber, and Temperature Treatment module is enclosed in the light current intracavitary, cooling motor control of braking
It is intracavitary that molding block is enclosed in forceful electric power；6 road forceful electric power circuits are furnished with the forceful electric power is intracavitary, are supplied simultaneously for the 6 tunnels cooling motor that brakes respectively
Electricity；6 signal input parts are placed in the light current chamber, receive the output signal of each temperature sensor respectively.
8. six trains main airplane wheel brake cooling system as described in claim 1, which is characterized in that the wheel fixture nut
The outer surface of one end is circle segments, and the outer surface of the circle segments is the screw thread connecting with main landing gear axle end mouth inner surface；?
The outer surface of the wheel fixture nut other end is six sides section；There is the positioning of radially protruding in the circle segments and six sides section diameter
The inner face of plate, the positioning plate is bonded with the end face of main landing gear axis；Diameter there are three being evenly distributed in the circumferential surface of the six sides section
To screw hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821813094.4U CN209196016U (en) | 2018-11-06 | 2018-11-06 | Six train main airplane wheel brake cooling systems |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821813094.4U CN209196016U (en) | 2018-11-06 | 2018-11-06 | Six train main airplane wheel brake cooling systems |
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| CN209196016U true CN209196016U (en) | 2019-08-02 |
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ID=67410302
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| CN201821813094.4U Active CN209196016U (en) | 2018-11-06 | 2018-11-06 | Six train main airplane wheel brake cooling systems |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562443A (en) * | 2019-10-08 | 2019-12-13 | 西安航空制动科技有限公司 | Cooling controller and control method for airplane brake wheel |
| CN111439243A (en) * | 2020-04-30 | 2020-07-24 | 中国商用飞机有限责任公司 | Brake fan driving device and brake fan driving method |
| US11940027B2 (en) | 2020-12-10 | 2024-03-26 | Airbus Operations Limited | Aircraft brake temperature control system |
-
2018
- 2018-11-06 CN CN201821813094.4U patent/CN209196016U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110562443A (en) * | 2019-10-08 | 2019-12-13 | 西安航空制动科技有限公司 | Cooling controller and control method for airplane brake wheel |
| CN111439243A (en) * | 2020-04-30 | 2020-07-24 | 中国商用飞机有限责任公司 | Brake fan driving device and brake fan driving method |
| US11940027B2 (en) | 2020-12-10 | 2024-03-26 | Airbus Operations Limited | Aircraft brake temperature control system |
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