CN106081074A - Select to slide the airplane wheel brake system of brake based on brake pressure - Google Patents
Select to slide the airplane wheel brake system of brake based on brake pressure Download PDFInfo
- Publication number
- CN106081074A CN106081074A CN201610436272.5A CN201610436272A CN106081074A CN 106081074 A CN106081074 A CN 106081074A CN 201610436272 A CN201610436272 A CN 201610436272A CN 106081074 A CN106081074 A CN 106081074A
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- brake
- wheel
- valve
- pressure
- electrohydraulic servo
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Classifications
-
- 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
- B64C25/44—Actuating mechanisms
-
- 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
- B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
- B60T8/17—Using electrical or electronic regulation means to control braking
- B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
- B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
-
- 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
-
- 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
- B64C25/44—Actuating mechanisms
- B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
Abstract
A kind of airplane wheel brake system sliding brake based on brake pressure selection, including water brake valve, electrohydraulic servo valve, control box, electromagnetic valve, pressure transducer and wheel spin-up transducer.Wherein controlling box, electrohydraulic servo valve and wheel spin-up transducer and constitute brake anti-sliding control part, electromagnetic valve, pressure transducer and control box are used for realizing brake machine wheel brake and select.Pressure transducer is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth.Brake system is exported and is divided into two to the fluid pressure line of wheel brake by the present invention, connects with little brake gear oil-in and big brake gear oil-in respectively.Realizing aircraft floor and slide the least brake gear by controlling two fluid pressure lines and run, two brake gears of other situations run simultaneously, reduce and slide carbon mill in brake and damage, and improve and improve carbon dish service life.The present invention efficiently solves the difficult problem that the brake carbon brake disc abrasion of existing single-wheel list is big, service life is short, improves service life and the economic benefit of carbon dish.
Description
Technical field
The present invention relates to a kind of airplane wheel brake system, especially, relate to a kind of aircraft single-wheel double-brake have based on
Brake pressure selects to slide the brake control system of brake.
Background technology
Aircraft carbon brake uses carbon-to-carbon composite friction material manufacture completely due to brake disc, for the brake of relatively steel, has weight
Measure the advantages such as light, wear-resistant, specific heat is high, high temperature is the most bonding, significantly improve aircraft utilization technical performance and reliance security
Property maintainability economy, thus be used widely on present generation aircraft.Carbon brake is particularly suitable for high-energy brake condition, excellent
Good friction and wear characteristic, gives the long-lived quality of carbon brake disc.But, carbon brake puts into after outfield is run and finds, carbon
Brake disc does not reaches the life value that design is given service life, and have is only about the 60% of value projected life.Carbon dish is caused to make
By the main cause that the life-span is short, present analysis is considered carbon-to-carbon composite friction material to sliding brake bad adaptability, and aircraft is on ground
It is big that wear extent under braking state is slided in face.If the structure that the brake gear of existing brake machine wheel uses " being divided into two " is set
Meter, i.e. single-wheel is equipped with small one and large one two brake gears or double-brake, and little brake is slided for aircraft floor when being used alone
Brake, improves the level that can carry of carbon dish when sliding brake, thus reduces and slide carbon mill damage in brake, improve and improve making of carbon dish
With the life-span, other situations two brake or double-brake use as set of device simultaneously.
Airplane wheel brake system is used for brake control and the anti-sliding control of airplane wheel, wide variety of on current aircraft
It it is electronic anti-skid braking system.Airplane wheel brake system mainly includes handling, detecting and control, for conventional water brake
System, mainly includes water brake valve, electrohydraulic servo valve, wheel spin-up transducer, control box.For a wheel, electronics
The brake machine wheel that anti-skid brake system (ABS) is controlled is the so-called single brake machine wheel on a wheel with a disc brake device,
Even if some aged aircrafts are to meet braking ability to be equipped with the so-called dual brake of two hose type brake gears on a wheel
Car wheel, two brakes of this double-brake wheel are also controlled by brake system to run simultaneously.For solving the use longevity of carbon dish
Life problem, selects to use the requirement of brake according to single-wheel double-brake, and existing airplane wheel brake system does not have this ability.
Summary of the invention
For overcoming the deficiency that can not select brake modes present in prior art, the present invention proposes a kind of based on brake
Pressure selects to slide the airplane wheel brake system of brake.
The present invention includes that water brake valve, electrohydraulic servo valve, control box, electromagnetic valve, pressure transducer and wheel speed pass
Sensor.Control box therein, electrohydraulic servo valve and wheel spin-up transducer constitute brake anti-sliding control part, electromagnetic valve, pressure
Sensor is used for realizing brake machine wheel brake together with controlling box and selects: select little brake gear to run to realize airplane wheel
Part brake, or select little brake gear to run with big brake gear simultaneously, it is achieved whole brakes of airplane wheel.
Water brake valve is arranged on below cockpit floor, driver handle it, the water brake pressure needed for output
Power.Three hydraulic interfaces of water brake valve are water brake valve oil-in, water brake valve brake mouth and water brake respectively
Valve oil return opening.Oil-in water brake valve therein couples with airplane brake system pressure source pipeline, water brake valve brake mouth
Coupling with electrohydraulic servo valve oil-in pipeline, water brake valve oil return opening couples with aircraft return line.
The electrical outlets of described electrohydraulic servo valve is implemented electrically to couple with controlling box by cable, receives and controls what box was sent
Brake anti-sliding control current signal.Three hydraulic interfaces of described electrohydraulic servo valve are electrohydraulic servo valve oil-in, electro-hydraulic respectively
Servo valve brake mouth and electrohydraulic servo valve oil return opening, wherein: described electrohydraulic servo valve oil-in and the brake mouth pipe of brake valve
Road couples；Electrohydraulic servo valve oil return opening couples with aircraft return line；Electrohydraulic servo valve brake mouth fills with two brakes of wheel
Put oil-in pipeline couple, specifically this electrohydraulic servo valve brake mouth connecting pipeline be divided into little brake gear fluid pressure line and
Big brake gear fluid pressure line, wherein: little brake gear fluid pressure line is directly and the little brake gear oil-feed interface of brake machine wheel
Pipeline couples；Big brake gear fluid pressure line joins with by the big brake gear oil-feed interface of pipeline brake machine wheel through electromagnetic valve
Connect.
Wheel spin-up transducer is arranged on plane axletree or in brake shell, is coupled with wheel by machine driving, sense
By wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.The electric interfaces of wheel spin-up transducer is by electricity
Cable electrically couples with controlling box, and the wheel rotary speed voltage signal detected is supplied to control box, monitoring brake machine wheel
Sliding mode.
One input of described control box electric interfaces and wheel spin-up transducer are by cable connection, to receive wheel
The wheel rate signal that velocity sensor provides；Another input of described control box electric interfaces passes through with pressure transducer
Cable connection, to receive the brake pressure signal that pressure transducer is sent.Described by the pressure biography controlling box output control electric current
The brake pressure setting value of sensor impression is 40～65% normal braking pressure；One output of the electric interfaces of described control box
End and electrohydraulic servo valve, by cable connection, send control signal to electrohydraulic servo valve；Another of described control box electrically connects
The outfan of mouth and electromagnetic valve, by cable connection, send to electromagnetic valve and are switched on or switched off control signal；Control box by aircraft electricity
Origin system is powered.
Pressure transducer is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth, and the electric interfaces of this pressure transducer leads to
Cross shielding insulation wire and electrically couple with controlling box electric interfaces input, electrohydraulic servo valve brake in time controlling box input brake
The water brake pressure of mouth output；The hydraulic interface of this pressure transducer is by the hydraulic tube of pipeline with electrohydraulic servo valve brake mouth
Road couples.
Electromagnetic valve is arranged on the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output；The electricity of described electromagnetic valve
Gas interface is electrically coupled with controlling box electric interfaces outfan by shielding insulation wire, receives and controls the control electric current that box is sent
Signal；Three hydraulic interfaces of described electromagnetic valve are electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth respectively, its
In: electromagnetic valve oil-in couples with the brake mouth pipeline of electrohydraulic servo valve；Electromagnetic valve oil-out and the dress that brakes greatly of brake machine wheel
Put oil-feed interface pipeline to couple；Electromagnetic valve oil return mouth couples with aircraft return line.
The present invention uses the way of " being divided into two ", i.e. brake system exports to wheel brake fluid pressure line
Being divided into two, a fluid pressure line leads directly to a little brake gear, and this fluid pressure line keeps unimpeded；Another fluid pressure line sets
Putting control device, then lead to another big brake gear, the break-make of this fluid pressure line is by controlling device control.Thus realize aircraft
The least brake gear of ground taxi runs, the function that the whole brake gear of other situations runs, and slides in brake reaching reduction
Carbon mill damages, and improves the purpose improving carbon dish service life.
In the present invention, by wheel spin-up transducer, control box and electrohydraulic servo valve constitutes brake anti-sliding control part；Electromagnetism
Valve, pressure transducer and control box are used for realizing partly the brake operation of the least brake gear and i.e. two brake gears that all brake
The function all run.By electromagnetic valve, pressure transducer and control box composition control device, brake pressure control methods is used to carry out oil
Road opens and closes and controls, to realize the brake selection of aircraft: when the brake pressure that pressure transducer detects is less than setting value, control
Box does not controls electric current to electromagnetic valve output, and electromagnetic valve is not powered and is in cut-off or closed mode, and electromagnetic valve does not has hydraulic coupling
Output；Otherwise, controlling box and send control signal to electromagnetic valve or electric energy is provided, electromagnetic valve obtains for electrically activating and being in unlatching shape
State, the fluid pressure line that electromagnetic valve controls is open-minded, and electromagnetic valve has hydraulic coupling to export.
Electromagnetic valve is arranged on another fluid pressure line of electrohydraulic servo valve brake mouth output, is provided by pressure transducer
Give the hydraulic pressure signal controlling box, controlled switching on and off of electromagnetic valve by controlling box, thus control electromagnetic valve place hydraulic pressure
Whether pipeline exports and disconnects brake pressure.Control box whether send control current signal to electromagnetic valve, be controlled by pressure sensing
The brake pressure that device detects；When brake pressure is less than setting value, controls box and do not send control current signal to electromagnetic valve, electricity
Magnet valve is not energized and is off, and electromagnetic valve oil-out does not export, and oil-out and oil return opening are linked up；Work as brake pressure
During more than or equal to setting value, controlling box and send control current signal to electromagnetic valve, solenoid valves is opened, and electromagnetic valve oil return mouth closes
Closing, oil-in and oil-out are linked up, and the fluid pressure line that electromagnetic valve controls is open-minded.
The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, can meet single-wheel double-brake and select to use brake
Requirement.Owing to native system has the ability selecting to slide brake, so, when aircraft floor slides brake, only with little brake dress
Put or brake gear runs rather than all brake gears are the most all running, improve the energy of carbon dish when sliding brake
Load level, thus avoid the short slab that carbon-to-carbon composite friction material brake disc low speed mental retardation brake wear extent is excessive, make to slide and stop
Carbon dish wear extent during car reduces, and reaches to improve or improve the purpose in carbon dish service life.Designed by this wheel and system,
Have adjusted the use state of carbon dish, make the anti abrasive good characteristic of carbon-to-carbon composite friction material be given full play of, effectively
Solve the difficult problem that the brake carbon brake disc abrasion of existing single-wheel list is big, service life is short, improve service life and the warp of carbon dish
Ji benefit.
Accompanying drawing explanation
Accompanying drawing 1 is the structural representation of the present invention.In figure:
1. water brake valve；2. electrohydraulic servo valve；3. control box；4. wheel spin-up transducer；5. brake machine wheel；6. electromagnetism
Valve；7. pressure transducer；The least brake gear fluid pressure line；9. big brake gear fluid pressure line；The least brake gear oil-feed connects
Mouthful；11. big brake gear oil-feed interfaces.
Detailed description of the invention
The present embodiment is a kind of airplane wheel brake system selecting to slide brake based on brake pressure.
Described brake system is that conventional hydraulic is handled.Main landing gear is equipped with a brake machine wheel, with two brake gears,
It is referred to as single-wheel double-brake wheel.The brake disc of brake gear uses carbon-to-carbon composite friction material manufacture completely.
The brake disc number of a brake gear in described 2 brake gears is less, and braking for single disc-type or double plate fills
Put, make heat reservoir axial dimension little, therefore the least brake gear；Another brake gear brake disc number is more, for multiple-disc brake
Device, makes heat reservoir axial dimension big, therefore the biggest brake gear.Described little brake gear and big brake gear are all disclosed in
In the innovation and creation of Application No. 201610281025.2:
The heat reservoir of described little brake gear is made up of compression plate, bearing disc and Moving plate, and Moving plate quantity is 1～2 dishes, for single-deck
Formula or double plate brake；Compression plate therein is adjacent with described cylinder block, a card of bearing disc be positioned in brake shell
End surfaces laminating of housing bearing disc, Moving plate is between described compression plate and bearing disc.Described little brake is individually grasped
Brake for ground taxi time vertical.
The heat reservoir of described big brake gear is made up of compression plate, bearing disc, multiple Moving plate and multiple quiet dish；Described Moving plate
Quantity is 3～5 dishes, for multiple-disc brake device；Described compression plate is adjacent with cylinder block, and a card of bearing disc is stopped with being positioned at
One end surfaces laminating of the housing bearing disc on car housing；Multiple Moving plates and multiple quiet dish are with Moving plate-quiet dish-Moving plate-quiet
The interleaved mode of dish is arranged between described compression plate and bearing disc.
The present embodiment includes water brake valve 1, electrohydraulic servo valve 2, controls box 3, electromagnetic valve 6, pressure transducer 7 and wheel
Velocity sensor 4.Control box 3 therein, electrohydraulic servo valve 2 and wheel spin-up transducer 4 constitute brake anti-sliding control part, electricity
Magnet valve 6, pressure transducer 7 are used for realizing brake machine wheel 5 brake together with controlling box 3 and select: the least brake gear runs, with reality
Now part brake, or two brake gears all runs, it is achieved all brake.
Water brake valve 1 is arranged on below cockpit floor, driver handle it, the water brake pressure needed for output
Power.Water brake valve 1 has three hydraulic interfaces, is that water brake valve oil-in, water brake valve brake mouth and hydraulic pressure are stopped respectively
Car valve oil return opening.Described oil-in water brake valve couples with airplane brake system pressure source pipeline, water brake valve brake mouth
Coupling with electrohydraulic servo valve 2 oil-in pipeline, water brake valve oil return opening couples with aircraft return line.
Electrohydraulic servo valve 2 has an electrical outlets and three hydraulic interfaces.Three described hydraulic interfaces are electro-hydraulic respectively
Servo valve oil-in, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening.Described electrical outlets passes through connectorized cable
Implement electrically to couple with controlling box 3, receive and control the brake anti-sliding control current signal that box 3 is sent.
Described electrohydraulic servo valve oil-in couples with the brake mouth pipeline of brake valve 1；Electrohydraulic servo valve brake mouth and machine
Two brake gear oil-in pipelines of wheel couple, specifically at the connecting pipeline of this electrohydraulic servo valve brake mouth through three way cock
Be divided into little brake gear fluid pressure line 8 and big brake gear fluid pressure line 9, little brake gear fluid pressure line 8 therein directly with
Little brake gear oil-feed interface 10 pipeline of brake machine wheel 5 couples；Big brake gear fluid pressure line 9 is through electromagnetic valve 6 and braking machine
Big brake gear oil-feed interface 11 pipeline of wheel 5 couples, specifically, by described big brake gear fluid pressure line 9 and electromagnetic valve 6
Oil-in pipeline couples, and is coupled with big brake gear oil-in 11 pipeline of brake machine wheel 5 by the oil-out of described electromagnetic valve 6.
Electrohydraulic servo valve oil return opening couples with aircraft return line.Electrohydraulic servo valve 2 is not when controlling electric current, and oil return opening is closed, and enters
Hydraulic fluid port and brake mouth oil circuit couple unimpeded, and electrohydraulic servo valve is only a passage.
Wheel spin-up transducer 4 is arranged on plane axletree or in brake shell, is coupled with wheel by machine driving, sense
By wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.In the present embodiment, described wheel spin-up transducer 4
It is arranged on plane axletree, brake machine wheel 5 hub drive pin is rotated.The electric interfaces of wheel spin-up transducer 4 passes through
Cable electrically couples with controlling box 3, is supplied to the wheel rotary speed voltage signal detected control box, monitors brake machine wheel
The sliding mode of 5.
Control box 3 and there is brake anti-sliding control, the function of fault detect.One input of described control box 3 electric interfaces
End and wheel spin-up transducer 4 are by cable connection, to receive the wheel rate signal that wheel spin-up transducer 4 provides；Described
Control another input and the pressure transducer 7 of box 3 electric interfaces by cable connection, send receiving pressure transducer 7
Brake pressure signal.Described export that to control the brake pressure setting value experienced of pressure transducer 7 of electric current be 40 by controlling box 3
～65% normal braking pressure；The present embodiment brake pressure setting value is 55% normal braking pressure；
One outfan of the electric interfaces of described control box 3 and electrohydraulic servo valve 2 are by cable connection, to electro-hydraulic servo
Valve 2 sends control signal；The outfan of another electric interfaces of described control box 3 and electromagnetic valve 6 are by cable connection, to electricity
Magnet valve 6 sends and is switched on or switched off control signal；Control box 3 to be powered by aircraft power system.
Pressure transducer 7 be arranged on electrohydraulic servo valve 3 brake mouth fluid pressure line on, to experience brake pressure, will brake
Pressure transition is that the signal of telecommunication is supplied to control box 3, is used for controlling turning on or off of electromagnetic valve 6.Described pressure transducer 7 has one
Individual electric interfaces and a hydraulic interface.Described electric interfaces is by shielding insulation wire and control box 3 electric interfaces input
Electrically coupling, in time controlling box 3 input brake, electrohydraulic servo valve 2 brakes the water brake pressure of mouth output；Pressure transducer 7
Hydraulic interface is coupled by brake with electrohydraulic servo valve 2 fluid pressure line of mouth of pipeline.
Electromagnetic valve 6 be arranged on electrohydraulic servo valve 2 brake mouth output big brake gear fluid pressure line 9 on, passed by pressure
Sensor 7 is supplied to control the hydraulic pressure signal of box 3, is controlled switching on and off of electromagnetic valve 6 by controlling box 3, thus controls electricity
Whether magnet valve 6 place fluid pressure line exports and disconnects brake pressure.
Described electromagnetic valve 6 has an electric interfaces and three hydraulic interfaces.Described three hydraulic interfaces are electromagnetic valve respectively
Oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth.
The electric interfaces of electromagnetic valve 6 is electrically coupled with controlling box 3 electric interfaces outfan by shielding insulation wire；Receive
Control the control current signal that box 3 is sent；Control box 3 whether send control current signal to electromagnetic valve 6, be controlled by pressure sensing
The brake pressure that device 7 detects；When brake pressure is less than setting value, controls box 3 and do not send control electric current letter to electromagnetic valve 6
Number, electromagnetic valve 6 is not energized and is off, and electromagnetic valve 6 oil-out does not export, and oil-out and oil return opening are linked up；When
When brake pressure is more than or equal to setting value, controlling box 3 and send control current signal to electromagnetic valve 6, electromagnetic valve 6 energising is opened, electricity
Magnet valve 6 oil return opening is closed, and oil-in and oil-out are linked up, and the fluid pressure line that electromagnetic valve 6 controls is open-minded.
In three hydraulic interfaces of described electromagnetic valve, electromagnetic valve oil-in couples with the brake mouth pipeline of electrohydraulic servo valve 2；
Electromagnetic valve oil-out couples with big brake gear oil-feed interface 11 pipeline of brake machine wheel 5；Electromagnetic valve oil return mouth and aircraft oil return
Pipeline couples.
Wheel velocity measuring is completed by wheel spin-up transducer 4；Anti-sliding control is completed by controlling box 3；Electrohydraulic servo valve 2 sound
The control current signal of box 3 should be controlled, export and regulate the brake pressure transporting to brake machine wheel 5.
Select brake by electromagnetic valve 6, pressure transducer 7 and to control box 3 composition control device, use brake pressure control methods
Carry out oil circuit and open and close control realization；When the brake pressure that pressure transducer 7 detects is less than setting value, control box 3 not to electricity
Magnet valve 6 output controls electric current, and electromagnetic valve 6 is not powered and is in cut-off or closed mode, and electromagnetic valve 6 does not has hydraulic coupling to export；
Otherwise, controlling box 3 and send control signal to electromagnetic valve 6 or electric energy is provided, electromagnetic valve 6 obtains for electrically activating and being in unlatching shape
State, the fluid pressure line that electromagnetic valve 6 controls is open-minded, and electromagnetic valve 6 has hydraulic coupling to export.That is, Article 1 brake passage i.e. fluid pressure line 8
Unblocked, it is ensured that to can be used at any time braking, Article 2 brake passage i.e. fluid pressure line 9 is with good conditionsi open-minded, makes described brake
System ensure that only uses little brake gear when aircraft floor slides brake, little brake gear and big brake gear in the case of other
Use, it is achieved the double-brake to aircraft simultaneously.
Brake process skids if there is wheel, by controlling box 3, electrohydraulic servo valve 2 and wheel spin-up transducer 4 structure
The brake anti-sliding control part become is implemented to control.Anti-sliding control is realized by prior art.
Claims (7)
1. selecting to slide an airplane wheel brake system for brake based on brake pressure, the main landing gear of aircraft is stopped equipped with one
Car wheel, this brake machine wheel has little brake gear and big brake gear, it is characterised in that include water brake valve, electro-hydraulic servo
Valve, control box, electromagnetic valve, pressure transducer and wheel spin-up transducer；Control box therein, electrohydraulic servo valve and wheel speed
Sensor constitutes brake anti-sliding control part, and electromagnetic valve, pressure transducer are used for realizing brake machine wheel brake together with control box
Select: select little brake gear to run the part to realize airplane wheel and brake, or select little brake gear and the dress that brakes greatly
Put and run simultaneously, it is achieved whole brakes of airplane wheel.
2. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that liquid
Pressure brake valve is arranged on below cockpit floor, driver handle it, the water brake pressure needed for output；Water brake
Three hydraulic interfaces of valve are water brake valve oil-in, water brake valve brake mouth and water brake valve oil return opening respectively；Its
In oil-in water brake valve couple with airplane brake system pressure source pipeline, water brake valve brake mouth and electrohydraulic servo valve
Oil-in pipeline couples, and water brake valve oil return opening couples with aircraft return line.
3. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that institute
The electrical outlets stating electrohydraulic servo valve is implemented electrically to couple with controlling box by cable, receives and controls the anti-slip control of brake that box is sent
Current signal processed；Three hydraulic interfaces of described electrohydraulic servo valve are electrohydraulic servo valve oil-in, electrohydraulic servo valve brake respectively
Mouth and electrohydraulic servo valve oil return opening, wherein: described electrohydraulic servo valve oil-in couples with the brake mouth pipeline of brake valve；Electro-hydraulic
Servo valve oil return opening couples with aircraft return line；Electrohydraulic servo valve brake mouth and two brake gear oil-in pipelines of wheel
Coupling, the specifically connecting pipeline at this electrohydraulic servo valve brake mouth is divided into little brake gear fluid pressure line and big brake gear liquid
Pressure pipe road, wherein: little brake gear fluid pressure line directly couples with the little brake gear oil-feed interface pipeline of brake machine wheel；Stop greatly
Car device fluid pressure line couples with by the big brake gear oil-feed interface of pipeline brake machine wheel through electromagnetic valve.
4. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that machine
Wheel speed sensor is arranged on plane axletree or in brake shell, is coupled with wheel by machine driving, experiences wheel and rotates
Speed, is converted to signal of telecommunication output by wheel rotary speed；The electric interfaces of wheel spin-up transducer is by cable and control box
Electrically couple, the wheel rotary speed voltage signal detected is supplied to control box, the sliding mode of monitoring brake machine wheel.
5. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that institute
State the input controlling box electric interfaces with wheel spin-up transducer by cable connection, to receive wheel spin-up transducer
The wheel rate signal provided；Another input of described control box electric interfaces passes through cable connection with pressure transducer,
To receive the brake pressure signal that pressure transducer is sent；The described pressure transducer impression being controlled electric current by control box output
Brake pressure setting value is 40～65% normal braking pressure；One outfan of the electric interfaces of described control box is watched with electro-hydraulic
Take valve and pass through cable connection, send control signal to electrohydraulic servo valve；The outfan of another electric interfaces of described control box
With electromagnetic valve by cable connection, send to electromagnetic valve and be switched on or switched off control signal；Control box to be powered by aircraft power system.
6. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that pressure
Force transducer is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth, and the electric interfaces of this pressure transducer passes through shielding insulation
Wire electrically couples with controlling box electric interfaces input, the liquid of electrohydraulic servo valve brake mouth output in time controlling box input brake
Pressure brake pressure；The hydraulic interface of this pressure transducer is coupled by the fluid pressure line of pipeline with electrohydraulic servo valve brake mouth.
7. select to slide the airplane wheel brake system of brake based on brake pressure as claimed in claim 1, it is characterised in that electricity
Magnet valve is arranged on the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output；The electric interfaces of described electromagnetic valve passes through
Shielding insulation wire electrically couples with controlling box electric interfaces outfan, receives and controls the control current signal that box is sent；Described
Three hydraulic interfaces of electromagnetic valve are electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth respectively, wherein: electromagnetic valve
Oil-in couples with the brake mouth pipeline of electrohydraulic servo valve；Electromagnetic valve oil-out and the big brake gear oil-feed interface of brake machine wheel
Pipeline couples；Electromagnetic valve oil return mouth couples with aircraft return line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610436272.5A CN106081074B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel brake system of brake is slided based on brake pressure selection |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610436272.5A CN106081074B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel brake system of brake is slided based on brake pressure selection |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106081074A true CN106081074A (en) | 2016-11-09 |
| CN106081074B CN106081074B (en) | 2017-12-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610436272.5A Expired - Fee Related CN106081074B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel brake system of brake is slided based on brake pressure selection |
Country Status (1)
| Country | Link |
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| CN (1) | CN106081074B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113895415A (en) * | 2021-09-13 | 2022-01-07 | 西安航空制动科技有限公司 | Method for converting working modes of airplane wheel braking system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000142359A (en) * | 1998-11-12 | 2000-05-23 | Akebono Brake Ind Co Ltd | Antilock controlling method |
| EP1135286B1 (en) * | 1999-10-02 | 2002-12-18 | DaimlerChrysler AG | Braking system comprising an electro-hydraulic brake booster for a vehicle |
| CN102556340A (en) * | 2012-03-03 | 2012-07-11 | 西安航空制动科技有限公司 | Airplane anti-skid brake control system and method |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
-
2016
- 2016-06-17 CN CN201610436272.5A patent/CN106081074B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000142359A (en) * | 1998-11-12 | 2000-05-23 | Akebono Brake Ind Co Ltd | Antilock controlling method |
| EP1135286B1 (en) * | 1999-10-02 | 2002-12-18 | DaimlerChrysler AG | Braking system comprising an electro-hydraulic brake booster for a vehicle |
| CN102556340A (en) * | 2012-03-03 | 2012-07-11 | 西安航空制动科技有限公司 | Airplane anti-skid brake control system and method |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113895415A (en) * | 2021-09-13 | 2022-01-07 | 西安航空制动科技有限公司 | Method for converting working modes of airplane wheel braking system |
| CN113895415B (en) * | 2021-09-13 | 2023-08-18 | 西安航空制动科技有限公司 | Working mode conversion method of airplane wheel braking system |
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