CN106081073A - A kind of aircraft single-wheel double-brake optional Flight By Wire brake system - Google Patents
A kind of aircraft single-wheel double-brake optional Flight By Wire brake system Download PDFInfo
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- CN106081073A CN106081073A CN201610436221.2A CN201610436221A CN106081073A CN 106081073 A CN106081073 A CN 106081073A CN 201610436221 A CN201610436221 A CN 201610436221A CN 106081073 A CN106081073 A CN 106081073A
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- brake
- wheel
- oil
- servo valve
- electrohydraulic servo
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Classifications
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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
- B64C25/44—Actuating mechanisms
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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
- B60T13/00—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems
- B60T13/10—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with fluid assistance, drive, or release
- B60T13/66—Electrical control in fluid-pressure brake systems
- B60T13/68—Electrical control in fluid-pressure brake systems by electrically-controlled valves
- B60T13/686—Electrical control in fluid-pressure brake systems by electrically-controlled valves in hydraulic systems or parts thereof
-
- 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
- B60T8/171—Detecting parameters used in the regulation; Measuring values used in the regulation
-
- 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
- B60T8/32—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
- B60T8/321—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration deceleration
- B60T8/325—Systems specially adapted for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
Abstract
A kind of aircraft single-wheel double-brake optional Flight By Wire brake system, including brake instruction transducer, controls box, electrohydraulic servo valve, hydraulic selector, electromagnetic valve and wheel spin-up transducer.Described wheel spin-up transducer, control box and electrohydraulic servo valve constitute brake anti-sliding control part；Hydraulic selector and electromagnetic valve are for realizing the selection of brake modes；The described selection realizing brake modes is to select little brake gear to run to realize the brake of the part to wheel, or selects little brake gear to run with big brake gear simultaneously, it is achieved the double-brake to wheel.The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, disclosure satisfy that single-wheel double-brake selects to use the requirement of brake, have adjusted the use state of carbon dish, the carbon anti abrasive good characteristic of carbon composite friction material is made to be given full play of, efficiently 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 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 adnexa, detection accessory and control adnexa, for often
The hydraulic brake system of rule, mainly includes water brake valve, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box；For
Brake-by-wire system, mainly includes brake instruction transducer, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box, with often
The hydraulic brake system of rule is compared, and brake instruction transducer instead of water brake valve, additionally, Electric hydraulic pressure servo valve is just to increase
Benefit valve.Airplane wheel brake system controls the single brake machine wheel on a wheel with a brake, or on a wheel with
The double-brake wheel of two brakes, such as hose type double-brake wheel, the operation of two brakes of double-brake wheel is to carry out simultaneously
's.Select to use the requirement of brake according to single-wheel double-brake, existing airplane wheel brake system does not have this ability.
Summary of the invention
For overcoming the deficiency selecting brake modes present in prior art, the present invention proposes a kind of aircraft single-wheel dual brake
Car optional Flight By Wire brake system.
The present invention includes brake instruction transducer, controls box, electrohydraulic servo valve, hydraulic selector, electromagnetic valve and wheel speed
Sensor.Described wheel spin-up transducer, control box and electrohydraulic servo valve constitute brake anti-sliding control part；Hydraulic selector and electricity
Magnet valve is for realizing the selection of brake modes；The described selection realizing brake modes is to select little brake gear to run to realize machine
The part brake of wheel, or select little brake gear to run with big brake gear simultaneously, it is achieved the double-brake to wheel.
Described brake instruction transducer is arranged on below cockpit floor, and the electric interfaces of this brake instruction transducer passes through
Cable electrically couples with controlling box, is supplied to the brake instruction voltage signal of driver control box, for the brake of wheel.
Described electrohydraulic servo valve is selected hydraulic lock electrohydraulic servo valve；The electrical outlets of described electrohydraulic servo valve passes through cable
Implement electrically to couple with controlling box；Described electrohydraulic servo valve hydraulic interface be electrohydraulic servo valve oil-in respectively, electro-hydraulic watch
Take valve brake mouth and electrohydraulic servo valve oil return opening.Electrohydraulic servo valve oil-in therein is by hydraulic lock and brake system pressure source
Carry out oil pipe line to couple；The little brake gear oil-in of described electrohydraulic servo valve brake mouth and wheel and big brake gear oil inlet pipe
Road couples, and brake mouth connecting pipeline is specifically divided into little brake gear fluid pressure line and big brake gear fluid pressure line, and makes
Little brake gear fluid pressure line therein directly couples with the little brake gear oil-in pipeline of wheel so that it is in the dress that brakes greatly
Put fluid pressure line to couple with the big brake gear oil-in pipeline of wheel through electromagnetic valve；The oil-out of described electromagnetic valve and wheel
Big brake gear oil-in pipeline couples.Described electrohydraulic servo valve oil return opening couples with aircraft return line；
Velocity sensor is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode and wheel
Couple, experience wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.
Hydraulic selector is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth.The electric interfaces of hydraulic selector is by shielding
Insulated conductor electrically couples with the electric interfaces of electromagnetic valve, specifically by the electromagnetism of the microswitch of this hydraulic selector Yu electromagnetic valve
Iron coil is connected, and is switched on or switched off the control current signal of the electromagnet coil being supplied to electromagnetic valve；The hydraulic pressure of hydraulic selector connects
Mouth couples with the brake mouth pipeline of electrohydraulic servo valve.
Electromagnetic valve is arranged on the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output, is entered by hydraulic control
And become electric control and realize oil-feed oil circuit and the communication of fuel-displaced oil circuit and disconnection, thus control place fluid pressure line whether export and
Disconnect brake pressure.The electric interfaces of described electromagnetic valve is electrically joined by the electric interfaces of shielding insulation wire with hydraulic selector
Connecing, specifically, the electromagnet coil of electromagnetic valve is connected with the microswitch of hydraulic selector, then is connected on power supply, receives
Control current signal is sent after the microswitch Guan Bi of hydraulic selector；
The hydraulic interface of described electromagnetic valve is electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth respectively.Its
In: electromagnetic valve oil-in is connected in parallel on little brake gear fluid pressure line by pipeline, thus with the brake mouth of electrohydraulic servo valve even
Logical；Electromagnetic valve oil-out is coupled by big brake gear fluid pressure line with described big brake gear oil-in；Electromagnetic valve oil return mouth
Couple with aircraft return line.
The brake pressure setting value of described control hydraulic selector is 40～65% normal braking pressure.
The input of the electric interfaces of described control box passes through cable with velocity sensor and brake instruction transducer respectively
Couple, the brake instruction voltage signal that the wheel speed of reception velocity sensor offer respectively and brake instruction transducer are sent.
Control the outfan of the electric interfaces of box, with electrohydraulic servo valve cable connection, send control signal to electrohydraulic servo valve；Control
Box is powered by aircraft power system.
For adapting to the needs of main landing gear single-wheel double-brake wheel structure choice brake, the present invention uses " being divided into two "
Way, i.e. brake system export and are divided into two to wheel brake fluid pressure line, and a fluid pressure line leads directly to one
Little brake gear, this fluid pressure line keeps unimpeded；Another fluid pressure line arranges control device, then leads to another big brake
Device, the break-make of this fluid pressure line is by controlling device control.Thus realize aircraft floor and slide the operation of the least brake gear, other
The function that the whole brake gear of situation runs, slides in brake carbon mill and damages reaching reduction, improves and improves carbon dish service life
Purpose；
In the present invention, wheel spin-up transducer, controls box and electrohydraulic servo valve constitutes brake anti-sliding control part；Hydraulic pressure is opened
Close and electromagnetic valve is used for realizing the part the least brake gear that brakes and runs and whole brake merits that i.e. two brake gears all run
Energy.Compared with conventional hydraulic brake system, brake instruction transducer instead of water brake valve, additionally, electrohydraulic servo valve is
Postiive gain valve, brake instruction transducer and control box, electrohydraulic servo valve constitute brake and control part；Electrohydraulic servo valve and control box
Both complete control task of braking, complete again anti-sliding control task.
For safeguards system safe and reliable operation, select the electrohydraulic servo valve with hydraulic lock, receive when controlling box brake first
The signal of telecommunication first unblanked, next oily to connect the voltage supply of electrohydraulic servo valve.
Brake is selected to use brake pressure control methods to carry out oil by the control device being made up of electromagnetic valve and hydraulic selector
Road opens and closes control realization: when brake pressure is less than setting value, and hydraulic selector disconnects the power supply circuits of electromagnetic valve, and electromagnetic valve does not has
Powering and be in cut-off or closed mode, electromagnetic valve does not has hydraulic coupling to export；Otherwise, hydraulic selector is connected or closed electromagnetic valve
Power supply circuits, electromagnetic valve obtains for electrically activating and being in opening, and the fluid pressure line that electromagnetic valve controls is open-minded, and electromagnetic valve has liquid
Pressure exports.
In the present invention, electrohydraulic servo valve is not when controlling electric current, and oil-in is closed, and oil return opening and brake mouth oil circuit couple
Unimpeded；Electrohydraulic servo valve is when there being control electric current, and oil return opening is closed, and oil-in opens, and with brake mouth oil circuit UNICOM, brake mouth is defeated
Go out the corresponding water brake pressure controlling electric current；The control electric current controlling box input electrohydraulic servo valve is the biggest, and electrohydraulic servo valve is defeated
The brake pressure gone out is the biggest, it is achieved that the Stress control of postiive gain.
In the present invention, the unlatching of electromagnetic valve is controlled by hydraulic selector, and the closed and disconnected of hydraulic selector is controlled by electro-hydraulic
The output brake pressure of servo valve, when brake pressure is less than setting value, hydraulic selector is not enough to by the piston of action of hydraulic force
Promoting push rod microswitch button Guan Bi to be connected, hydraulic selector is still off, and electromagnetic valve is not energized and is off,
Electromagnetic valve oil-out does not export, and oil-out and oil return opening are linked up；When brake pressure is more than or equal to setting value, hydraulic selector closes
Closing circuit, solenoid valves is opened, and electromagnetic valve oil return mouth is closed, and oil-in and oil-out are linked up, the hydraulic tube that electromagnetic valve controls
Road is open-minded.
In the present invention, when Article 1 brake passage i.e. fluid pressure line is unblocked, it is ensured that can be used at any time braking, second
Bar brake passage i.e. fluid pressure line is with good conditionsi open-minded.So, described brake system when ensureing that aircraft floor slides brake only
Using little brake gear, in the case of other, two brake gears use simultaneously, it is achieved the double-brake of aircraft.
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. brake instruction transducer；2. electrohydraulic servo valve；3. control box；4. velocity sensor；5. brake machine wheel；6. electromagnetism
Valve；7. hydraulic selector；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 aircraft main landing gear of the present embodiment is equipped with a brake machine wheel, with two brake gears, referred to as single-wheel dual brake
Car wheel.The brake disc of brake gear uses carbon-to-carbon composite friction material manufacture completely.
Said two brake gear is little brake gear and big brake gear respectively.The brake disc number of described little brake gear
Less, make heat reservoir axial dimension little, therefore the least brake gear；The brake disc number of described big brake gear is more, makes heat reservoir axle
Big to size, therefore the biggest brake gear.Described little brake gear and big brake gear are all disclosed in Application No.
201610281025.2 innovation and creation in:
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.
Brake system described in the present embodiment is fly-by-wire, including brake instruction transducer 1, controls box 3, electro-hydraulic
Servo valve 2, hydraulic selector 7, electromagnetic valve 6 and wheel spin-up transducer 4.Described wheel spin-up transducer 4, control box 3 and electro-hydraulic
Servo valve 2 constitutes brake anti-sliding control part；Hydraulic selector 7 and electromagnetic valve 6 with realize the selection of brake modes, i.e. select little
Brake gear runs, it is achieved brakes the part of wheel, or selects little brake gear to run with big brake gear simultaneously, to realize
Double-brake to wheel.
Described brake instruction transducer 1 is arranged on below cockpit floor, driver handle it, controls output required
Brake instruction voltage signal, then controlled electrohydraulic servo valve 2 export required water brake pressure by controlling box 3.Brake instruction
Sensor 1 has an electric interfaces, is electrically coupled with controlling box 3 by cable, is carried by the brake instruction voltage signal of driver
Supply controls box 3, for the brake of wheel.
Described electrohydraulic servo valve 2 has an electrical outlets and three hydraulic interfaces.Described electrical outlets is by band plug
Cable is implemented electrically to couple with controlling box 3, receives and controls the brake anti-sliding control current signal that box 3 is sent.Described three hydraulic pressure
Interface is electrohydraulic servo valve oil-in, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening respectively.Electro-hydraulic servo therein
Valve oil-in carrys out oil pipe line with brake system pressure source and couples, by the oil-out connection of this electrohydraulic servo valve oil-in with hydraulic lock
Connect, carry out oil pipe line by hydraulic lock with brake system pressure source and couple；Described electrohydraulic servo valve brake mouth is stopped with the little of wheel
Car device oil-in and big brake gear in-line couple, and specifically through three way cock, brake mouth connecting pipeline are divided into little stopping
Car device fluid pressure line 8 and big brake gear fluid pressure line 9, and make little brake gear fluid pressure line 8 therein directly and wheel
Little brake gear oil-in 10 pipeline couple so that it is in big brake gear fluid pressure line 9 stopping greatly through electromagnetic valve 6 and wheel
Car device oil-in 11 pipeline couple so that described electrohydraulic servo valve 2 brake mouth also with electromagnetic valve 6 oil-in pipeline connection；Institute
Big brake gear oil-in 11 pipeline of the oil-out and wheel of stating electromagnetic valve couples.
Described electrohydraulic servo valve oil return opening couples with aircraft return line；When electrohydraulic servo valve does not control electric current, electricity
Hydraulic servo oil-in is closed, and electrohydraulic servo valve oil return opening couples unimpeded with electrohydraulic servo valve brake mouth oil circuit；Work as electro-hydraulic servo
When valve 2 has control electric current, electrohydraulic servo valve oil return opening is closed, and electrohydraulic servo valve oil-in is opened, with electrohydraulic servo valve brake mouth
Oil circuit UNICOM, this electrohydraulic servo valve brake mouth output correspondence controls the water brake pressure of electric current.Control box 3 and input electro-hydraulic servo
The control electric current of valve 2 is the biggest, and the brake pressure of electrohydraulic servo valve output is the biggest, it is achieved that the Stress control of postiive gain；Electro-hydraulic watch
Take valve 2 and control box 3 had both completed control task of braking, complete again anti-sliding control task.
For safeguards system safe and reliable operation, select with hydraulic lock electrohydraulic servo valve 2, receive and control head when box 3 brakes
The signal of telecommunication first unblanked, next oily to connect the voltage supply of electrohydraulic servo valve 2.
Velocity sensor 4 is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode and wheel
Couple, experience wheel rotary speed, wheel rotary speed is converted to signal of telecommunication output.The present embodiment velocity sensor 4 is installed
On plane axletree, brake machine wheel 5 hub drive pin it is rotated.The electric interfaces of velocity sensor 4 passes through cable and control
Box 3 processed electrically couples, and the wheel rotary speed voltage signal detected is supplied to control box 3, the sliding mode of monitoring wheel.
Hydraulic selector 7 be arranged on electrohydraulic servo valve 2 brake mouth fluid pressure line on, specifically brake at electrohydraulic servo valve 2
On the fluid pressure line of mouth.Described hydraulic selector 7 includes piston, push rod and microswitch.Brake pressure experienced by hydraulic selector 7, behaviour
Vertical microswitch is to control disconnection and the Guan Bi of electric wiring.
Hydraulic selector 7 has an electric interfaces and a hydraulic interface.Described electric interfaces by shielding insulation wire with
The electric interfaces of electromagnetic valve 6 electrically couples, specifically by the electromagnet coil of the microswitch of this hydraulic selector 7 Yu electromagnetic valve 6
Series connection, is switched on or switched off the control current signal of the electromagnet coil being supplied to electromagnetic valve 6；Hydraulic selector 7 hydraulic interface and electricity
The brake mouth pipeline of hydraulic servo 2 couples.
Electromagnetic valve 6 be arranged on electrohydraulic servo valve 2 brake mouth output another fluid pressure line 9 on, entered by hydraulic control
And become electric control and realize oil-feed oil circuit and the communication of fuel-displaced oil circuit and disconnection, thus control place fluid pressure line whether export and
Disconnect 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.Wherein:
Electromagnetic valve oil-in is connected in parallel on little brake gear fluid pressure line 8 by pipeline, thus with the stopping of electrohydraulic servo valve 2
Car mouth connects；Electromagnetic valve oil-out is coupled by big brake gear fluid pressure line 9 with described big brake gear oil-in 11；Electromagnetism
Valve oil return opening couples with aircraft return line.
The electric interfaces of described electromagnetic valve 6 is electrically coupled with the electric interfaces of hydraulic selector 7 by shielding insulation wire, tool
Body ground, the electromagnet coil of electromagnetic valve 6 is connected with the microswitch of hydraulic selector 7, then is connected on power supply, receives hydraulic pressure
Control current signal is sent after the microswitch Guan Bi of switch 7；The unlatching of electromagnetic valve 6 is controlled by hydraulic selector 7, and hydraulic selector
The closed and disconnected of 7 is controlled by the output brake pressure of electrohydraulic servo valve 2: when brake pressure is less than setting value, hydraulic selector 7
Being not enough to promote push rod microswitch button Guan Bi to be connected by the piston of action of hydraulic force, hydraulic selector 7 is still off, electromagnetism
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；Work as brake pressure
During more than or equal to setting value, hydraulic selector 7 closes circuit, and electromagnetic valve 6 energising is opened, and electromagnetic valve 6 oil return opening is closed, oil-in and
Oil-out is linked up, and the fluid pressure line that electromagnetic valve 6 controls is open-minded.
The brake pressure setting value of described control hydraulic selector 7 is 40～65% normal braking pressure；The present embodiment brakes
Pressure set points is 55% normal braking pressure；
Control box 3 and there is brake anti-sliding control and fault detection capability.Control box 3 electric interfaces input respectively with
Velocity sensor 4 and brake instruction transducer 1 by cable connection, receive respectively wheel speed that velocity sensor 4 provides and
The brake instruction voltage signal that brake instruction transducer 1 is sent.Control the outfan of the electric interfaces of box 3, with electrohydraulic servo valve 2
By cable connection, send control signal to electrohydraulic servo valve 2；Control box 3 to be powered by aircraft power system.
By the control device being made up of electromagnetic valve 6 and hydraulic selector 7.Brake pressure control methods is used to carry out oil circuit keying
Control to select brake modes: when brake pressure is less than setting value, hydraulic selector 7 disconnects the power supply circuits of electromagnetic valve 6, electromagnetic valve
6 do not power and are in cut-off or closed mode, and electromagnetic valve 6 does not has hydraulic coupling to export；Otherwise, hydraulic selector 7 is connected or is closed
The power supply circuits of electromagnetic valve 6, electromagnetic valve 6 obtains for electrically activating and being in opening, and the fluid pressure line that electromagnetic valve 6 controls leaves
Logical, electromagnetic valve 6 has hydraulic coupling to export.
In the present embodiment, little brake gear fluid pressure line 8 is unblocked, it is ensured that can be used in brake at any time, brake greatly dress
Put fluid pressure line 9 with good conditionsi open-minded.So, described brake system ensure that and only uses little brake when aircraft floor slides brake
Device, in the case of other, little brake gear and big brake gear are tested simultaneously, to realize the double-brake of aircraft.
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.
Compared with conventional hydraulic brake system, in the present embodiment, brake instruction transducer 1 instead of water brake valve,
Additionally, electrohydraulic servo valve 2 is postiive gain valve, brake instruction transducer 1 and control box 3, electrohydraulic servo valve 2 constitute brake control portion
Point；Electrohydraulic servo valve 2 and control box 3 had both completed control task of braking, and completed again anti-sliding control task.
For safeguards system safe and reliable operation, electrohydraulic servo valve 2 is also with hydraulic lock, when reception control box 3 brakes first
The signal of telecommunication unblanked, next oily to connect the voltage supply of electrohydraulic servo valve 2.
Wheel velocity measuring is completed by wheel spin-up transducer 4, the sliding mode of monitoring wheel；Anti-sliding control is by controlling box
3 complete；Electrohydraulic servo valve 2 response controls the control current signal of box, exports and regulate the brake pressure transporting to brake machine wheel 5；
Brake is selected to be carried out by pilot operated valve device.
Claims (7)
1. an aircraft single-wheel double-brake optional Flight By Wire brake system, the main landing gear of aircraft is equipped with a braking machine
Wheel, this brake machine wheel has two brake gears, it is characterised in that described Flight By Wire brake system includes that brake instruction senses
Device, control box, electrohydraulic servo valve, hydraulic selector, electromagnetic valve and wheel spin-up transducer；Described wheel spin-up transducer, control
Box and electrohydraulic servo valve constitute brake anti-sliding control part；Hydraulic selector and electromagnetic valve are for realizing the selection of brake modes；Institute
Stating and realizing the selection of brake modes is to select little brake gear to run to realize the part to wheel and brake, or selects little brake gear
Run with big brake gear, it is achieved the double-brake to wheel simultaneously.
2. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that described brake
Instruction sensor is arranged on below cockpit floor, and the electric interfaces of this brake instruction transducer is electric with control box by cable
Couple, be supplied to the brake instruction voltage signal of driver control box, for the brake of wheel.
3. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that described electro-hydraulic
Servo valve is selected hydraulic lock electrohydraulic servo valve；The electrical outlets of described electrohydraulic servo valve is implemented electrically with controlling box by cable
Couple；Described electrohydraulic servo valve hydraulic interface be electrohydraulic servo valve oil-in, electrohydraulic servo valve brake mouth and electro-hydraulic respectively
Servo valve oil return opening；Electrohydraulic servo valve oil-in therein carrys out oil pipe line by hydraulic lock with brake system pressure source and couples；Institute
The electrohydraulic servo valve brake mouth stated couples with little brake gear oil-in and the big brake gear in-line of wheel, specifically will
Brake mouth connecting pipeline is divided into little brake gear fluid pressure line and big brake gear fluid pressure line, and makes little brake gear therein
Fluid pressure line directly couples with the little brake gear oil-in pipeline of wheel so that it is in big brake gear fluid pressure line through electromagnetism
Valve couples with the big brake gear oil-in pipeline of wheel；The oil-out of described electromagnetic valve and the big brake gear oil-in of wheel
Pipeline couples；Described electrohydraulic servo valve oil return opening couples with aircraft return line.
4. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that velocity pick-up
Device is arranged on plane axletree, or on wheel braking housing, is coupled with wheel by mechanically operated mode, experiences wheel and rotates
Speed, is converted to signal of telecommunication output by wheel rotary speed.
5. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that hydraulic selector
It is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth；The electric interfaces of hydraulic selector passes through shielding insulation wire and electromagnetic valve
Electric interfaces electrically couple, specifically the microswitch of this hydraulic selector is connected with the electromagnet coil of electromagnetic valve, connect
Or disconnect the control current signal of the electromagnet coil being supplied to electromagnetic valve；The hydraulic interface of hydraulic selector and electrohydraulic servo valve
Brake mouth pipeline couples.
6. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that electromagnetic valve is pacified
Be contained in electrohydraulic servo valve brake mouth output big brake gear fluid pressure line on, by hydraulic control so that become electric control realize
Oil-feed oil circuit and the communication of fuel-displaced oil circuit and disconnection, thus control whether place fluid pressure line exports and disconnect brake pressure；Institute
The electric interfaces stating electromagnetic valve is electrically coupled with the electric interfaces of hydraulic selector by shielding insulation wire, specifically, and electromagnetic valve
Electromagnet coil connect with the microswitch of hydraulic selector, then be connected on power supply, the fine motion receiving hydraulic selector is opened
Control current signal is sent after closing Guan Bi；
The hydraulic interface of described electromagnetic valve is electromagnetic valve oil-in, electromagnetic valve oil-out and electromagnetic valve oil return mouth respectively；Wherein: electricity
Magnet valve oil-in is connected in parallel on little brake gear fluid pressure line by pipeline, thus connects with the brake mouth of electrohydraulic servo valve；Electricity
Magnet valve oil-out is coupled by big brake gear fluid pressure line with described big brake gear oil-in；Electromagnetic valve oil return mouth and aircraft
Return line couples；
The brake pressure setting value of described control hydraulic selector is 40～65% normal braking pressure.
7. aircraft single-wheel double-brake optional Flight By Wire brake system as claimed in claim 1, it is characterised in that described control
The input of the electric interfaces of box passes through cable connection with velocity sensor and brake instruction transducer respectively, receives speed respectively
The brake instruction voltage signal that the wheel speed of sensor offer and brake instruction transducer are sent；Control the electric interfaces of box
Outfan, with electrohydraulic servo valve cable connection, sends control signal to electrohydraulic servo valve；Control box to be supplied by aircraft power system
Electricity.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610436221.2A CN106081073B (en) | 2016-06-17 | 2016-06-17 | A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610436221.2A CN106081073B (en) | 2016-06-17 | 2016-06-17 | A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake |
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| Publication Number | Publication Date |
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| CN106081073A true CN106081073A (en) | 2016-11-09 |
| CN106081073B CN106081073B (en) | 2018-03-02 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610436221.2A Expired - Fee Related CN106081073B (en) | 2016-06-17 | 2016-06-17 | A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100241A (en) * | 2017-12-06 | 2018-06-01 | 西安航空制动科技有限公司 | It can self-stopping aircraft brake-by-wire system and brake method |
| CN108146622A (en) * | 2017-12-06 | 2018-06-12 | 西安航空制动科技有限公司 | The aircraft brake-by-wire system and brake method switched using self-actuating brake |
| CN110514343A (en) * | 2019-09-02 | 2019-11-29 | 西安航空制动科技有限公司 | A kind of brake instruction transducer and its design method |
| CN110525405A (en) * | 2019-09-09 | 2019-12-03 | 西安航空制动科技有限公司 | The brake system and design method of hydraulic power source are controlled by brake instruction transducer |
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| GB2349676A (en) * | 1999-05-05 | 2000-11-08 | Lucas Ind Plc | Back-up braking in electro-hydraulic (ehb) braking systems |
| JP2004291769A (en) * | 2003-03-26 | 2004-10-21 | Advics:Kk | Hydraulic brake device for vehicle |
| CN202106959U (en) * | 2011-04-18 | 2012-01-11 | 中南大学 | Anti-slip brake control system of an airplane |
| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2349676A (en) * | 1999-05-05 | 2000-11-08 | Lucas Ind Plc | Back-up braking in electro-hydraulic (ehb) braking systems |
| JP2004291769A (en) * | 2003-03-26 | 2004-10-21 | Advics:Kk | Hydraulic brake device for vehicle |
| CN202106959U (en) * | 2011-04-18 | 2012-01-11 | 中南大学 | Anti-slip brake control system of an airplane |
| 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 (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100241A (en) * | 2017-12-06 | 2018-06-01 | 西安航空制动科技有限公司 | It can self-stopping aircraft brake-by-wire system and brake method |
| CN108146622A (en) * | 2017-12-06 | 2018-06-12 | 西安航空制动科技有限公司 | The aircraft brake-by-wire system and brake method switched using self-actuating brake |
| CN110514343A (en) * | 2019-09-02 | 2019-11-29 | 西安航空制动科技有限公司 | A kind of brake instruction transducer and its design method |
| CN110525405A (en) * | 2019-09-09 | 2019-12-03 | 西安航空制动科技有限公司 | The brake system and design method of hydraulic power source are controlled by brake instruction transducer |
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|---|---|
| CN106081073B (en) | 2018-03-02 |
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