CN105905281A - Airplane wheel fly-by-wire operation brake system capable of selecting braking modes - Google Patents
Airplane wheel fly-by-wire operation brake system capable of selecting braking modes Download PDFInfo
- Publication number
- CN105905281A CN105905281A CN201610436553.0A CN201610436553A CN105905281A CN 105905281 A CN105905281 A CN 105905281A CN 201610436553 A CN201610436553 A CN 201610436553A CN 105905281 A CN105905281 A CN 105905281A
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- China
- Prior art keywords
- brake
- wheel
- oil
- electromagnetic valve
- electrohydraulic servo
- Prior art date
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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
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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
- 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
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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
- 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
Abstract
An airplane wheel fly-by-wire operation brake system capable of selecting brake modes comprises a brake instruction sensor, a control box, an electro-hydraulic servo valve, an electromagnetic valve, an airplane wheel speed sensor and a pressure sensor. The airplane wheel speed sensor, the control box and the electro-hydraulic servo valve form a brake anti-slip control part. The control box and the electromagnetic valve conducts oil path opening and closing through a brake pressure control method to control an airplane to be partly braked through a small brake device or achieve complete brake through a large brake device. The brake pressure value is set to be 40-65% of normal brake pressure. The system is suitable for a single-wheel double-brake airplane wheel with a carbon brake, can meet the requirement that the single-wheel double-brake airplane wheel selects and uses the brake so that the use state of a carbon disc can be adjusted, the good characteristic of abrasion resistance of a carbon-carbon composite friction material is given full play to, the problems that an existing single-wheel single-brake carbon brake disc is large in abrasion and short in service life are effectively solved, the service life of the carbon disc is prolonged, and economic benefits of the carbon disc are improved.
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 reliable
Property safety maintainability economy, thus be used widely on present generation aircraft.Carbon brake is particularly suitable for high-energy
Brake condition, excellent friction and wear characteristic, give the long-lived quality of carbon brake disc.But, carbon brake puts into
Outfield finds after running, and carbon brake disc does not reaches the life value that design is given service life, and have is only value projected life
About 60%.Causing the main cause that carbon dish service life is short, present analysis is considered carbon-to-carbon composite friction material pair
Sliding brake bad adaptability, aircraft wear extent under ground taxi braking state is big.If by existing brake machine wheel
Brake gear uses the structure design of " being divided into two ", i.e. single-wheel is equipped with small one and large one two brake gears or dual brake
Car, slides brake for aircraft floor when little brake is used alone, and that improves carbon dish when sliding brake can carry level, from
And reduce and slide carbon mill damage in brake, improve the service life improving carbon dish, 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 liquid
Pressure brake system, mainly includes water brake valve, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box；Right
In brake-by-wire system, mainly include brake instruction transducer, Electric hydraulic pressure servo valve, wheel spin-up transducer, control
Box processed, compared with conventional hydraulic brake system, brake instruction transducer instead of water brake valve, additionally, electro-hydraulic
Pressure servo valve is postiive gain valve.Airplane wheel brake system controls the single braking machine on a wheel with a brake
Wheel, or with the double-brake wheels of two brakes, such as hose type double-brake wheel, double-brake wheel on a wheel
The operation of two brakes is carried out simultaneously.Select to use the requirement of brake, existing airplane wheel according to single-wheel double-brake
Brake system does not have this ability.
Summary of the invention
For the deficiency overcoming two brake gears present in prior art to run simultaneously, the present invention proposes one
The airplane wheel Flight By Wire brake system of brake modes can be selected.
The present invention include brake instruction transducer, control box, electrohydraulic servo valve, electromagnetic valve, wheel spin-up transducer and
Pressure transducer.Described wheel spin-up transducer, control box and electrohydraulic servo valve constitute brake anti-sliding control part；Control
Box processed and electromagnetic valve carry out oil circuit by the method that brake pressure controls and open and close the part brake or whole of control realization aircraft
Brake.The brake of described part realizes by running little brake gear；Described whole brake is by running little brake dress simultaneously
Put and realize with big brake gear.Described brake pressure setting value is 40～65% normal braking pressure.
Described brake instruction transducer is arranged on below cockpit floor；Described electromagnetic valve is located at electrohydraulic servo valve brake
On the big brake gear hydraulic tube of mouth output；Pressure transducer is arranged on the fluid pressure line of described electrohydraulic servo valve brake mouth
On；The oil-in of electrohydraulic servo valve is oily with brake system pressure source to be coupled by pipeline, and electrohydraulic servo valve brake mouth divides
Not with the little brake gear oil-in of wheel and big brake gear oil-in by being coupled by pipeline, electrohydraulic servo valve
Input couples with the outfan controlling box electric interfaces.
Described brake instruction transducer is arranged on below cockpit floor；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, stopping for wheel
Car.
Described electrohydraulic servo valve has an electrical outlets and three hydraulic interfaces.Described electrical outlets is by the electricity of band plug
Cable is implemented electrically to couple with controlling box, receives and controls the brake anti-sliding control current signal that box 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.Therein electro-hydraulic
Servo valve oil-in carrys out oil pipe line by hydraulic lock with brake system pressure source and couples, and described electrohydraulic servo valve brake mouth divides
Not coupled by pipeline with little brake gear oil-in and the big brake gear oil-in of wheel, described electrohydraulic servo valve is stopped
Car mouth is coupled by pipeline with little brake gear oil-in and the big brake gear oil-in of wheel respectively, during connection, and will
Brake mouth connecting pipeline is divided into little brake gear fluid pressure line and big brake gear fluid pressure line, by described little brake gear
Fluid pressure line directly couples with the little brake gear oil-in of wheel, by direct for described big brake gear fluid pressure line and machine
The big brake gear oil-in of wheel couples.Described big brake gear fluid pressure line is in series with electromagnetic valve, specifically will
The electromagnetic valve oil-in of described electromagnetic valve is connected with little brake gear fluid pressure line, so that this electromagnetic valve enters by pipeline
Hydraulic fluid port connects with the brake mouth of electrohydraulic servo valve；Big brake gear oil-in by the electromagnetic valve hydraulic fluid port of electromagnetic valve Yu wheel
Coupled by pipeline.Described electrohydraulic servo valve oil return opening couples with aircraft return line.
Described electromagnetic valve has an electric interfaces and three hydraulic interfaces.Described three hydraulic interfaces are that electromagnetic valve enters respectively
Hydraulic fluid port, electromagnetic valve oil-out and electromagnetic valve oil return mouth.Electromagnetic valve oil-in therein and the brake mouth pipe of electrohydraulic servo valve
Road couple, electromagnetic valve oil-out couples with the big brake gear oil-feed interface pipeline of brake machine wheel, electromagnetic valve oil return mouth and
Aircraft return line couples.The electric interfaces of electromagnetic valve is by shielding insulation wire and control box electric interfaces outfan electricity
Gas couples.
Velocity sensor is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode and wheel
Couple, experience wheel rotary speed, and wheel rotary speed is converted to signal of telecommunication output.Velocity sensor electric
Interface is electrically coupled with controlling box by cable, is supplied to the wheel rotary speed voltage signal detected control box,
The sliding mode of monitoring wheel.
, the input of the electric interfaces controlling box passes through cable connection with velocity sensor and brake instruction transducer respectively,
The brake instruction voltage letter that the wheel rate signal provided to receive velocity sensor is sent with reception brake instruction transducer
Number.Control outfan and the electrohydraulic servo valve cable connection of the electric interfaces of box, send control letter to electrohydraulic servo valve
Number.Control box to be powered by aircraft power system.
Pressure transducer is arranged on the fluid pressure line of described electrohydraulic servo valve brake mouth.Described pressure transducer has one
Electric interfaces and a hydraulic interface；The electric interfaces of described pressure transducer is by shielding insulation wire and control box electricity
Gas interface input electrically couples, the water brake pressure of electrohydraulic servo valve brake mouth output in time controlling box input brake；
The hydraulic interface of described pressure transducer couples with the fluid pressure line of electrohydraulic servo valve brake mouth.
For adapting to the needs of main landing gear single-wheel double-brake wheel structure choice brake, overcome present in prior art not
Foot, the present invention uses the way of " being divided into two ", i.e. brake system exports to wheel brake hydraulic tube
Road is divided into two, and a fluid pressure line leads directly to a little brake gear, and this fluid pressure line keeps unimpeded；Another liquid
Pressure pipe road arranges control device, then leads to another big brake gear, and 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, the function that the whole brake gear of other situations runs, to reach
Slide in brake carbon mill to reduction to damage, improve the purpose improving carbon dish service life.
Selectively brake by electromagnetic valve and control box composition control device, using brake pressure control methods to carry out oil circuit keying
Control realization；When the brake pressure corresponding to the brake instruction of brake instruction transducer output 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 liquid
Pressure exports；Otherwise, controlling box and send control signal to electromagnetic valve or electric energy is provided, electromagnetic valve obtains for electrically activating
Being in opening, the fluid pressure line that electromagnetic valve controls is open-minded, and electromagnetic valve has hydraulic coupling to export.
In the present invention, wheel velocity measuring is completed by wheel spin-up transducer, the sliding mode of monitoring wheel；Anti-slip control
Make and completed by control box；Electro-hydraulic servo response valve controls the control current signal of box, exports and brake machine wheel is transported in regulation
Brake pressure；Brake is selected to be carried out by electromagnetic valve and control box composition control device.
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；Electricity
Hydraulic servo 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, electro-hydraulic servo
The brake pressure of valve output is the biggest, it is achieved that the Stress control of postiive gain；
Control box and there is the brake function such as anti-sliding control, fault detect.Control the input of the electric interfaces of box, with speed
Degree sensor-use cable couples, and receives the wheel speed that velocity sensor provides；Control the input of the electric interfaces of box,
Also with brake instruction transducer cable connection, receive the brake instruction voltage signal that brake instruction transducer is sent；Control
The outfan of the electric interfaces of box processed, with electrohydraulic servo valve cable connection, sends control signal to electrohydraulic servo valve；
Control box to be powered by aircraft power system.
Electromagnetic valve is arranged on another fluid pressure line of electrohydraulic servo valve brake mouth output, passes through brake instruction transducer
The corresponding relation of the water brake pressure that the brake instruction voltage signal sent exports with electrohydraulic servo valve, by controlling box root
Judge that brake pressure size controls switching on and off of electromagnetic valve according to brake instruction voltage signal size, thus control electricity
Whether magnet valve place fluid pressure line exports and disconnects brake pressure.The electric interfaces of electromagnetic valve by shielding insulation wire with
Control box electric interfaces outfan electrically to couple；Receive and control the control current signal that box is sent；Control whether box is sent
Control current signal to electromagnetic valve, depend on brake instruction voltage signal or the electricity of correspondence that brake instruction transducer exports
The water brake pressure of hydraulic servo output；When brake instruction voltage signal or brake pressure are less than setting value, control
Box does not sends control current signal to electromagnetic valve, and electromagnetic valve is not energized and is off, and electromagnetic valve oil-out does not has
Output, oil-out and oil return opening is had to link up；When brake instruction voltage signal or brake pressure are 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 is closed, oil-in and
Oil-out is linked up, and the fluid pressure line that electromagnetic valve controls is open-minded.
In the present invention, Article 1 brake passage i.e. fluid pressure line is unblocked, it is ensured that can be used at any time braking, Article 2
Brake passage i.e. fluid pressure line is with good conditionsi open-minded.So, described brake system can ensure when aircraft floor slides brake
Only use little brake gear, use two brake gears in the case of other, it is achieved the double-brake to aircraft simultaneously.
Brake process skids if there is wheel, is constituted by controlling box, electrohydraulic servo valve and wheel spin-up transducer
Brake anti-sliding control part implement control.
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 gear or a brake gear operation rather than all brake gears are the most all running, and improve and slide brake
Time carbon dish the level that can carry, thus avoid carbon-to-carbon composite friction material brake disc low speed mental retardation brake wear extent excessive
Short slab, carbon dish wear extent when making to slide brake reduces, and reaches to improve or improve the purpose in carbon dish service life.Pass through
This wheel and system design, have adjusted the use state of carbon dish, make the anti abrasive excellent spy of carbon-to-carbon composite friction material
Property given full play of, efficiently solve the difficulty that the brake carbon brake disc abrasion of existing single-wheel list is big, service life is short
Topic, improves service life and the economic benefit of carbon dish.
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. electricity
Magnet valve；The least brake gear fluid pressure line；8. big brake gear fluid pressure line；The least brake gear oil-feed interface；10.
Big brake gear oil-feed interface.
Detailed description of the invention
See accompanying drawing 1.Main landing gear is equipped with a brake machine wheel, with two brake gears, referred to as single-wheel double-brake
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 axial dimension is big, therefore the biggest brake gear.Described little brake gear and big brake gear are all disclosed in Shen
Please number be in the innovation and creation of 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 list
Disc type or double plate brake；Compression plate therein is adjacent with described cylinder block, a card of bearing disc be positioned at brake
One end surfaces laminating of the housing bearing disc on housing, Moving plate is between described compression plate and bearing disc.Described little
Brake for ground taxi when brake is individually handled.
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 be 3～5 dishes, for multiple-disc brake device；Described compression plate is adjacent with cylinder block, a card of bearing disc
An end surfaces laminating with the housing bearing disc being positioned in brake shell；Multiple Moving plates and multiple quiet dish are with Moving plate-quiet
The interleaved mode of dish-Moving plate-quiet dish is arranged between described compression plate and bearing disc.
The present embodiment is the aircraft single-wheel double-brake selectively brake system of a kind of Flight By Wire, passes including brake instruction
Sensor 1, control box 3, electrohydraulic servo valve 2, electromagnetic valve 6 and wheel spin-up transducer 4.Described wheel velocity pick-up
Device 4, control box 3 and electrohydraulic servo valve 2 constitute brake anti-sliding control part；Control box 3 and electromagnetic valve 6 for real
Now part is braked or all brakes.The brake of described part realizes by running little brake gear；Described whole brake is passed through
Run little brake gear simultaneously and big brake gear realizes.Compared with conventional hydraulic brake system, in the present embodiment,
Brake instruction transducer 1 instead of water brake valve, and uses the electrohydraulic servo valve 2 of postiive gain.Brake instruction senses
Device 1 and control box 3, electrohydraulic servo valve 2 constitute brake and control part；Electrohydraulic servo valve 2 and control box 3 both completed
Brake control task, completes again anti-sliding control task.
Select the pattern of brake by the control device being made up of electromagnetic valve 6 and control box 3, use brake pressure to control
Method carry out oil circuit open and close control realization: when brake instruction transducer 1 output brake instruction corresponding to brake pressure
When power is less than setting value, control box 3 controls electric current to electromagnetic valve 6 output, and electromagnetic valve 6 is not powered and is in and cuts
Stopping or closed mode, electromagnetic valve 6 does not has hydraulic coupling to export；Otherwise, control box 3 and send control signal to electromagnetic valve 6
Or offer electric energy, electromagnetic valve 6 obtains for electrically activating and being in opening, and the fluid pressure line that electromagnetic valve 6 controls is open-minded,
Electromagnetic valve 6 has hydraulic coupling to export.
Described brake pressure setting value is 40～65% normal braking pressure；
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 completes.Electrohydraulic servo valve 2 response controls the control current signal of box 3, exports and brake machine wheel 5 is transported in regulation
Brake pressure.Brake is selected to be carried out by electromagnetic valve 6 and control box 3 composition control device；
Described brake instruction transducer 1 is arranged on below cockpit floor, driver handle it, controls output institute
The brake instruction voltage signal needed, then controlled electrohydraulic servo valve 2 export required water brake pressure by controlling box 3.
The electric interfaces of described brake instruction transducer 1 is electrically coupled with controlling box 3 by cable, the brake of driver is referred to
Voltage signal is made to be supplied to control 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
Individual hydraulic interface is electrohydraulic servo valve oil-in, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening respectively.Wherein
Electrohydraulic servo valve oil-in carry out oil pipe line with brake system pressure source and couple, specifically by this electrohydraulic servo valve oil-in
Couple with the oil-out of hydraulic lock, carry out oil pipe line by hydraulic lock with brake system pressure source and couple；Described electro-hydraulic servo
Valve brake mouth is coupled by pipeline with little brake gear oil-in and the big brake gear oil-in of wheel respectively, during connection,
Brake mouth connecting pipeline is divided into little brake gear fluid pressure line 7 and big brake gear fluid pressure line 8, little stops described
Car device fluid pressure line 7 directly couples with the little brake gear oil-in 9 of wheel, by described big brake gear hydraulic tube
Road 8 directly couples with the big brake gear oil-in B of wheel.Described big brake gear fluid pressure line 8 is in series with
Electromagnetic valve 6, specifically by the electromagnetic valve oil-in of described electromagnetic valve 6 by pipeline and little brake gear fluid pressure line 7
Connection, so that this electromagnetic valve oil-in connects with the brake mouth of electrohydraulic servo valve 2；By the electromagnetism valve oil of electromagnetic valve 6
Mouth is coupled by pipeline with the big brake gear oil-in B of wheel.Described electrohydraulic servo valve oil return opening and aircraft oil return pipe
Road couples.When electrohydraulic servo valve 2 is not when controlling electric current, electrohydraulic servo valve oil-in is closed, and electrohydraulic servo valve returns
Hydraulic fluid port and electrohydraulic servo valve brake mouth oil circuit couple unimpeded；Electrohydraulic servo valve 2 have control electric current time, electrohydraulic servo valve
Oil return opening is closed, and oil-in opens, with electrohydraulic servo valve brake mouth oil circuit UNICOM, the brake mouth output of this electrohydraulic servo valve
The corresponding water brake pressure controlling electric current.Controlling box 3, to input the control electric current of electrohydraulic servo valve 2 the biggest, electro-hydraulic watches
The brake pressure taking valve 2 output is the biggest, it is achieved that the Stress control of postiive gain.
Described electromagnetic valve 6 be located at electrohydraulic servo valve 2 brake mouth output big brake gear hydraulic tube 8 on, by stopping
The brake instruction voltage signal that car instruction sensor 1 sends is corresponding with the water brake pressure that electrohydraulic servo valve 2 exports
According to brake instruction voltage signal size, relation, is judged that brake pressure size controls connecing of electromagnetic valve 6 by controlling box 3
On and off is opened, thus controls whether electromagnetic valve 6 place fluid pressure line exports and disconnect brake pressure.Described electromagnetic valve 6
There are an electric interfaces and three hydraulic interfaces.Described three hydraulic interfaces are that electromagnetic valve oil-in, electromagnetic valve go out respectively
Hydraulic fluid port and electromagnetic valve oil return mouth.Electromagnetic valve oil-in therein couples with the brake mouth pipeline of electrohydraulic servo valve 2, electromagnetism
Valve oil-out couples with big brake gear oil-feed interface 10 pipeline of brake machine wheel 5, electromagnetic valve oil return mouth and aircraft oil return
Pipeline couples.The electric interfaces of electromagnetic valve 6 is electrically joined with controlling box 3 electric interfaces outfan by shielding insulation wire
Connect；Receive and control the control current signal that box 3 is sent；Control box 3 whether send control current signal to electromagnetic valve 6,
Depend on the hydraulic pressure of electrohydraulic servo valve 2 output of brake instruction voltage signal that brake instruction transducer 1 exports or correspondence
Brake pressure；When brake pressure is less than setting value, controls box 3 and do not send control current signal to electromagnetic valve 6, electricity
Magnet 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 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 leads to
Electric-opening, the closedown of electromagnetic valve 6 oil return opening, oil-in and oil-out communication, the fluid pressure line that electromagnetic valve 6 controls is open-minded；
Described brake instruction voltage signal setting value is 40～65% normal braking command voltage signal, or brake pressure sets
Definite value is 40～65% normal braking pressure；The present embodiment brake instruction voltage signal setting value is 55% normal braking instruction
Voltage signal, or brake pressure setting value is 55% normal braking pressure.
Velocity sensor 4 is arranged on plane axletree, or on wheel braking housing, by mechanically operated mode and machine
Wheel couples, and experiences wheel rotary speed, and wheel rotary speed is converted to signal of telecommunication output.The speed of the present embodiment
Sensor 4 is arranged on plane axletree, brake machine wheel 5 hub drive pin be rotated；Velocity sensor 4 has one
Individual electric interfaces, is electrically coupled with controlling box 3 by cable, is provided by the wheel rotary speed voltage signal detected
Give and control box 3, the sliding mode of monitoring wheel.
Control box 3 and there is the brake function such as anti-sliding control, fault detect；The input of the electric interfaces controlling box 3 divides
Not with velocity sensor 4 and brake instruction transducer 1 by cable connection, to receive the machine of velocity sensor 4 offer
The brake instruction voltage signal that wheel speed signal and reception brake instruction transducer 1 are sent.Control the electric interfaces of box 3
Outfan and electrohydraulic servo valve 2 cable connection, send control signal to electrohydraulic servo valve 2.Control box 3 by flying
Electromechanical source system power supply.
Pressure transducer 7 is arranged on the fluid pressure line of described electrohydraulic servo valve brake mouth, experiences brake pressure, and will
Brake pressure is changed into the signal of telecommunication and is supplied to control box 3, with control the turning on or off of electromagnetic valve 6.Described pressure
Sensor 7 has an electric interfaces and a hydraulic interface；Electric interfaces is by shielding insulation wire and control box 3 electricity
Gas interface input electrically couples, to control box 3 input brake time electrohydraulic servo valve 2 brake mouth output water brake
Pressure；Brake with electrohydraulic servo valve 2 fluid pressure line of mouth of the hydraulic interface of pressure transducer 7 couples.
In the present embodiment, little brake gear fluid pressure line 7 is unblocked, it is ensured that can be used in brake at any time；Big brake
Device fluid pressure line 8 is with good conditionsi open-minded, i.e. when described brake system when ensureing that aircraft floor slides brake only with little
Brake gear, in the case of other, described little brake gear and big brake gear use simultaneously, it is achieved 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
The brake anti-sliding control part constituted is implemented to control.Anti-sliding control is realized by prior art.
Claims (7)
1. can select an airplane wheel Flight By Wire brake system for brake modes, the main landing gear of aircraft is stopped equipped with one
Car wheel, this brake machine wheel has two brake gears, it is characterised in that the brake of described airplane wheel Flight By Wire is
System includes brake instruction transducer, controls box, electrohydraulic servo valve, electromagnetic valve, wheel spin-up transducer and pressure biography
Sensor；Described wheel spin-up transducer, control box and electrohydraulic servo valve constitute brake anti-sliding control part；Control box
Carry out oil circuit with electromagnetic valve by the method that brake pressure controls and open and close the part brake or whole of control realization aircraft
Brake；The brake of described part realizes by running little brake gear；Described whole brake is by running little brake simultaneously
Device and big brake gear realize；Described brake pressure setting value is 40～65% normal braking pressure；
Described brake instruction transducer is arranged on below cockpit floor；Described electromagnetic valve is located at electrohydraulic servo valve brake mouth
On the big brake gear hydraulic tube of output；Pressure transducer is arranged on the fluid pressure line of described electrohydraulic servo valve brake mouth
On；The oil-in of electrohydraulic servo valve is oily with brake system pressure source to be coupled by pipeline, electrohydraulic servo valve brake mouth
Respectively with the little brake gear oil-in of wheel and big brake gear oil-in by being coupled by pipeline, electro-hydraulic servo
The input of valve couples with the outfan controlling box electric interfaces.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
Described brake instruction transducer is arranged on below cockpit floor；The electric interfaces of this brake instruction transducer is by electricity
Cable electrically couples with controlling box, is supplied to the brake instruction voltage signal of driver control box, stopping for wheel
Car.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
Described electrohydraulic servo valve has an electrical outlets and three hydraulic interfaces；Described electrical outlets passes through connectorized cable
Implement electrically to couple with controlling box, receive and control the brake anti-sliding control current signal that box 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；Electricity therein
Hydraulic servo oil-in carrys out oil pipe line by hydraulic lock with brake system pressure source and couples, and described electrohydraulic servo valve brakes
Mouthful coupled by pipeline with little brake gear oil-in and the big brake gear oil-in of wheel respectively, described electro-hydraulic watch
Take valve brake mouth to be coupled by pipeline with little brake gear oil-in and the big brake gear oil-in of wheel respectively, connection
When connecing, brake mouth connecting pipeline is divided into little brake gear fluid pressure line and big brake gear fluid pressure line, by described
Little brake gear fluid pressure line directly couples with the little brake gear oil-in of wheel, by described big brake gear hydraulic pressure
Pipeline directly couples with the big brake gear oil-in of wheel；Described big brake gear fluid pressure line is in series with electricity
Magnet valve, is specifically connected the electromagnetic valve oil-in of described electromagnetic valve with little brake gear fluid pressure line by pipeline,
So that this electromagnetic valve oil-in connects with the brake mouth of electrohydraulic servo valve；By electromagnetic valve hydraulic fluid port and the wheel of electromagnetic valve
Big brake gear oil-in coupled by pipeline；Described electrohydraulic servo valve oil return opening couples with aircraft return line.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
Described electromagnetic valve has an electric interfaces and three hydraulic interfaces；Described three hydraulic interfaces are electromagnetic valve oil-feed respectively
Mouth, electromagnetic valve oil-out and electromagnetic valve oil return mouth；Electromagnetic valve oil-in therein and the brake mouth pipe of electrohydraulic servo valve
Road couples, and electromagnetic valve oil-out couples with the big brake gear oil-feed interface pipeline of brake machine wheel, electromagnetic valve oil return mouth
Couple with aircraft return line；The electric interfaces of electromagnetic valve is exported with controlling box electric interfaces by shielding insulation wire
End electrically couples.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
Velocity sensor is arranged on plane axletree, or on wheel braking housing, is joined with wheel by mechanically operated mode
Connect, experience wheel rotary speed, and wheel rotary speed is converted to signal of telecommunication output；Velocity sensor electric
Interface is electrically coupled with controlling box by cable, is supplied to the wheel rotary speed voltage signal detected control
Box, the sliding mode of monitoring wheel.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
The input of the electric interfaces controlling box passes through cable connection with velocity sensor and brake instruction transducer respectively, with
The brake instruction voltage that the wheel rate signal that receiving velocity sensor provides is sent with reception brake instruction transducer
Signal；Control outfan and the electrohydraulic servo valve cable connection of the electric interfaces of box, send control to electrohydraulic servo valve
Signal processed；Control box to be powered by aircraft power system.
The airplane wheel Flight By Wire brake system of brake modes can be selected the most as claimed in claim 1, it is characterised in that
Pressure transducer is arranged on the fluid pressure line of described electrohydraulic servo valve brake mouth；Described pressure transducer has an electricity
Gas interface and a hydraulic interface；The electric interfaces of described pressure transducer is by shielding insulation wire and control box electricity
Gas interface input electrically couples, the water brake pressure of electrohydraulic servo valve brake mouth output in time controlling box input brake
Power；The hydraulic interface of described pressure transducer couples with the fluid pressure line of electrohydraulic servo valve brake mouth.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610436553.0A CN105905281B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel Flight By Wire brake system of brake modes can be selected |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610436553.0A CN105905281B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel Flight By Wire brake system of brake modes can be selected |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105905281A true CN105905281A (en) | 2016-08-31 |
| CN105905281B CN105905281B (en) | 2017-12-12 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610436553.0A Expired - Fee Related CN105905281B (en) | 2016-06-17 | 2016-06-17 | The airplane wheel Flight By Wire brake system of brake modes can be selected |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105905281B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319096A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
| CN109319095A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Enhance the aircraft brake-by-wire system and control method of take-off line braking ability |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2688789B2 (en) * | 1990-11-28 | 1997-12-10 | 住友精密工業株式会社 | Solenoid drive type automatic brake controller |
| CN103158867A (en) * | 2013-03-06 | 2013-06-19 | 西安航空制动科技有限公司 | Airplane electrical signal transmission brake antiskid control system |
| CN104787310A (en) * | 2015-04-01 | 2015-07-22 | 西安航空制动科技有限公司 | Normal brake system used for airplane and having take-off line brake capability |
| US20150225075A1 (en) * | 2014-02-10 | 2015-08-13 | Airbus Operations (Sas) | Aircraft comprising a landing gear having one wheel provided with an electric motor and control system for said electric motor |
-
2016
- 2016-06-17 CN CN201610436553.0A patent/CN105905281B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2688789B2 (en) * | 1990-11-28 | 1997-12-10 | 住友精密工業株式会社 | Solenoid drive type automatic brake controller |
| CN103158867A (en) * | 2013-03-06 | 2013-06-19 | 西安航空制动科技有限公司 | Airplane electrical signal transmission brake antiskid control system |
| US20150225075A1 (en) * | 2014-02-10 | 2015-08-13 | Airbus Operations (Sas) | Aircraft comprising a landing gear having one wheel provided with an electric motor and control system for said electric motor |
| CN104787310A (en) * | 2015-04-01 | 2015-07-22 | 西安航空制动科技有限公司 | Normal brake system used for airplane and having take-off line brake capability |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319096A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
| CN109319095A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | Enhance the aircraft brake-by-wire system and control method of take-off line braking ability |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105905281B (en) | 2017-12-12 |
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