CN105905281B - The airplane wheel Flight By Wire brake system of brake modes can be selected - Google Patents
The airplane wheel Flight By Wire brake system of brake modes can be selected Download PDFInfo
- Publication number
- CN105905281B CN105905281B CN201610436553.0A CN201610436553A CN105905281B CN 105905281 B CN105905281 B CN 105905281B CN 201610436553 A CN201610436553 A CN 201610436553A CN 105905281 B CN105905281 B CN 105905281B
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- Prior art keywords
- brake
- wheel
- control box
- electrohydraulic servo
- servo valve
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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
- 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 airplane wheel Flight By Wire brake system that can select brake modes, including brake instruction transducer, control box, electrohydraulic servo valve, magnetic valve, wheel spin-up transducer and pressure sensor.Wheel spin-up transducer, control box and electrohydraulic servo valve form brake anti-sliding control part；The method that control box and magnetic valve are controlled by brake pressure carries out oil circuit keying control aircraft and braked by small brake gear part, or passes through big brake gear and realize all brakes.Brake pressure setting value is 40~65% normal braking pressure.The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, requirement of the single-wheel double-brake selection using brake can be met, to adjust the use state of carbon disk, the anti abrasive good characteristic of carbon carbon composite friction material is set to give full play of, the problem that existing single-wheel list brake carbon brake disc abrasion is big, service life is short is efficiently solved, improves the service life and economic benefit of carbon disk.
Description
Technical field
The present invention relates to a kind of airplane wheel brake system, especially, it is related to a kind of aircraft single-wheel double-brake and has and be based on
Brake pressure selects to slide the brake control system of brake.
Background technology
Aircraft carbon brake for steel brake, has weight because brake disc is manufactured using carbon-to-carbon composite friction material completely
The advantages that light, wear-resistant, specific heat is high, high temperature is not bonded is measured, significantly improves aircraft utilization technical performance and reliance security
Property maintainability economy, thus be used widely on present generation aircraft.Carbon brakes particularly suitable for high-energy brake condition, excellent
Good friction and wear characteristic, assign the long-lived quality of carbon brake disc.However, found after carbon brake input outfield operation, carbon
Brake disc service life does not reach the given life value of design, and some is only 60% or so of projected life value.Carbon disk is caused to make
The main reason for short life, present analysis are 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 brake gear of existing brake machine wheel is set using the structure of " being divided into two "
Meter, i.e. single-wheel are equipped with small one and large one two brake gears or double-brake, and small brake is slided when being used alone for aircraft floor
Brake, the energy load level of carbon disk when sliding brake is improved, carbon mill damage in brake is slided so as to reduce, improves and improve making for carbon disk
With the life-span, two brakes of other situations or double-brake use simultaneously as set of device.
Airplane wheel brake system is used for brake control and the anti-sliding control of airplane wheel, wide variety of on current aircraft
It is electronic anti-skid braking system.Airplane wheel brake system mainly includes manipulating, detect and controlling, for the water brake of routine
System, mainly include water brake valve, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box；For brake-by-wire system
System, mainly including brake instruction transducer, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box, stopped with the hydraulic pressure of routine
Car system is compared, and brake instruction transducer instead of water brake valve, in addition, Electric hydraulic pressure servo valve is postiive gain valve.Aircraft
Wheel brake system controls single brake machine wheel with a brake on a wheel, or braked on a wheel with two
Double-brake wheel, such as hose type double-brake wheel, the operation of two brakes of double-brake wheel is carried out simultaneously.According to single-wheel
Double-brake selection does not have this ability using the requirement braked, existing airplane wheel brake system.
The content of the invention
To overcome the shortcomings of that two brake gears present in prior art can only be run simultaneously, the present invention proposes one kind
The airplane wheel Flight By Wire brake system of brake modes can be selected.
The present invention includes brake instruction transducer, control box, electrohydraulic servo valve, magnetic valve, wheel spin-up transducer and pressure
Force snesor.The wheel spin-up transducer, control box and electrohydraulic servo valve form brake anti-sliding control part；Control box and electricity
The method that magnet valve is controlled by brake pressure carries out oil circuit and opens and closes part brake or all brakes that aircraft is realized in control.The portion
Brake is divided to be realized by running small brake gear；All brakes are real by running small brake gear and big brake gear simultaneously
It is existing.The brake pressure setting value is 40~65% normal braking pressure.
The brake instruction transducer is arranged on below cockpit floor；The magnetic valve is located to brake in electrohydraulic servo valve
On the big brake gear hydraulic tube of mouth output；Pressure sensor is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth；
The oil inlet of electrohydraulic servo valve is coupled with brake system pressure source coming oil by pipeline, electrohydraulic servo valve brake mouth respectively with wheel
Small brake gear oil inlet and big brake gear oil inlet by being coupled by pipeline, the input of electrohydraulic servo valve and control
The output end connection of box electric interfaces.
The brake instruction transducer is arranged on below cockpit floor；The electric interfaces of the brake instruction transducer pass through
Cable electrically couples with control box, the brake instruction voltage signal of driver is supplied into control box, the brake for wheel.
The electrohydraulic servo valve has an electrical outlets and three hydraulic interfaces.The electrical outlets pass through the electricity with plug
Cable is implemented electrically to couple with control box, receives the brake anti-sliding control current signal that control box is sent.Three hydraulic interfaces
It is electrohydraulic servo valve oil inlet, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening respectively.Electrohydraulic servo valve therein enters
Hydraulic fluid port is coupled by hydraulic lock with brake system pressure source come oil pipe line, and the electrohydraulic servo valve brake mouth is small with wheel respectively
Brake gear oil inlet and big brake gear oil inlet are coupled by pipeline, electrohydraulic servo valve brake mouth respectively with wheel
Small brake gear oil inlet and big brake gear oil inlet are coupled by pipeline, during connection, will brake mouth connecting pipeline be divided into it is small
Brake gear fluid pressure line and big brake gear fluid pressure line, by small brake of the small brake gear fluid pressure line directly with wheel
Car device oil inlet couples, and the big brake gear fluid pressure line is directly coupled with the big brake gear oil inlet of wheel.
Magnetic valve is in series with the big brake gear fluid pressure line, the magnetic valve oil inlet of the magnetic valve is specifically passed through into pipeline
Connected with small brake gear fluid pressure line, so that the magnetic valve oil inlet connects with the brake mouth of electrohydraulic servo valve；By electromagnetism
The magnetic valve hydraulic fluid port of valve is coupled with the big brake gear oil inlet of wheel by pipeline.The electrohydraulic servo valve oil return opening and aircraft
Return line couples.
The magnetic valve has an electric interfaces and three hydraulic interfaces.Three hydraulic interfaces are that magnetic valve enters respectively
Hydraulic fluid port, magnetic valve oil-out and electromagnetic valve oil return mouth.The brake mouth pipeline connection of magnetic valve oil inlet and electrohydraulic servo valve therein
Connect, magnetic valve oil-out couples with the big brake gear oil-feed interface pipeline of brake machine wheel, electromagnetic valve oil return mouth and aircraft oil return
Pipeline couples.The electric interfaces of magnetic valve are electrically coupled by shielding insulation wire with control box electric interfaces output end.
Velocity sensor is arranged on plane axletree, or on wheel braking housing, passes through mechanically operated mode and wheel
Connection, experiences wheel rotary speed, and wheel rotary speed is converted into electric signal output.The electric interfaces of velocity sensor lead to
Cross cable with control box electrically to couple, the wheel rotary speed voltage signal detected is supplied to control box, monitors wheel
Sliding mode.
, the input of the electric interfaces of control box joined with velocity sensor and brake instruction transducer by cable respectively
Connect, the brake instruction voltage sent with receiving the wheel rate signal of velocity sensor offer and reception brake instruction transducer is believed
Number.The output end of the electric interfaces of control box and electrohydraulic servo valve cable connection, control signal is sent to electrohydraulic servo valve.Control
Box processed is powered by aircraft power system.
Pressure sensor is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth.The pressure sensor has one
Electric interfaces and a hydraulic interface；The electric interfaces of the pressure sensor are electrically connect by shielding insulation wire with control box
Mouth input electrically couples, and the water brake pressure of electrohydraulic servo valve brake mouth output when braking is inputted to control box；The pressure
The hydraulic interface of force snesor couples with the fluid pressure line of electrohydraulic servo valve brake mouth.
To adapt to the needs of main landing gear single-wheel double-brake wheel structure choice brake, overcome present in prior art not
Foot, using the way of " being divided into two ", i.e., brake system exports is divided into the present invention to a fluid pressure line of wheel brake
Two, a fluid pressure line leads directly to a small brake gear, and this fluid pressure line keeps unimpeded；Another fluid pressure line sets control
Device processed, then lead to another big brake gear, the break-make of the fluid pressure line is controlled by control device.So as to realize aircraft floor
Only small brake gear operation is slided, the function of other situation whole brake gears operation, carbon disk in brake is slided to reach reduction
Abrasion, improve the purpose for improving carbon disk service life.
Selectively brake by magnetic valve and control box composition control device, oil circuit keying is carried out using brake pressure control methods
Control is realized；When the brake pressure corresponding to the brake instruction of brake instruction transducer output is less than setting value, control box is not
Magnetic valve output control electric current is given, magnetic valve is not powered and do not have hydraulic coupling output in cut-off or closed mode, magnetic valve；
Conversely, control box sends control signal to magnetic valve or provides electric energy, magnetic valve obtains power supply and starts and be in opening, electricity
The fluid pressure line of magnet valve control is open-minded, and magnetic valve has hydraulic coupling output.
In the present invention, wheel velocity measuring is completed by wheel spin-up transducer, monitors the sliding mode of wheel；Anti-sliding control
Completed by control box；The brake of brake machine wheel is transported in the control electric current signal of electrohydraulic servo valve response control box, output and regulation
Pressure；Selection brake is carried out by magnetic valve and control box composition control device.
Electrohydraulic servo valve when not having control electric current, close by oil inlet, and oil return opening and the oil circuit connection of brake mouth are unimpeded；It is electro-hydraulic
Servo valve when there is control electric current, closed by oil return opening, and oil inlet is opened, with brake mouth oil circuit UNICOM, the corresponding control of brake mouth output
The water brake pressure of electric current processed；The control electric current of control box input electrohydraulic servo valve is bigger, the brake of electrohydraulic servo valve output
Pressure is bigger, realizes the Stress control of postiive gain；
Control box has the functions such as brake anti-sliding control, fault detect.The input of the electric interfaces of control box, with speed
Sensor-use cable couples, and receives the wheel speed that velocity sensor provides；The input of the electric interfaces of control box, also with brake
Car instruction sensor cable connection, receive the brake instruction voltage signal that brake instruction transducer is sent；Control box it is electric
The output end of interface, with electrohydraulic servo valve cable connection, control signal is sent to electrohydraulic servo valve；Control box is by aircraft power supply
System power supply.
Magnetic valve is arranged on another fluid pressure line of electrohydraulic servo valve brake mouth output, passes through brake instruction transducer
The brake instruction voltage signal sent and the corresponding relation of the water brake pressure of electrohydraulic servo valve output, by control box according to brake
Car command voltage signal magnitude judges brake pressure size and controls switching on and off for magnetic valve, so as to control magnetic valve place
Whether fluid pressure line exports and disconnects brake pressure.The electric interfaces of magnetic valve are electrically connect by shielding insulation wire with control box
Mouth output end electrically couples；Receive the control electric current signal that control box is sent；Whether control box sends control electric current signal to electricity
Magnet valve, depending on the brake instruction voltage signal of brake instruction transducer output or the hydraulic pressure of corresponding electrohydraulic servo valve output are stopped
Car pressure；When brake instruction voltage signal or brake pressure are less than setting value, control box does not send control electric current to magnetic valve
Signal, magnetic valve are not powered and are off, and magnetic valve oil-out does not export, and oil-out and oil return opening are linked up；When
When brake instruction voltage signal or brake pressure are more than or equal to setting value, control box sends control electric current signal to magnetic valve, electricity
Magnet valve, which is powered, to be opened, and electromagnetic valve oil return mouth is closed, and oil inlet and oil-out are linked up, and the fluid pressure line of solenoid valve control is open-minded.
In the present invention, first brake passage is that fluid pressure line is unblocked, ensures to can be used for braking at any time, Article 2 is stopped
Vehicle passage is that fluid pressure line is conditional open-minded.So, the brake system can ensure when aircraft floor slides brake only with small
Brake gear, two brake gears are used simultaneously in the case of other, realize the double-brake to aircraft.
Skidded in brake process if there is wheel, by control box, electrohydraulic servo valve and wheel spin-up transducer are formed
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 that the selection of single-wheel double-brake uses brake
It is required that.Because the system has the ability for selecting to slide brake, so, when aircraft floor slides brake, only filled with small brake
Put or a brake gear is run, rather than all brake gears are all being run simultaneously, improve the energy of carbon disk when sliding brake
Level is carried, so as to avoid the excessive short slab of carbon-to-carbon composite friction material brake disc low speed low energy brake wear extent, makes to slide brake
Carbon mill damage amount during car reduces, and reaches the purpose for improving or improving carbon disk service life.By this wheel and system design,
The use state of carbon disk is have adjusted, the anti abrasive good characteristic of carbon-to-carbon composite friction material is given full play of, effectively
Solve the problem that existing single-wheel list brake carbon brake disc abrasion is big, service life is short, improve the service life and warp of carbon disk
Ji benefit.
Brief description of the drawings
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. small brake gear fluid pressure line；8. big brake gear fluid pressure line；9. small brake gear oil-feed interface；10. big brake dress
Put oil-feed interface.
Embodiment
Referring to accompanying drawing 1.Main landing gear is equipped with a brake machine wheel, with two brake gears, referred to as single-wheel dual brake vehicle device
Wheel.The brake disc of brake gear is manufactured using carbon-to-carbon composite friction material completely.
Described two brake gears are small brake gear and big brake gear respectively.The brake disc number of the small brake gear
It is less, make heat reservoir axial dimension small, therefore referred to as small brake gear；The brake disc number of the big brake gear is more, makes heat reservoir axle
It is big to size, therefore referred to as big brake gear.Described small brake gear and big brake gear are disclosed in Application No.
201610281025.2 innovation and creation in：
The heat reservoir of the small brake gear is made up of compression plate, bearing disc and Moving plate, and Moving plate quantity is 1~2 disk, is single-deck
Formula or double plate brake；Compression plate therein is adjacent with the cylinder block, and a card of bearing disc is with being located in brake shell
Housing bearing disc an end surfaces fitting, Moving plate is between the compression plate and bearing disc.The small brake is individually grasped
Brake and use for ground taxi when vertical.
The heat reservoir of the big brake gear is made up of compression plate, bearing disc, multiple Moving plates and multiple quiet disks；The Moving plate
Quantity is 3~5 disks, is multiple-disc brake device；The compression plate is adjacent with cylinder block, and a card of bearing disc is stopped with being located at
The end surfaces fitting of housing bearing disc on car housing；Multiple Moving plates and multiple quiet disks are with Moving plate-quiet disk-Moving plate-quiet
The interleaved mode of disk is arranged between the compression plate and bearing disc.
The present embodiment is a kind of aircraft single-wheel double-brake selectively brake system, including brake instruction biography of Flight By Wire
Sensor 1, control box 3, electrohydraulic servo valve 2, magnetic valve 6 and wheel spin-up transducer 4.The wheel spin-up transducer 4, control box
3 and electrohydraulic servo valve 2 form brake anti-sliding control part；Control box 3 and magnetic valve 6 are used to realize part brake or all stopped
Car.The part brake is realized by running small brake gear；All brakes are by running small brake gear and big simultaneously
Brake gear is realized.Compared with the hydraulic brake system of routine, in the present embodiment, brake instruction transducer 1 instead of hydraulic pressure brake
Car valve, and using the electrohydraulic servo valve 2 of postiive gain.Brake instruction transducer 1 and control box 3, electrohydraulic servo valve 2 form brake control
Part processed；Electrohydraulic servo valve 2 and control box 3 both complete control task of braking, and complete anti-sliding control task again.
The pattern of brake is selected to be controlled by the control device being made up of magnetic valve 6 and control box 3 using brake pressure
Method carries out oil circuit and opens and closes control realization：When the brake pressure corresponding to the brake instruction that brake instruction transducer 1 exports is less than
During setting value, control box 3 does not give the output control electric current of magnetic valve 6, and magnetic valve 6 is in cut-off or closed mode without power supply,
Magnetic valve 6 exports without hydraulic coupling；Conversely, control box 3 sends control signal to magnetic valve 6 or provides electric energy, magnetic valve 6 obtains
Power supply starts and is in opening, and the fluid pressure line that magnetic valve 6 controls is open-minded, and magnetic valve 6 has hydraulic coupling output.
The brake pressure setting value is 40~65% normal braking pressure；
Wheel velocity measuring is completed by wheel spin-up transducer 4, monitors the sliding mode of wheel.Anti-sliding control is by control box
3 complete.The brake pressure of brake machine wheel 5 is transported in the control electric current signal of the response control box 3 of electrohydraulic servo valve 2, output and regulation.
Selection brake is carried out by magnetic valve 6 and the composition control device of control box 3；
The brake instruction transducer 1 is arranged on below cockpit floor, and it is manipulated by driver, needed for control output
Brake instruction voltage signal, then control electrohydraulic servo valve 2 to export required water brake pressure by control box 3.The brake
The electric interfaces of instruction sensor 1 are electrically coupled by cable with control box 3, and the brake instruction voltage signal of driver is provided
To control box 3, the brake for wheel.
The electrohydraulic servo valve 2 has an electrical outlets and three hydraulic interfaces.The electrical outlets pass through with plug
Cable is implemented electrically to couple with control box 3, receives the brake anti-sliding control current signal that control box 3 is sent.Three hydraulic pressure
Interface is electrohydraulic servo valve oil inlet, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening respectively.Electro-hydraulic servo therein
Valve oil inlet carrys out oil pipe line with brake system pressure source and coupled, specifically by the fuel-displaced of the electrohydraulic servo valve oil inlet and hydraulic lock
Mouth connection, is coupled by hydraulic lock with brake system pressure source come oil pipe line；Electrohydraulic servo valve brake mouth respectively with wheel
Small brake gear oil inlet and big brake gear oil inlet coupled by pipeline, during connection, brake mouth connecting pipeline is divided into
Small brake gear fluid pressure line 7 and big brake gear fluid pressure line 8, by the small brake gear fluid pressure line 7 directly and wheel
Small brake gear oil inlet 9 couple, by big brake gear oil inlet of the big brake gear fluid pressure line 8 directly with wheel
B couples.Magnetic valve 6 is in series with the big brake gear fluid pressure line 8, specifically enters the magnetic valve of the magnetic valve 6
Hydraulic fluid port is connected by pipeline with small brake gear fluid pressure line 7, so that the brake of the magnetic valve oil inlet and electrohydraulic servo valve 2
Mouth connection；The magnetic valve hydraulic fluid port of magnetic valve 6 is coupled with the big brake gear oil inlet B of wheel by pipeline.It is described electro-hydraulic to watch
Valve oil return opening is taken with aircraft return line to couple.When electrohydraulic servo valve 2 is not having control electric current, electrohydraulic servo valve oil inlet closes
Close, electrohydraulic servo valve oil return opening and electrohydraulic servo valve brake mouth oil circuit connection are unimpeded；Electrohydraulic servo valve 2 when there is control electric current,
Electrohydraulic servo valve oil return opening is closed, and oil inlet is opened, with electrohydraulic servo valve brake mouth oil circuit UNICOM, electrohydraulic servo valve brake mouth
The water brake pressure of the corresponding control electric current of output.The control electric current that control box 3 inputs electrohydraulic servo valve 2 is bigger, electro-hydraulic servo
The brake pressure that valve 2 exports is bigger, realizes the Stress control of postiive gain.
The magnetic valve 6 is located on the big brake gear hydraulic tube 8 for braking mouth output in electrohydraulic servo valve 2, passes through brake
The corresponding relation for the water brake pressure that the brake instruction voltage signal that instruction sensor 1 is sent exports with electrohydraulic servo valve 2, by
Control box 3 judges brake pressure size according to brake instruction voltage signal size and controls switching on and off for magnetic valve 6, so as to
Whether the control place fluid pressure line of magnetic valve 6 exports and disconnects brake pressure.The magnetic valve 6 has an electric interfaces and three
Hydraulic interface.Three hydraulic interfaces are magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively.It is therein
Magnetic valve oil inlet couples with the brake mouth pipeline of electrohydraulic servo valve 2, magnetic valve oil-out and the big brake gear of brake machine wheel 5
The pipeline of oil-feed interface 10 couples, and electromagnetic valve oil return mouth couples with aircraft return line.The electric interfaces of magnetic valve 6 are exhausted by shielding
Edge wire electrically couples with the electric interfaces output end of control box 3；Receive the control electric current signal that control box 3 is sent；Control box 3 is
No control electric current signal of sending is to magnetic valve 6, the brake instruction voltage signal that is exported depending on brake instruction transducer 1 or correspondingly
Electrohydraulic servo valve 2 export water brake pressure；When brake pressure is less than setting value, control box 3 is not sent to magnetic valve 6
Control electric current signal, magnetic valve 6 are off without being powered, and the oil-out of magnetic valve 6 does not export, oil-out and oil return
Oral groove leads to；When brake pressure is more than or equal to setting value, control box 3 sends control electric current signal to magnetic valve 6, and magnetic valve 6 is logical
Electric-opening, the oil return opening of magnetic valve 6 are closed, and oil inlet and oil-out are linked up, and the fluid pressure line that magnetic valve 6 controls is open-minded；
The brake instruction voltage signal setting value is 40~65% normal braking command voltage signals, or brake pressure is set
Definite value is 40~65% normal braking pressure；The present embodiment brake instruction voltage signal setting value is 55% normal braking instruction electricity
Signal is pressed, or brake pressure setting value is 55% normal braking pressure.
Velocity sensor 4 is arranged on plane axletree, or on wheel braking housing, passes through mechanically operated mode and wheel
Connection, experiences wheel rotary speed, and wheel rotary speed is converted into electric signal output.The velocity sensor 4 of the present embodiment
On plane axletree, driven and rotated by the hub drive pin of brake machine wheel 5；Velocity sensor 4 has an electric interfaces, passes through
Cable electrically couples with control box 3, and the wheel rotary speed voltage signal detected is supplied into control box 3, monitors wheel
Sliding mode.
Control box 3 has the functions such as brake anti-sliding control, fault detect；The input difference of the electric interfaces of control box 3
With velocity sensor 4 and brake instruction transducer 1 by cable connection, believed with receiving the wheel speed of the offer of velocity sensor 4
Number and receive the brake instruction voltage signal sent of brake instruction transducer 1.The output end of the electric interfaces of control box 3 with it is electro-hydraulic
The cable connection of servo valve 2, control signal is sent to electrohydraulic servo valve 2.Control box 3 is powered by aircraft power system.
Pressure sensor 7 is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth, experiences brake pressure, and will stop
Car pressure transition is that electric signal is supplied to control box 3, with controlling turning on or off for magnetic valve 6.The pressure sensor 7 has
One electric interfaces and a hydraulic interface；Electric interfaces pass through shielding insulation wire and the electric interfaces input of control box 3 electricity
Gas couples, and the water brake pressure of the brake of electrohydraulic servo valve 2 mouth output when braking is inputted to control box 3；The liquid of pressure sensor 7
Crimping mouth couples with the fluid pressure line of the brake mouth of electrohydraulic servo valve 2.
In the present embodiment, small brake gear fluid pressure line 7 is unblocked, and guarantee can be used in braking at any time；Big brake dress
It is conditional open-minded to put fluid pressure line 8, i.e., is only filled when the brake system is ensureing that aircraft floor slides brake with small brake
Put, small brake gear and big brake gear use simultaneously in the case of other, realize the double-brake of aircraft.
Skidded in brake process if there is wheel, by control box 3, electrohydraulic servo valve 2 and the structure of wheel spin-up transducer 4
Into brake anti-sliding control part implement control.Anti-sliding control is realized by prior art.
Claims (7)
1. a kind of airplane wheel Flight By Wire brake system that can select brake modes, the main landing gear of aircraft is equipped with a brake
Vehicle device wheel, the brake machine wheel have two brake gears, it is characterised in that the airplane wheel Flight By Wire brake system includes stopping
Car instruction sensor, control box, electrohydraulic servo valve, magnetic valve, wheel spin-up transducer and pressure sensor；The wheel speed
Sensor, control box and electrohydraulic servo valve form brake anti-sliding control part；Control box and magnetic valve are controlled by brake pressure
Method carry out oil circuit open and close control realize aircraft part brake or all brake；The part brake is by running small brake
Device is realized；All brakes are realized by running small brake gear and big brake gear simultaneously；The brake pressure setting
It is worth for the 40%~65% of normal braking pressure；When the brake pressure corresponding to the brake instruction of brake instruction transducer output is small
When setting value, control box does not give magnetic valve output control electric current, and magnetic valve is not powered and is in cut-off or closed mode, electricity
Magnet valve does not have hydraulic coupling output；Conversely, control box sends control signal to magnetic valve or provides electric energy, magnetic valve obtains power supply and opened
Move and be in opening, the fluid pressure line of solenoid valve control is open-minded, and magnetic valve has hydraulic coupling output；
The brake instruction transducer is arranged on below cockpit floor；The magnetic valve is located at defeated in electrohydraulic servo valve brake mouth
On the big brake gear hydraulic tube gone out；Pressure sensor is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth；It is electro-hydraulic
The oil inlet of servo valve is coupled with brake system pressure source coming oil by pipeline, and electrohydraulic servo valve brake mouth is small with wheel respectively
Brake gear oil inlet and big brake gear oil inlet are coupled by pipeline, and the input of electrohydraulic servo valve electrically connects with control box
The output end connection of mouth.
2. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that institute
The electric interfaces for stating brake instruction transducer are electrically coupled by cable with control box, by the brake instruction voltage signal of driver
Control box is supplied to, the brake for wheel.
3. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that institute
Stating electrohydraulic servo valve has an electrical outlets and three hydraulic interfaces；The electrical outlets pass through connectorized cable and control box
Implement electrically connection, receive the brake anti-sliding control current signal that control box is sent；Three hydraulic interfaces are electro-hydraulic respectively
Servo valve oil inlet, electrohydraulic servo valve brake mouth and electrohydraulic servo valve oil return opening；Electrohydraulic servo valve oil inlet therein passes through liquid
Pressure lock carrys out oil pipe line with brake system pressure source and coupled, and small brake gear of the electrohydraulic servo valve brake mouth respectively with wheel enters
Hydraulic fluid port and big brake gear oil inlet are coupled by pipeline, and during connection, brake mouth connecting pipeline is divided into small brake gear hydraulic pressure
Pipeline and big brake gear fluid pressure line, by small brake gear oil inlet of the small brake gear fluid pressure line directly with wheel
Connection, the big brake gear fluid pressure line is directly coupled with the big brake gear oil inlet of wheel；In the big brake dress
Put and magnetic valve is in series with fluid pressure line, the magnetic valve oil inlet of the magnetic valve is specifically passed through into pipeline and small brake gear
Fluid pressure line connects, so that the magnetic valve oil inlet connects with the brake mouth of electrohydraulic servo valve；The magnetic valve of magnetic valve is gone out
Hydraulic fluid port is coupled with the big brake gear oil inlet of wheel by pipeline；The electrohydraulic servo valve oil return opening joins with aircraft return line
Connect.
4. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that institute
Stating magnetic valve has an electric interfaces and three hydraulic interfaces；Three hydraulic interfaces are magnetic valve oil inlet, electromagnetism respectively
Valve oil-out and electromagnetic valve oil return mouth；Magnetic valve oil inlet therein couples with the brake mouth pipeline of electrohydraulic servo valve, magnetic valve
Oil-out couples with the big brake gear oil-feed interface pipeline of brake machine wheel, and electromagnetic valve oil return mouth couples with aircraft return line；
The electric interfaces of magnetic valve are electrically coupled by shielding insulation wire with control box electric interfaces output end.
5. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that machine
Wheel speed sensor is arranged on plane axletree, or on wheel braking housing, is coupled by mechanically operated mode with wheel, is felt
Electric signal output is converted to by wheel rotary speed, and by wheel rotary speed；The electric interfaces of wheel spin-up transducer pass through
Cable electrically couples with control box, and the wheel rotary speed voltage signal detected is supplied into control box, monitors the cunning of wheel
Dynamic state.
6. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that control
The input of the electric interfaces of box processed is respectively with wheel spin-up transducer and brake instruction transducer by cable connection, to receive
The wheel rate signal and receive the brake instruction voltage signal that brake instruction transducer is sent that wheel spin-up transducer provides；Control
The output end of the electric interfaces of box processed and electrohydraulic servo valve cable connection, control signal is sent to electrohydraulic servo valve；Control box
Powered by aircraft power system.
7. the airplane wheel Flight By Wire brake system of brake modes can be selected as claimed in claim 1, it is characterised in that pressure
Force snesor is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth；The pressure sensor have an electric interfaces and
One hydraulic interface；The electric interfaces of the pressure sensor pass through shielding insulation wire and control box electric interfaces input electricity
Gas couples, and the water brake pressure of electrohydraulic servo valve brake mouth output when braking is inputted to control box；The pressure sensor
Hydraulic interface 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 CN105905281A (en) | 2016-08-31 |
| CN105905281B true 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) |
Families Citing this family (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 (3)
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3017367B1 (en) * | 2014-02-10 | 2017-02-24 | Airbus Operations Sas | AIRCRAFT COMPRISING A LANDING TRAIN WITH A WHEEL PROVIDED WITH AN ELECTRIC MOTOR AND A CONTROL SYSTEM OF SAID ELECTRIC MOTOR |
-
2016
- 2016-06-17 CN CN201610436553.0A patent/CN105905281B/en not_active Expired - Fee Related
Patent Citations (3)
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105905281A (en) | 2016-08-31 |
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Granted publication date: 20171212 Termination date: 20210617 |