CN106081073B - A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake - Google Patents
A kind of optional Flight By Wire brake system of aircraft single-wheel double-brake Download PDFInfo
- Publication number
- CN106081073B CN106081073B CN201610436221.2A CN201610436221A CN106081073B CN 106081073 B CN106081073 B CN 106081073B CN 201610436221 A CN201610436221 A CN 201610436221A CN 106081073 B CN106081073 B CN 106081073B
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- Prior art keywords
- brake
- wheel
- hydraulic
- servo valve
- electrohydraulic servo
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
- 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 optional Flight By Wire brake system of aircraft single-wheel double-brake, including brake instruction transducer, control box, electrohydraulic servo valve, hydraulic selector, magnetic valve and wheel spin-up transducer.The wheel spin-up transducer, control box and electrohydraulic servo valve form brake anti-sliding control part；Hydraulic selector and magnetic valve are used for the selection for realizing brake modes；The selection for realizing brake modes is that the small brake gear operation realization of selection is braked to the part of wheel, or the small brake gear of selection is run simultaneously with big brake gear, realizes the double-brake to wheel.The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, it disclosure satisfy that requirement of the single-wheel double-brake selection using brake, it have adjusted 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 annex, detection accessory and control annex, for normal
The hydraulic brake system of rule, mainly include water brake valve, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box；For
Brake-by-wire system, it is and normal mainly including brake instruction transducer, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box
The hydraulic brake system of rule is compared, and brake instruction transducer instead of water brake valve, in addition, Electric hydraulic pressure servo valve is just to increase
Beneficial valve.Airplane wheel brake system controls single brake machine wheel with a brake on a wheel, or is carried on a wheel
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.The requirement using brake is selected according to single-wheel double-brake, existing airplane wheel brake system does not have this ability.
The content of the invention
To overcome the shortcomings of to select brake modes present in prior art, the present invention proposes a kind of aircraft single-wheel dual brake
The optional Flight By Wire brake system of car.
The present invention includes brake instruction transducer, control box, electrohydraulic servo valve, hydraulic selector, magnetic valve and wheel speed
Sensor.The wheel spin-up transducer, control box and electrohydraulic servo valve form brake anti-sliding control part；Hydraulic selector and electricity
Magnet valve is used for the selection for realizing brake modes；The selection for realizing brake modes is that the small brake gear operation of selection is realized to machine
The part brake of wheel, or the small brake gear of selection are run simultaneously with big brake gear, realize the double-brake to wheel.
The brake instruction transducer is arranged on below cockpit floor, and 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, which is selected, hydraulic lock electrohydraulic servo valve；The electrical outlets of the electrohydraulic servo valve pass through cable
Implement electrically to couple with control box；The hydraulic interface of the electrohydraulic servo valve is electrohydraulic servo valve oil inlet respectively, electro-hydraulic watched
Take valve brake mouth and electrohydraulic servo valve oil return opening.Electrohydraulic servo valve oil inlet therein passes through hydraulic lock and brake system pressure source
Carry out oil pipe line connection；Described electrohydraulic servo valve brake mouth and small brake gear oil inlet and the big brake gear oil inlet pipe of wheel
Road couples, and brake mouth connecting pipeline specifically is divided into small brake gear fluid pressure line and big brake gear fluid pressure line, and make
Small brake gear fluid pressure line therein directly couples with the small brake gear oil inlet pipeline of wheel, makes big brake dress therein
Fluid pressure line is put through magnetic valve with the big brake gear oil inlet pipeline of wheel to couple；The oil-out of the magnetic valve and wheel
Big brake gear oil inlet pipeline connection.The electrohydraulic servo valve oil return opening couples with aircraft return line；
Velocity sensor is arranged on plane axletree, or on wheel braking housing, passes through mechanically operated mode and wheel
Connection, experiences wheel rotary speed, wheel rotary speed is converted into electric signal output.
Hydraulic selector is arranged on the fluid pressure line of electrohydraulic servo valve brake mouth.The electric interfaces of hydraulic selector pass through shielding
Insulated conductor electrically couples with the electric interfaces of magnetic valve, specifically by the microswitch of the hydraulic selector and the electromagnetism of magnetic valve
Iron coil is connected, and is switched on or switched off the control electric current signal for the electromagnet coil for being supplied to magnetic valve；The hydraulic pressure of hydraulic selector connects
Mouth couples with the brake mouth pipeline of electrohydraulic servo valve.
Magnetic valve is arranged on the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output, is entered by hydraulic control
And be changed into communication and disconnection that oil-feed oil circuit and fuel-displaced oil circuit are realized in electric control, whether export so as to fluid pressure line where controlling and
Disconnect brake pressure.The electric interfaces of the magnetic valve are electrically joined by the electric interfaces of shielding insulation wire and hydraulic selector
Connect, specifically, the electromagnet coil of magnetic valve is connected with the microswitch of hydraulic selector, then is connected on power supply, is received
Control electric current signal is sent after the microswitch closure of hydraulic selector；
The hydraulic interface of the magnetic valve is magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively.Its
In：Magnetic valve oil inlet is connected in parallel on small brake gear fluid pressure line by pipeline, so as to connect with the brake mouth of electrohydraulic servo valve
It is logical；Magnetic valve oil-out is coupled with the big brake gear oil inlet by big brake gear fluid pressure line；Electromagnetic valve oil return mouth
Couple with aircraft return line.
The brake pressure setting value for controlling hydraulic selector is 40~65% normal braking pressure.
The input of the electric interfaces of the control box passes through cable with velocity sensor and brake instruction transducer respectively
Connection, the brake instruction voltage signal that the wheel speed and brake instruction transducer that reception velocity sensor provides respectively are sent.
The output end of the electric interfaces of control box, with electrohydraulic servo valve cable connection, control signal is sent to electrohydraulic servo valve；Control
Box is powered by aircraft power system.
To adapt to the needs of main landing gear single-wheel double-brake wheel structure choice brake, the present invention is using " being divided into two "
Way, i.e. brake system export is divided into two to a fluid pressure line of wheel brake, and a fluid pressure line is straight-through one
Small brake gear, this fluid pressure line keep unimpeded；Another fluid pressure line sets control device, then leads to another big brake
Device, the break-make of the fluid pressure line are controlled by control device.So as to realize that aircraft floor slides only small brake gear operation, other
The function of situation whole brake gear operation, carbon mill damage in brake is slided to reach reduction, improves and improves carbon disk service life
Purpose；
In the present invention, wheel spin-up transducer, control box and electrohydraulic servo valve form brake anti-sliding control part；Hydraulic pressure is opened
Close and magnetic valve is used for realizing the i.e. small brake gear operation of part brake and the work(that i.e. two brake gears are all run that all brakes
Energy.Compared with the hydraulic brake system of routine, brake instruction transducer instead of water brake valve, in addition, electrohydraulic servo valve is
Postiive gain valve, brake instruction transducer and control box, electrohydraulic servo valve form brake control section；Electrohydraulic servo valve and control box
Both control task of braking is completed, completes anti-sliding control task again.
For safeguards system safe and reliable operation, from the electrohydraulic servo valve with hydraulic lock, receive first during control box brake
The electric signal first unlocked, to connect the voltage supply coming oil of electrohydraulic servo valve.
Selection brake carries out oil by the control device being made up of magnetic valve and hydraulic selector using brake pressure control methods
Road opens and closes control and realized：When brake pressure is less than setting value, hydraulic selector disconnects the power supply circuit of magnetic valve, and magnetic valve does not have
Power and there is no hydraulic coupling output in cut-off or closed mode, magnetic valve；Conversely, hydraulic selector is connected or closed electromagnetic valve
Power supply circuit, magnetic valve obtain power supply and start and be in opening, and the fluid pressure line of solenoid valve control is open-minded, and magnetic valve has liquid
Pressure output.
In the present invention, electrohydraulic servo valve when not having control electric current, close by oil inlet, oil return opening and the oil circuit connection of brake mouth
It is unimpeded；Electrohydraulic servo valve when there is control electric current, closed by oil return opening, and oil inlet is opened, defeated with brake mouth oil circuit UNICOM, brake mouth
Go out the water brake pressure of corresponding control electric current；The control electric current of control box input electrohydraulic servo valve is bigger, and electrohydraulic servo valve is defeated
The brake pressure gone out is bigger, realizes the Stress control of postiive gain.
In the present invention, the unlatching of magnetic valve is controlled by hydraulic selector, and the closed and disconnected of hydraulic selector be controlled by it is 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 to close microswitch button to connect, hydraulic selector is still to disconnect, and magnetic valve is not powered and is off,
Magnetic valve oil-out is not exported, and oil-out and oil return opening are linked up；When brake pressure is more than or equal to setting value, hydraulic selector closes
Circuit is closed, solenoid valves are opened, and electromagnetic valve oil return mouth is closed, and oil inlet and oil-out are linked up, the hydraulic tube of solenoid valve control
Road is open-minded.
In the present invention, the passage that braked when first is that fluid pressure line is unblocked, and guarantee can be used in braking at any time, second
Bar brake passage is that fluid pressure line is conditional open-minded.So, the brake system when ensureing that aircraft floor slides brake only
With small brake gear, two brake gears use simultaneously in the case of other, realize the double-brake of aircraft.
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. hydraulic selector；8. small brake gear fluid pressure line；9. big brake gear fluid pressure line；10. small brake gear oil-feed connects
Mouthful；11. big brake gear oil-feed interface.
Embodiment
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
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.
Brake system described in the present embodiment is fly-by-wire, including brake instruction transducer 1, control box 3, electro-hydraulic
Servo valve 2, hydraulic selector 7, magnetic valve 6 and wheel spin-up transducer 4.The wheel spin-up transducer 4, control box 3 and electro-hydraulic
Servo valve 2 forms brake anti-sliding control part；The selection of hydraulic selector 7 and magnetic valve 6 with realizing brake modes, that is, select small
Brake gear is run, and realizes that the part brake to wheel, or the small brake gear of selection are run simultaneously with big brake gear, to realize
To the double-brake of wheel.
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.Brake instruction
Sensor 1 has an electric interfaces, is electrically coupled with control box 3 by cable, the brake instruction voltage signal of driver is carried
Supply 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, and the electrohydraulic servo valve oil inlet and the oil-out of hydraulic lock are joined
Connect, coupled by hydraulic lock with brake system pressure source come oil pipe line；Described electrohydraulic servo valve brake mouth and the small brake of wheel
Car device oil inlet and the connection of big brake gear in-line, are specifically divided into small brake by brake mouth connecting pipeline through three-way connection
Car device fluid pressure line 8 and big brake gear fluid pressure line 9, and make small brake gear fluid pressure line 8 therein directly and wheel
The small pipeline of brake gear oil inlet 10 connection, make big brake of the big brake gear fluid pressure line 9 therein through magnetic valve 6 Yu wheel
The pipeline of car device oil inlet 11 couples so that the electrohydraulic servo valve 2 brake mouth also with the oil inlet pipeline connection of magnetic valve 6；Institute
The oil-out of magnetic valve is stated with the big pipeline of brake gear oil inlet 11 of wheel to couple.
The electrohydraulic servo valve oil return opening couples with aircraft return line；When electrohydraulic servo valve does not have control electric current, electricity
Hydraulic servo oil inlet 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 inlet is opened, with electrohydraulic servo valve brake mouth
Oil circuit UNICOM, the water brake pressure of the corresponding control electric current of electrohydraulic servo valve brake mouth output.Control box 3 inputs electro-hydraulic servo
The control electric current of valve 2 is bigger, and the brake pressure of electrohydraulic servo valve output is bigger, realizes the Stress control of postiive gain；It is electro-hydraulic to watch
Take valve 2 and control box 3 both completes control task of braking, complete anti-sliding control task again.
For safeguards system safe and reliable operation, from hydraulic lock electrohydraulic servo valve 2, receive first when control box 3 is braked
The electric signal first unlocked, to connect the voltage supply coming oil of electrohydraulic servo valve 2.
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, wheel rotary speed is converted into electric signal output.The present embodiment velocity sensor 4 is installed
On plane axletree, driven and rotated by the hub drive pin of brake machine wheel 5.The electric interfaces of velocity sensor 4 pass through cable and control
Box 3 processed electrically couples, and the wheel rotary speed voltage signal detected is supplied into control box 3, monitors the sliding mode of wheel.
Hydraulic selector 7 is arranged on the fluid pressure line of the brake mouth of electrohydraulic servo valve 2, is specifically braked in electrohydraulic servo valve 2
On the fluid pressure line of mouth.The hydraulic selector 7 includes piston, push rod and microswitch.Hydraulic selector 7 experiences brake pressure, behaviour
Microswitch is indulged to control the disconnection of electric wiring and closure.
Hydraulic selector 7 has an electric interfaces and a hydraulic interface.The electric interfaces by shielding insulation wire with
The electric interfaces of magnetic valve 6 electrically couple, specifically by the microswitch of the hydraulic selector 7 and the electromagnet coil of magnetic valve 6
Series connection, it is switched on or switched off the control electric current signal for the electromagnet coil for being supplied to magnetic valve 6；The hydraulic interface of hydraulic selector 7 and electricity
The brake mouth pipeline connection of hydraulic servo 2.
Magnetic valve 6 is arranged on electrohydraulic servo valve 2 and braked on another fluid pressure line 9 that mouth exports, and is entered by hydraulic control
And be changed into communication and disconnection that oil-feed oil circuit and fuel-displaced oil circuit are realized in electric control, whether export so as to fluid pressure line where controlling and
Disconnect brake pressure.
The magnetic valve 6 has an electric interfaces and three hydraulic interfaces.Three hydraulic interfaces are magnetic valve respectively
Oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth.Wherein：
Magnetic valve oil inlet is connected in parallel on small brake gear fluid pressure line 8 by pipeline, so as to the brake with electrohydraulic servo valve 2
Car mouth connects；Magnetic valve oil-out is coupled with the big brake gear oil inlet 11 by big brake gear fluid pressure line 9；Electromagnetism
Valve oil return opening couples with aircraft return line.
The electric interfaces of the magnetic valve 6 are electrically coupled by shielding insulation wire with the electric interfaces of hydraulic selector 7, tool
Body, the electromagnet coil of magnetic valve 6 is connected with the microswitch of hydraulic selector 7, then is connected on power supply, receives hydraulic pressure
Control electric current signal is sent after the microswitch closure of switch 7；The unlatching of magnetic valve 6 is controlled by hydraulic selector 7, and hydraulic selector
7 closed and disconnected is controlled by the output brake pressure of electrohydraulic servo valve 2：When brake pressure is less than setting value, hydraulic selector 7
It is not enough to promote push rod that microswitch button is closed into connection by the piston of action of hydraulic force, hydraulic selector 7 is still to disconnect, electromagnetism
Valve 6 is off without being powered, and the oil-out of magnetic valve 6 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, the closed circuit of hydraulic selector 7, magnetic valve 6 be powered open, the oil return opening of magnetic valve 6 close, oil inlet and
Oil-out is linked up, and the fluid pressure line that magnetic valve 6 controls is open-minded.
The brake pressure setting value for controlling hydraulic selector 7 is 40~65% normal braking pressure；The present embodiment brakes
Pressure set points are 55% normal braking pressure；
Control box 3 has brake anti-sliding control and fault detection capability.The input of the electric interfaces of control box 3 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.The output end of the electric interfaces of control box 3, with electrohydraulic servo valve 2
With cable connection, control signal is sent to electrohydraulic servo valve 2；Control box 3 is powered by aircraft power system.
Pass through the control device being made up of magnetic valve 6 and hydraulic selector 7.Oil circuit keying is carried out using brake pressure control methods
Control selections brake modes：When brake pressure is less than setting value, hydraulic selector 7 disconnects the power supply circuit of magnetic valve 6, magnetic valve
6 export without power supply in cut-off or closed mode, magnetic valve 6 without hydraulic coupling；Conversely, hydraulic selector 7 is connected or closed
The power supply circuit of magnetic valve 6, magnetic valve 6 obtain power supply and start and be in opening, and the fluid pressure line that magnetic valve 6 controls is opened
Logical, magnetic valve 6 has hydraulic coupling output.
In the present embodiment, small brake gear fluid pressure line 8 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 9.So, the brake system can ensure when aircraft floor slides brake only with small brake
Device, small brake gear and big brake gear are tested simultaneously in the case of other, to 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.
Compared with the hydraulic brake system of routine, in the present embodiment, brake instruction transducer 1 instead of water brake valve,
In addition, electrohydraulic servo valve 2 is postiive gain valve, brake instruction transducer 1 and control box 3, electrohydraulic servo valve 2 form brake control unit
Point；Electrohydraulic servo valve 2 and control box 3 both complete control task of braking, and complete anti-sliding control task again.
For safeguards system safe and reliable operation, electrohydraulic servo valve 2 also carries hydraulic lock, receives when control box 3 is braked first
The electric signal of unlocking, to connect the voltage supply coming oil of electrohydraulic servo valve 2.
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 of electrohydraulic servo valve 2, output and regulation；
Selection brake is carried out by pilot operated valve device.
Claims (7)
1. a kind of optional Flight By Wire brake system of aircraft single-wheel double-brake, the main landing gear of aircraft is equipped with a braking machine
Wheel, the brake machine wheel have two brake gears, it is characterised in that the Flight By Wire brake system senses including brake instruction
Device, control box, electrohydraulic servo valve, hydraulic selector, magnetic valve and wheel spin-up transducer；The wheel spin-up transducer, control
Box and electrohydraulic servo valve form brake anti-sliding control part；Hydraulic selector and magnetic valve are used for the selection for realizing brake modes；Institute
State and realize that the selections of brake modes is that selection small brake gear operation is realized the part of wheel is braked, or the small brake gear of selection
Run simultaneously with big brake gear, realize the whole brake to wheel.
2. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that the brake
Instruction sensor is arranged on below cockpit floor, and the electric interfaces of the brake instruction transducer are electric with control box by cable
Connection, is supplied to control box, the brake for wheel by the brake instruction voltage signal of driver.
3. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that described electro-hydraulic
Servo valve, which is selected, hydraulic lock electrohydraulic servo valve；The electrical outlets of the electrohydraulic servo valve are implemented electric by cable and control box
Connection；The hydraulic interface of the electrohydraulic servo valve is electrohydraulic servo valve oil inlet, electrohydraulic servo valve brake mouth and electro-hydraulic respectively
Servo valve oil return opening；Electrohydraulic servo valve oil inlet therein is coupled by hydraulic lock with brake system pressure source come oil pipe line；Institute
The electrohydraulic servo valve brake mouth stated couples with the small brake gear oil inlet of wheel and big brake gear in-line, specifically will
Brake mouth connecting pipeline is divided into small brake gear fluid pressure line and big brake gear fluid pressure line, and makes small brake gear therein
Fluid pressure line directly couples with the small brake gear oil inlet pipeline of wheel, makes big brake gear fluid pressure line therein through electromagnetism
Valve couples with the big brake gear oil inlet pipeline of wheel；The oil-out of the magnetic valve and the big brake gear oil inlet of wheel
Pipeline couples；The electrohydraulic servo valve oil return opening couples with aircraft return line.
4. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that wheel speed
Sensor is arranged on plane axletree, or on wheel braking housing, is coupled by mechanically operated mode with wheel, experienced wheel
Rotary speed, wheel rotary speed is converted into electric signal output.
5. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that hydraulic selector
On the fluid pressure line of electrohydraulic servo valve brake mouth；The electric interfaces of hydraulic selector pass through shielding insulation wire and magnetic valve
Electric interfaces electrically couple, specifically the microswitch of the hydraulic selector is connected with the electromagnet coil of magnetic valve, connect
Or disconnect the control electric current signal that the microswitch is supplied to the electromagnet coil of magnetic valve；The hydraulic interface of hydraulic selector and electricity
The brake mouth pipeline connection of hydraulic servo.
6. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that magnetic valve is pacified
On the big brake gear fluid pressure line of electrohydraulic servo valve brake mouth output, electric control realization is changed into by hydraulic control
The communication and disconnection of oil-feed oil circuit and fuel-displaced oil circuit, so as to control whether place fluid pressure line exports and disconnect brake pressure；Institute
The electric interfaces for stating magnetic valve are electrically coupled by shielding insulation wire with the electric interfaces of hydraulic selector, specifically, magnetic valve
Electromagnet coil connected with the microswitch of hydraulic selector, then be connected on power supply, the fine motion for receiving hydraulic selector is opened
Send control electric current signal in pass；
The hydraulic interface of the magnetic valve is magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively；Wherein：
Magnetic valve oil inlet is connected in parallel on small brake gear fluid pressure line by pipeline, so as to connect with the brake mouth of electrohydraulic servo valve
It is logical；Magnetic valve oil-out is coupled with the big brake gear oil inlet by big brake gear fluid pressure line；Electromagnetic valve oil return mouth
Couple with aircraft return line；
The brake pressure setting value for controlling hydraulic selector is 40%~65% normal braking pressure.
7. the optional Flight By Wire brake system of aircraft single-wheel double-brake as claimed in claim 1, it is characterised in that the control
The input of the electric interfaces of box receives respectively respectively with wheel spin-up transducer and brake instruction transducer by cable connection
The brake instruction voltage signal that the wheel speed and brake instruction transducer that velocity sensor provides are sent；Control box electrically connects
The output end of mouth, with electrohydraulic servo valve cable connection, control signal is sent to electrohydraulic servo valve；Control box is by aircraft power supply system
System power supply.
Priority Applications (1)
| 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 CN106081073A (en) | 2016-11-09 |
| CN106081073B true 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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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108100241B (en) * | 2017-12-06 | 2020-11-10 | 西安航空制动科技有限公司 | Airplane fly-by-wire brake system capable of automatically braking and brake method |
| CN108146622B (en) * | 2017-12-06 | 2021-01-05 | 西安航空制动科技有限公司 | Airplane fly-by-wire brake system using automatic brake switch and brake method |
| 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 |
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 |
-
2016
- 2016-06-17 CN CN201610436221.2A patent/CN106081073B/en not_active Expired - Fee Related
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 |
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| CN106081073A (en) | 2016-11-09 |
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