CN106005380B - A kind of optional brake system of aircraft single-wheel mono-/bis-brake - Google Patents
A kind of optional brake system of aircraft single-wheel mono-/bis-brake Download PDFInfo
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- CN106005380B CN106005380B CN201610431429.5A CN201610431429A CN106005380B CN 106005380 B CN106005380 B CN 106005380B CN 201610431429 A CN201610431429 A CN 201610431429A CN 106005380 B CN106005380 B CN 106005380B
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- brake
- wheel
- valve
- hydraulic
- 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
-
- 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
- B60T11/00—Transmitting braking action from initiating means to ultimate brake actuator without power assistance or drive or where such assistance or drive is irrelevant
- B60T11/10—Transmitting braking action from initiating means to ultimate brake actuator without power assistance or drive or where such assistance or drive is irrelevant transmitting by fluid means, e.g. hydraulic
- B60T11/24—Single initiating means operating on more than one circuit, e.g. dual circuits
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Braking Arrangements (AREA)
- Regulating Braking Force (AREA)
Abstract
A kind of optional brake system of aircraft single-wheel mono-/bis-brake, including water brake valve, magnetic valve, hydraulic selector, control box, electrohydraulic servo valve and wheel spin-up transducer.Control box, electrohydraulic servo valve and wheel spin-up transducer therein form brake anti-sliding control part；Magnetic valve and hydraulic selector are used to control brake machine wheel to select brake modes.The present invention exports brake system is divided into the fluid pressure line led directly to small brake gear and the fluid pressure line connected with big brake gear to the fluid pressure line of wheel brake；There is control device on the fluid pressure line connected with big brake gear, realize that aircraft floor slides only small brake gear and run by the control device, the function of other situation whole brake gears operation, carbon mill damage in brake is slided to reach reduction, improve the purpose for improving carbon disk service life, 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 annex, for the hydraulic pressure of routine
Brake system, mainly include water brake valve, Electric hydraulic pressure servo valve, wheel spin-up transducer, control box.One wheel is come
Say, the brake machine wheel that electronic anti-skid braking system is controlled is so-called single brake with a disc brake device on a wheel
Vehicle device wheel, even if some aged aircrafts are to meet that braking ability is equipped with the institute of two hose type brake gears on a wheel
Double-brake wheel is called, two brakes of the double-brake wheel are also to control operation simultaneously by brake system.To solve carbon disk
Service life problem, the requirement using brake is selected according to single-wheel double-brake, existing airplane wheel brake system is without 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
The optional brake system of mono-/bis-brake.
The present invention includes water brake valve, magnetic valve, hydraulic selector, control box, electrohydraulic servo valve and wheel velocity pick-up
Device.Control box, electrohydraulic servo valve and wheel spin-up transducer therein form brake anti-sliding control part；Magnetic valve and hydraulic pressure are opened
Close for controlling brake machine wheel to select small brake gear operation to realize the brake of the part of brake machine wheel, or the selection small brake
Car is installed on big brake gear while run, to realize that the whole of brake machine wheel brake.
Water brake valve is arranged on below cockpit floor.Three hydraulic interfaces of the water brake valve are that hydraulic pressure is stopped respectively
Car valve oil inlet, water brake valve brake mouth and water brake valve oil return opening, wherein：The water brake valve oil inlet and aircraft
Brake system pressure source pipeline couples, and the water brake valve brake mouth couples with electrohydraulic servo valve oil inlet pipeline, the liquid
Pressure brake valve oil return opening couples with aircraft return line.
The electrical outlets of the electrohydraulic servo valve are electrically coupled by cable with control box, receive the brake that control box is sent
Anti-sliding control current signal；Three hydraulic interfaces of the electrohydraulic servo valve are electrohydraulic servo valve oil inlet, electro-hydraulic servo respectively
Valve brake mouth and electrohydraulic servo valve oil return opening；Wherein：The brake valve brake mouth pipe of the electrohydraulic servo valve oil inlet and brake valve
Road couples；Electrohydraulic servo valve oil return opening couples with aircraft return line；Electrohydraulic servo valve brake mouth connecting pipeline is watched by electro-hydraulic
Valve brake mouth is taken when coupling respectively with two brake gear oil-feed interface pipelines of wheel, brake mouth connecting pipeline is connected through three
Head is divided into small brake gear fluid pressure line and big brake gear fluid pressure line, small brake gear fluid pressure line therein directly with brake
The small brake gear oil-feed interface pipeline connection of vehicle device wheel, big brake of the big brake gear fluid pressure line through magnetic valve and brake machine wheel
Car device oil-feed interface pipeline couples.
Wheel spin-up transducer is arranged on plane axletree or in brake shell, is coupled by machine driving 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 brake machine wheel
Sliding mode.
The input of the electric interfaces of the control box, by cable connection, receives velocity sensor and carried with velocity sensor
The wheel speed of confession.The output end of the electric interfaces of control box is coupled by cable with electrohydraulic servo valve, is sent out to electrohydraulic servo valve
Go out control signal.Power supply needed for control box is provided by aircraft power system.
The hydraulic interface of the hydraulic selector is by hydraulic pressure pressure inlet and conduit with coupling the small brake gear hydraulic tube
Road connects.The electric interfaces of the hydraulic selector are electrically coupled by shielding insulation wire with the electric interfaces of magnetic valve, are specifically
The microswitch of hydraulic selector is connected with the electromagnet coil of magnetic valve, is switched on or switched off the electromagnetism iron wire for being supplied to magnetic valve
The control electric current signal of circle.
The electric interfaces of the magnetic valve are electrically coupled by shielding insulation wire with the electric interfaces of hydraulic selector.Joining
Connect magnetic valve electric interfaces and hydraulic selector electric interfaces when, by the fine motion of the electromagnet coil of magnetic valve and hydraulic selector
Switch series connection, then be connected on power supply, send control electric current signal after receiving the microswitch closure of hydraulic selector.It is described
Three hydraulic interfaces of magnetic valve are magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively.Wherein：The electricity
Magnet valve oil inlet couples with described electrohydraulic servo valve brake mouth pipeline；The big brake gear of magnetic valve oil-out and brake machine wheel
Pipeline couples, and passes to big brake gear oil-feed interface, electromagnetic valve oil return mouth couples with aircraft return line.
The brake pressure setting value of the hydraulic selector is 40~65% normal braking pressure.
The present invention uses the way of " being divided into two ", i.e. brake system exports a fluid pressure line to wheel brake
It is divided into two, a fluid pressure line leads directly to a small brake gear, and this fluid pressure line keeps unimpeded；Another fluid pressure line is set
Control device is put, then leads to another big brake gear, the break-make of the fluid pressure line is controlled by control device.So as to realize aircraft
The only small brake gear operation of ground taxi, the function of other situation whole brake gears operation, is slided in brake with reaching reduction
Carbon mill damage, improve the purpose for improving carbon disk service life.
In the present invention, selection brake is entered by magnetic valve and hydraulic selector composition control device using brake pressure control methods
Row oil circuit opens and closes control, and it is small brake gear operation and the work(that i.e. two brake gears are all run that all brakes to realize part brake
Energy；When brake pressure is less than setting value, hydraulic selector disconnects the power supply circuit of magnetic valve, and magnetic valve is not powered and is in and cuts
Only or closed mode, magnetic valve do not have hydraulic coupling output；Conversely, hydraulic selector is connected or the power supply circuit of closed electromagnetic valve, electricity
Magnet valve obtains power supply and starts and be in opening, and the fluid pressure line of solenoid valve control is open-minded, and magnetic valve has hydraulic coupling output.
Magnetic valve is arranged on the big brake gear fluid pressure line of water brake 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 electromagnet coil of magnetic valve is connected with the microswitch of hydraulic selector, then is connected on power supply, is connect
Control electric current signal is sent after receiving the microswitch closure of hydraulic selector；The unlatching of magnetic valve is controlled by hydraulic selector, and hydraulic pressure
The closed and disconnected of switch is controlled by the output brake pressure of electrohydraulic servo valve, and when brake pressure is less than setting value, hydraulic pressure is opened
Close and be not enough to promote push rod that microswitch button is closed into connection by the piston of action of hydraulic force, hydraulic selector is still to disconnect, electricity
Magnet valve is not powered and is off, and magnetic valve oil-out does not export, and oil-out and oil return opening are linked up；Work as brake pressure
During more than or equal to setting value, hydraulic selector closed circuit, solenoid valves are opened, and electromagnetic valve oil return mouth is closed, and oil inlet and is gone out
Hydraulic fluid port is linked up, and the fluid pressure line of solenoid valve control is open-minded.
The present invention is suitable for use with the single-wheel double-brake wheel of carbon brake, disclosure satisfy that the selection of single-wheel double-brake uses brake
Requirement.Because the system has the ability for selecting to slide brake, so, when aircraft floor slides brake, only with small brake
Device or a brake gear operation, rather than all brake gears are all being run simultaneously, improve carbon disk when sliding brake
Level can be 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
Carbon mill damage amount during brake reduces, and reaches the purpose for improving or improving carbon disk service life.Set by this wheel and system
Meter, have adjusted the use state of carbon disk, the anti abrasive good characteristic of carbon-to-carbon composite friction material is given 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 of carbon disk
And economic benefit.
Brief description of the drawings
Accompanying drawing 1 is the structural representation of the present invention.In figure：
1. water brake valve；2. electrohydraulic servo valve；3. control box；4. wheel spin-up transducer；5. brake machine wheel；6. electromagnetism
Valve；7. 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 present embodiment is a kind of optional brake system of aircraft single-wheel mono-/bis-brake.
The brake system manipulates for conventional hydraulic.Main landing gear is equipped with a brake machine wheel, with 2 brake gears,
Referred to as single-wheel double-brake wheel.The brake disc of each brake gear is manufactured using carbon-to-carbon composite friction material completely.
The brake disc number of a brake gear in 2 brake gears is less, is single disc-type or double plate brake dress
Put, make heat reservoir axial dimension small, therefore referred to as small brake gear；Another brake gear brake disc number is more, is multiple-disc brake
Device, make heat reservoir axial dimension big, therefore referred to as big brake gear.Described small brake gear and big brake gear are disclosed in
In the innovation and creation of Application No. 201610281025.2.
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 includes water brake valve 1, magnetic valve 6, hydraulic selector 8, control box 3, electrohydraulic servo valve 2 and wheel speed
Spend sensor 4.Control box 3, electrohydraulic servo valve 2 and wheel spin-up transducer 4 therein form brake anti-sliding control part；Electromagnetism
Valve 6 and hydraulic selector 8 are used to control the brake of brake machine wheel 5 to select, that is, select small brake gear to run, to realize brake machine wheel
Part brake；Or the big brake gear operation of selection, to realize that the whole of brake machine wheel brake.
Water brake valve 1 is arranged on below cockpit floor, and it is manipulated by driver, exports required water brake pressure
Power.Water brake valve 1 has three hydraulic interfaces, is that water brake valve oil inlet, water brake valve brake mouth and hydraulic pressure are stopped respectively
Car valve oil return opening, wherein：The water brake valve oil inlet couples with airplane brake system pressure source pipeline, the water brake
Valve brake mouth couples with electrohydraulic servo valve oil inlet pipeline, and the water brake valve oil return opening couples with aircraft return line.
Electrohydraulic servo valve 2 has an electrical outlets and three hydraulic interfaces, is electrohydraulic servo valve oil inlet respectively, electro-hydraulic watches
Take valve brake mouth and electrohydraulic servo valve oil return opening；Wherein：The electrical outlets are electrically joined by connectorized cable and control box 3
Connect, receive the brake anti-sliding control current signal that control box 3 is sent；The brake of the electrohydraulic servo valve oil inlet and brake valve 1
Valve brake mouth pipeline connection；Electrohydraulic servo valve brake mouth couples with two brake gear oil inlet pipelines of wheel respectively.
When electrohydraulic servo valve brake mouth is coupled with two brake gear oil-feed interface pipelines of wheel respectively, make brake
Mouth connecting pipeline is divided into small brake gear fluid pressure line 8 and big brake gear fluid pressure line 9, small brake therein through three-way connection
Device fluid pressure line 8 directly couples with the small pipeline of brake gear oil-feed interface 10 of brake machine wheel 5, big brake gear fluid pressure line
9 couple through magnetic valve 6 with the big pipeline of brake gear oil-feed interface 11 of brake machine wheel 5.
The electrohydraulic servo valve brake mouth couples with the magnetic valve oil inlet pipeline of magnetic valve 6；The oil-out of magnetic valve 6 with
The big pipeline of brake gear oil-feed interface 11 connection；Electrohydraulic servo valve oil return opening couples with aircraft return line.Electro-hydraulic servo
Valve 2 when not having control electric current, close by oil return opening, and oil inlet and the oil circuit connection of brake mouth are unimpeded, and electrohydraulic servo valve 2 is one
Passage.
Wheel spin-up transducer 4 is arranged on plane axletree or in brake shell, is coupled by machine driving with wheel, is felt
Electric signal output is converted to by wheel rotary speed, and by wheel rotary speed.In the present embodiment, the wheel spin-up transducer
4 are arranged on plane axletree, are driven and rotated by the hub drive pin of brake machine wheel 5.The electric interfaces of wheel spin-up transducer 4 pass through
Cable electrically couples with control box 3, and the wheel rotary speed voltage signal detected is supplied into control box, monitors brake machine wheel
5 sliding mode.
Control box 3 has brake anti-sliding control, the function of fault detect.The input of the electric interfaces of control box 3 and speed
Sensor 4 is spent by cable connection, receives the wheel speed that velocity sensor provides.The output end of the electric interfaces of control box 3
Coupled by cable with electrohydraulic servo valve 2, control signal is sent to electrohydraulic servo valve 2.Power supply needed for control box 3 is by aircraft electricity
Source system provides.
Hydraulic selector 7 uses prior art, for experiencing brake pressure, manipulates microswitch to control the disconnected of electric wiring
Open and close.The hydraulic interface of the hydraulic selector 7 is by hydraulic pressure pressure inlet and conduit with coupling the small brake gear hydraulic pressure
Pipeline connection.The electric interfaces of the hydraulic selector 7 are electrically coupled by shielding insulation wire with the electric interfaces of magnetic valve 6, tool
Body is that the microswitch of hydraulic selector 7 is connected with the electromagnet coil of magnetic valve 6, is switched on or switched off and is supplied to magnetic valve 6
The control electric current signal of electromagnet coil.
Magnetic valve 6 is arranged on the big brake gear fluid pressure line 9 of the brake mouth output of water brake valve 1 in a manner of series winding
On, the communication and disconnection that oil-feed oil circuit and fuel-displaced oil circuit are realized in electric control are changed into by hydraulic control, where controlling
Whether fluid pressure line exports and disconnects brake pressure.The magnetic valve 6 has an electric interfaces and three hydraulic interfaces.Described
Three hydraulic interfaces are magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively.Wherein：The magnetic valve oil-feed
Mouth couples with described electrohydraulic servo valve brake mouth pipeline；Magnetic valve oil-out and the big brake gear pipeline of brake machine wheel join
Connect, pass to big brake gear oil-feed interface, electromagnetic valve oil return mouth 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.
When coupling the electric interfaces of electric interfaces and hydraulic selector 7 of magnetic valve 6, by the electromagnet coil of magnetic valve 6 and hydraulic selector 7
Microswitch series connection, then be connected on power supply, control electric current letter sent after receiving the microswitch closure of hydraulic selector 7
Number.The unlatching of magnetic valve 6 is controlled by hydraulic selector 7, and the closed and disconnected of hydraulic selector 7 is controlled by the defeated of electrohydraulic servo valve 2
Go out brake pressure：When brake pressure is less than setting value, hydraulic selector 7 is not enough to promote push rod will by the piston of action of hydraulic force
Microswitch button closure is connected, and hydraulic selector 7 is still to disconnect, and magnetic valve 6 is off, magnetic valve 6 without being powered
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 7 closes electricity
Road, magnetic valve 6, which is powered, to be opened, and the oil return opening of magnetic valve 6 is closed, and oil inlet and oil-out are linked up, the fluid pressure line that magnetic valve 6 controls
It is open-minded.
The brake pressure setting value of the hydraulic selector 7 is 40~65% normal braking pressure.The present embodiment brake pressure
Setting value is 55% normal braking pressure.
Wheel velocity measuring is completed by wheel spin-up transducer 4；Anti-sliding control is completed by control box 3；The sound of electrohydraulic servo valve 2
The control electric current signal of control box 3 is answered, the brake pressure of brake machine wheel 5 is transported in output and regulation.
During work, brake selection carries out oil circuit using brake pressure control methods by magnetic valve 6 and hydraulic selector 7 and opens and closes control
System is realized：When brake pressure is less than setting value, hydraulic selector disconnects the power supply circuit of magnetic valve, and the magnetic valve 6 is not powered
And there is no hydraulic coupling output in cut-off or closed mode, magnetic valve；Conversely, hydraulic selector 7 is connected or the confession of closed electromagnetic valve 6
Circuit, the magnetic valve obtain power supply and start and be in opening, and the fluid pressure line that magnetic valve 6 controls is open-minded, and magnetic valve has
Hydraulic coupling exports.
Small brake gear fluid pressure line 8 is unblocked, and guarantee can be used in braking at any time, big brake gear fluid pressure line 9
It is conditional open-minded.So, the brake system can ensure when aircraft floor slides brake only with small brake gear, other feelings
Lower two brake gears of condition use simultaneously, realize double-brake.
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 (8)
- The optional brake system 1. a kind of aircraft single-wheel mono-/bis-is braked, the main landing gear of aircraft are equipped with a brake machine wheel, the brake Vehicle device wheel has small brake gear and big brake gear, it is characterised in that including water brake valve, magnetic valve, hydraulic selector, control Box, electrohydraulic servo valve and wheel spin-up transducer；Control box, electrohydraulic servo valve and wheel spin-up transducer therein form brake Anti-sliding control part；Magnetic valve and hydraulic selector are used to control brake machine wheel to select small brake gear operation to realize brake machine wheel Part brake, or the selection small brake gear runs simultaneously with big brake gear, to realize the whole brake of brake machine wheel Car.
- The optional brake system 2. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that water brake valve is pacified Below cockpit floor；Three hydraulic interfaces of the water brake valve are water brake valve oil inlet, water brake respectively Valve brake mouth and water brake valve oil return opening, wherein：The water brake valve oil inlet and airplane brake system pressure source pipeline Connection, the water brake valve brake mouth couple with electrohydraulic servo valve oil inlet pipeline, and the water brake valve oil return opening is with flying Machine return line couples.
- The optional brake system 3. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that the electro-hydraulic servo The electrical outlets of valve are electrically coupled by cable with control box, receive the brake anti-sliding control current signal that control box is sent；Institute Three hydraulic interfaces for stating electrohydraulic servo valve are electrohydraulic servo valve oil inlet, electrohydraulic servo valve brake mouth and electrohydraulic servo valve respectively Oil return opening；Wherein：The electrohydraulic servo valve oil inlet couples with the brake valve brake mouth pipeline of brake valve；Electrohydraulic servo valve oil return Mouth couples with aircraft return line；Electrohydraulic servo valve brake mouth connecting pipeline by electrohydraulic servo valve brake mouth respectively with wheel During two brake gear oil-feed interface pipeline connections, brake mouth connecting pipeline is set to be divided into small brake gear hydraulic tube through three-way connection Road and big brake gear fluid pressure line, small brake gear oil-feed of the small brake gear fluid pressure line therein directly with brake machine wheel Interface pipeline couples, and big brake gear fluid pressure line joins through magnetic valve and the big brake gear oil-feed interface pipeline of brake machine wheel Connect.
- The optional brake system 4. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that wheel velocity pick-up Device is arranged on plane axletree or in brake shell, is coupled by machine driving with wheel, experiences wheel rotary speed, and by machine Wheel rotary speed is converted to electric signal output；The electric interfaces of wheel spin-up transducer are electrically coupled by cable with control box, The wheel rotary speed voltage signal detected is supplied to control box, to monitor the sliding mode of brake machine wheel.
- The optional brake system 5. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that the control box The input of electric interfaces, by cable connection, receives the wheel speed that wheel spin-up transducer provides with wheel spin-up transducer Degree；The output end of the electric interfaces of control box is coupled by cable with electrohydraulic servo valve, and control signal is sent to electrohydraulic servo valve； Power supply needed for control box is provided by aircraft power system.
- The optional brake system 6. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that the hydraulic selector Hydraulic interface connected by hydraulic pressure pressure inlet and conduit with coupling the small brake gear fluid pressure line；The electricity of the hydraulic selector Gas interface is electrically coupled by shielding insulation wire with the electric interfaces of magnetic valve, specifically by the microswitch of hydraulic selector with The electromagnet coil series connection of magnetic valve, it is switched on or switched off the control electric current signal for the electromagnet coil for being supplied to magnetic valve.
- The optional brake system 7. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that the magnetic valve Electric interfaces are electrically coupled by shielding insulation wire with the electric interfaces of hydraulic selector；Connection magnetic valve electric interfaces with During the electric interfaces of hydraulic selector, the electromagnet coil of magnetic valve is connected with the microswitch of hydraulic selector, then be connected to confession On power supply, the control electric current signal sent after the microswitch closure of hydraulic selector is received；Three liquid of the magnetic valve It is magnetic valve oil inlet, magnetic valve oil-out and electromagnetic valve oil return mouth respectively to crimp mouth；Wherein：The magnetic valve oil inlet and institute The electrohydraulic servo valve brake mouth pipeline connection stated；Magnetic valve oil-out couples with the big brake gear pipeline of brake machine wheel, passes to Big brake gear oil-feed interface, electromagnetic valve oil return mouth couple with aircraft return line.
- The optional brake system 8. aircraft single-wheel mono-/bis-as claimed in claim 1 is braked, it is characterised in that the hydraulic selector Brake pressure setting value be 40%~65% normal braking pressure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610431429.5A CN106005380B (en) | 2016-06-17 | 2016-06-17 | A kind of optional brake system of aircraft single-wheel mono-/bis-brake |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610431429.5A CN106005380B (en) | 2016-06-17 | 2016-06-17 | A kind of optional brake system of aircraft single-wheel mono-/bis-brake |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106005380A CN106005380A (en) | 2016-10-12 |
| CN106005380B true CN106005380B (en) | 2017-12-12 |
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ID=57088820
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610431429.5A Expired - Fee Related CN106005380B (en) | 2016-06-17 | 2016-06-17 | A kind of optional brake system of aircraft single-wheel mono-/bis-brake |
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| Country | Link |
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| CN (1) | CN106005380B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110203379B (en) * | 2019-07-08 | 2024-02-02 | 西安航空制动科技有限公司 | Aircraft brake system with air residual pressure warning function and control method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0443213A2 (en) * | 1989-12-26 | 1991-08-28 | The Boeing Company | Improved carbon brake control for aircraft |
| CN102092373A (en) * | 2010-12-16 | 2011-06-15 | 西安航空制动科技有限公司 | Automatic braking method and device for plane |
| CN102556340A (en) * | 2012-03-03 | 2012-07-11 | 西安航空制动科技有限公司 | Airplane anti-skid brake control system and method |
| 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 |
-
2016
- 2016-06-17 CN CN201610431429.5A patent/CN106005380B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0443213A2 (en) * | 1989-12-26 | 1991-08-28 | The Boeing Company | Improved carbon brake control for aircraft |
| CN102092373A (en) * | 2010-12-16 | 2011-06-15 | 西安航空制动科技有限公司 | Automatic braking method and device for plane |
| CN102556340A (en) * | 2012-03-03 | 2012-07-11 | 西安航空制动科技有限公司 | Airplane anti-skid brake control system and method |
| 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 |
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| Publication number | Publication date |
|---|---|
| CN106005380A (en) | 2016-10-12 |
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