CN106364668B - It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake - Google Patents
It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake Download PDFInfo
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- CN106364668B CN106364668B CN201610902427.XA CN201610902427A CN106364668B CN 106364668 B CN106364668 B CN 106364668B CN 201610902427 A CN201610902427 A CN 201610902427A CN 106364668 B CN106364668 B CN 106364668B
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- emergency brake
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- hydraulic lock
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- 238000006243 chemical reaction Methods 0.000 claims description 5
- 230000000694 effects Effects 0.000 claims description 5
- 230000006837 decompression Effects 0.000 abstract description 2
- 230000005611 electricity Effects 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000003786 synthesis reaction Methods 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007935 neutral effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/42—Arrangement or adaptation of brakes
- B64C25/44—Actuating mechanisms
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Regulating Braking Force (AREA)
- Braking Systems And Boosters (AREA)
Abstract
It is a kind of to prevent the improper airplane brake system using emergency brake, including normal braking system and emergency brake system.The normal braking system includes brake instruction transducer, solenoid hydraulic lock, electrohydraulic servo valve, control box and wheel spin-up transducer.The emergency brake system includes emergency brake valve, changeover valve and switch.Normal braking system and emergency brake system are contacted and are converted by changeover valve.If present invention normal braking in emergency brake is also used, force normal braking system decompression, the normal input port of changeover valve is made not have pressure, ensure that changeover valve is transformed into emergency brake system completely, so that it is guaranteed that the implementation of emergency brake, has been inherently eliminated emergency brake and normal braking while using the emergency brake failure brought and accident potential.The present invention only increases an electric switch element in existing brake system, convenient for being reequiped in existing weaponry and equipment.
Description
Technical field
The present invention relates to airplane wheel brake systems, are specifically related to a kind of aircraft fax for ensuring emergency brake operation and stop
Vehicle system.
Background technology
Airplane wheel brake system is the important component of landing gear of aircraft, to ensure aircraft normally landing retraction
Short ground run distance, stops aircraft as early as possible, while prevents quick-fried tire of stopping.Aircraft brake-by-wire system is novel brake skill
Art expands using continuous.The brake system of aircraft brake-by-wire includes two part of normal braking and emergency brake.Emergency brake system
System after normal braking thrashing or in certain situations for using.The emergency brake and normal braking of some equipments of active service share one
It covers piston, that is, single channel cylinder seat and implements brake, changeover valve is provided between normal braking system and emergency brake system,
During emergency brake by changeover valve carry out by normal braking system to emergency brake system conversion, make wheel brake and
Emergency brake system is connected.The major advantage of this system structure design is a simplified brake gear, also mitigates weight, still,
Exist in use since human factor uses emergency brake and normal braking simultaneously or the non-solution of normal braking pressure is removed i.e.
Implement emergency brake, so as to cause changeover valve cannot be converted correctly and be parked in neutral position, block export pipeline and can not stop
Vehicle brings seriously using hidden danger, is worth noting.
Invention content
Brake accident is induced during to prevent driver's misoperation accidentally using the emergency brake system of aircraft brake to occur, this
Invention proposes a kind of anti-improper aircraft brake-by-wire system using emergency brake.
The present invention includes normal braking system and emergency brake system；The normal braking system is sensed including brake instruction
Device, solenoid hydraulic lock, electrohydraulic servo valve, control box and wheel spin-up transducer；The emergency brake system includes emergency brake
Valve, changeover valve and switch；Normal braking system and emergency brake system are contacted and are converted by changeover valve；
During normal braking, when control box is connected to the brake instruction request signal that brake instruction transducer is sent, control box
The control signal of unlocking is sent out to solenoid hydraulic lock first, solenoid hydraulic lock, which is powered, unlocks, and hydraulic power source is connected to electro-hydraulic servo
The input port of valve；Control box sends out brake control electric current signal to electrohydraulic servo valve simultaneously, and electrohydraulic servo valve exports corresponding liquid
Pressure pressure；
During emergency brake, driver pulls out emergency brake valve control crank, while normally closed switch mechanical linkage is disconnected,
So that the electrical connection circuit of switch control is go the rounds, route is disconnected, and solenoid hydraulic lock locking, electrohydraulic servo valve delivery outlet does not have
Pressure output, delivery outlet are linked up with oil return opening, and delivery outlet pressure is released completely；The normal input port of changeover valve does not have pressure,
The lower conversion completely of emergency brake pressure effect, it is ensured that the implementation of emergency brake；
The normal braking system and emergency brake system use two sets of independent pressure source systems；Solenoid hydraulic lock with
Normally closed switch is in series between control box.
In the normal braking system, brake instruction transducer is generated brake instruction voltage signal, is used by pilot control
In the brake pressure needed for control wheel normal braking；The delivery outlet of brake instruction transducer and the first input port of control box lead to
Electrical electric wire connection is crossed, brake instruction voltage signal is sent to control box；It stops with aircraft the input port of the solenoid hydraulic lock
Vehicle system pressure source pipeline couples, and the delivery outlet of solenoid hydraulic lock couples with the input port pipeline of electrohydraulic servo valve；Electro-hydraulic servo
One normal input port pipeline of valve delivery outlet and changeover valve couples；The input port of electrohydraulic servo valve and the brake mouth electricity of control box
Line connects, and receives the brake anti-sliding control current signal that control box is sent out；The input port of the solenoid hydraulic lock and control box
The electrical electric wire connection of the mouth that brakes；The unlocking of the solenoid hydraulic lock is controlled by control box；Solenoid hydraulic lock, which is powered, unlocks, electromagnetic hydraulic pressure
Lock delivery outlet has pressure output；Solenoid hydraulic lock powers off locking, the output of solenoid hydraulic lock delivery outlet no pressure.
The emergency brake system includes emergency brake valve, changeover valve and switch；Wherein：The delivery outlet of emergency brake valve
It is connected with the input port of changeover valve；The delivery outlet of changeover valve couples with wheel brake pressure inlet pipeline；Switch series connection
Between solenoid hydraulic lock and control box；The switch is closed type, with emergency brake valve control crank mechanical linkage.
The electrical connection circuit route of go the rounds of the solenoid hydraulic lock of the switch control is：Control box anode-switch-electromagnetism
Hydraulic lock-control box cathode, is grounded by control box bonding.
Wheel spin-up transducer is mounted in brake machine wheel, is rotated by machine driving with brake machine wheel；Wheel speed passes
Sensor is connect with control box electric wire, and the speed signal of brake machine wheel is provided to control box.
The present invention makes normal braking during emergency brake disable, it is ensured that answering by increasing control device sophisticated systems structure
The lower changeover valve of pressure of bringing to a halt effect is converted completely, even if emergency brake is used in combination with normal braking, changeover valve can be switched to
Emergency brake system.
In the present invention：
Brake instruction transducer generates brake instruction voltage signal, for controlling wheel normal braking by pilot control
Required brake pressure；Brake instruction transducer couples with the electrical electric wire of control box, and brake instruction voltage signal is sent to control
Box processed；
Solenoid hydraulic lock input port couples with airplane brake system pressure source pipeline, and solenoid hydraulic lock delivery outlet is watched with electro-hydraulic
The pipeline connection of valve input port is taken, electrohydraulic servo valve delivery outlet and changeover valve one input port, that is, normal mouth pipeline couple, converts
Valve delivery outlet couples with wheel brake pressure inlet pipeline；
Solenoid hydraulic lock couples with the electrical electric wire of control box；The unlocking of solenoid hydraulic lock is controlled by control box；Electromagnetic hydraulic pressure
Lock, which is powered, unlocks, and solenoid hydraulic lock delivery outlet has pressure output；Solenoid hydraulic lock powers off locking, and solenoid hydraulic lock delivery outlet is without pressure
Power exports；
Solenoid hydraulic lock is also controlled by switch；It connects between solenoid hydraulic lock and control box normally closed switch；
Emergency brake valve is used for controlling the brake pressure needed for wheel emergency brake；It emergency brake valve input port should with aircraft
Emergency stopping system pressure source pipeline couples, and emergency brake valve delivery outlet joins with the i.e. emergent mouth pipeline in another input port of changeover valve
It connects；
Electrohydraulic servo valve, control box, wheel spin-up transducer are the main accessories of electronic anti-breaking brake control；
Electrohydraulic servo valve is connect with control box electric wire, receives the brake anti-sliding control current signal that control box is sent out；In electricity
In the case of magnetic hydraulic lock is unlocked, for electrohydraulic servo valve when there is control electric current, electrohydraulic servo valve delivery outlet has pressure output, delivery outlet
The pressure size of output is directly proportional to the control electric current signal that control box is sent；Electrohydraulic servo valve is in no control electric current, electricity
Hydraulic servo delivery outlet no pressure exports；Under the non-slippery conditions of wheel, the control electric current that electrohydraulic servo valve receives is control box
The brake control electric current signal sent；It is had skidded in wheel, the control electric current that electrohydraulic servo valve receives is control box
By the current signal after brake control electric current and anti-sliding control electric current synthesis；In solenoid hydraulic lock locking, electro-hydraulic servo
Valve delivery outlet no pressure exports, and the input port cut-out of electrohydraulic servo valve, delivery outlet is linked up with oil return opening；
Wheel spin-up transducer is connect with control box electric wire, and brake machine wheel speed signal is provided to control box；Wheel speed
Sensor reflects the rotary motion state of wheel, it is existing whether monitoring brake machine wheel has skidded to detect wheel rotary speed
As；Wheel spin-up transducer is mounted in brake machine wheel, is rotated by machine driving with brake machine wheel, by the speed of brake machine wheel
It is converted to electric signal and inputs to control box, as the input of anti-sliding control, judge whether wheel has skidded by control box；If
It skids, control box, which will brake, controls electric current and anti-sliding control electric current to integrate, and reduces the control for issuing electrohydraulic servo valve
Current signal according to the wheel skidding depth, discharges water brake pressure of corresponding size, and the wheel is made to restore rotation, avoids stopping
Quick-fried tire；
Switch is connected between solenoid hydraulic lock and control box；Switch is closed type, with emergency brake valve control crank machine
Tool links；
Switching the electrical connection circuit route of go the rounds of the solenoid hydraulic lock of control is：Control box-switch-solenoid hydraulic lock-
Control box is grounded by control box bonding；
Switch forms emergency brake as controller and solenoid hydraulic lock and prevents the improper control device used, and emergency brake is answered in guarantee
Changeover valve is converted completely during vehicle, so that it is guaranteed that emergency brake can not independent reliability service by normal braking interference.
During emergency brake, driver pulls out emergency brake valve control crank, meanwhile, normally closed switch mechanical linkage is broken
It opens；At this moment, no matter normal braking system is either with or without output brake pressure, the electrical connection circuit route of go the rounds for switching control is broken
It opens, solenoid hydraulic lock locking, electrohydraulic servo valve delivery outlet does not have pressure output, and delivery outlet is linked up with oil return opening, delivery outlet pressure
It releases completely；The normal input port of changeover valve does not have pressure, is converted completely under the effect of emergency brake pressure, it is ensured that emergency brake
Implementation.
The present invention is by the switch with emergency brake valve control crank mechanical linkage, if the normal braking in emergency brake
Also it is used, forces normal braking system decompression, the normal input port of changeover valve is made not have pressure, ensure that changeover valve turns completely
Emergency brake system is changed to, so that it is guaranteed that the implementation of emergency brake, has been inherently eliminated emergency brake and normal braking simultaneously
Use the emergency brake failure brought and accident potential.The present invention only increases an electric switch member in existing brake system
Part, convenient for being reequiped in existing weaponry and equipment.
Description of the drawings
Attached drawing 1 is the structure diagram of the present invention.In figure：
1. brake instruction transducer；2. emergency brake valve；3. switch；4. control box；5. solenoid hydraulic lock；6. electro-hydraulic servo
Valve；7. changeover valve；8. wheel spin-up transducer；9. brake machine wheel.
Specific embodiment
The present embodiment is to prevent the improper brake-by-wire system using emergency brake with Mr. Yu's type machine.
The present embodiment includes normal braking system and emergency brake system.The normal braking system is passed including brake instruction
Sensor 1, solenoid hydraulic lock 5, electrohydraulic servo valve 6, control box 4 and wheel spin-up transducer 8.The emergency brake system includes should
Bring to a halt valve 2, changeover valve 7 and switch 3.Normal braking system and emergency brake system by changeover valve 7 carry out contact and
Conversion.
The normal braking system and emergency brake system use two sets of independent hydraulic pressure pressure source systems.
In the normal braking system, brake instruction transducer 1 generates brake instruction voltage signal by pilot control,
For controlling the brake pressure needed for wheel normal braking.The delivery outlet of brake instruction transducer 1 and the first input of control box 4
Mouth is coupled by electrical electric wire, and brake instruction voltage signal is sent to control box 4.Brake instruction transducer 1 and control box 4 by
Power supply is powered on machine.
The input port of the solenoid hydraulic lock 5 couples with airplane brake system pressure source pipeline, the output of solenoid hydraulic lock 5
Mouth couples with the input port pipeline of electrohydraulic servo valve 6；6 delivery outlet of electrohydraulic servo valve is managed with the normal input port of changeover valve 7 one
Road couples.The input port of electrohydraulic servo valve 6 is connect with the brake mouth electric wire of control box 4, and it is anti-skidding to receive the brake that control box 4 is sent out
Control electric current signal.
The input port of the solenoid hydraulic lock 5 couples with the electrical electric wire of brake mouth of control box 4.The solenoid hydraulic lock 5
Unlocking is controlled by control box 4；Solenoid hydraulic lock 5, which is powered, unlocks, and 5 delivery outlet of solenoid hydraulic lock has pressure output；Solenoid hydraulic lock 5
Power off locking, the output of 5 delivery outlet no pressure of solenoid hydraulic lock.
Normally closed switch 3 is in series between solenoid hydraulic lock 5 and control box 4.
Solenoid hydraulic lock is not only controlled by control box, is also controlled by the electric switch of emergency brake handle linkage.
The emergency brake system includes emergency brake valve 2, changeover valve 7 and switch 3.Wherein：Emergency brake valve 2 it is defeated
Outlet is connected with the input port of changeover valve 7；The delivery outlet of changeover valve 7 couples with wheel brake pressure inlet pipeline.It opens
3 are closed to be connected between solenoid hydraulic lock 5 and control box 4；The switch 3 is closed type, is joined with 2 control crank machinery of emergency brake valve
It is dynamic.
The electrical connection circuit route of go the rounds of the solenoid hydraulic locks 5 of 3 control of switch is：Control box anode-switch-electromagnetism
Hydraulic lock-control box cathode, is grounded by control box bonding.
Switch 3 forms emergency brake as controller and solenoid hydraulic lock 5 and prevents the improper control device used, ensures emergent
Changeover valve 7 is converted completely during brake, so that it is guaranteed that emergency brake can not independent reliability service by normal braking interference.
Solenoid hydraulic lock 5 is also controlled by switch 3.
Emergency brake valve 2 is used for controlling the brake pressure needed for wheel emergency brake；2 input port of emergency brake valve and aircraft
Emergency brake system pressure source pipeline couples, 2 delivery outlet of emergency brake valve and the i.e. emergent mouth pipe in another input port of changeover valve 7
Road couples.
The electrohydraulic servo valve 6, control box 4, wheel spin-up transducer 8 are the main accessories of electronic anti-breaking brake control.
Electrohydraulic servo valve 6 is connect with 4 electric wire of control box, receives the brake anti-sliding control current signal that control box 4 is sent out；
In the case of solenoid hydraulic lock 5 is unlocked, for electrohydraulic servo valve 6 when there is control electric current, 6 delivery outlet of electrohydraulic servo valve has pressure output,
The pressure size of delivery outlet output is directly proportional to the control electric current signal that control box 4 is sent；Electrohydraulic servo valve 6 is in no control electricity
During stream, the output of 6 delivery outlet no pressure of electrohydraulic servo valve；Under the non-slippery conditions of wheel, the control electric current of electrohydraulic servo valve reception
It is the brake control electric current signal that control box is sent；It is had skidded in wheel, the control electric current that electrohydraulic servo valve 6 receives
It is that brake is controlled the current signal after electric current and anti-sliding control electric current synthesis by control box 4；In 5 locking situation of solenoid hydraulic lock
Under, the output of 6 delivery outlet no pressure of electrohydraulic servo valve, the input port cut-out of electrohydraulic servo valve 6, delivery outlet and oil return opening are linked up；
Wheel spin-up transducer 8 is connect with 4 electric wire of control box, and the speed signal of brake machine wheel 9 is provided to control box 4；Machine
Wheel speed sensor 8 reflects the rotary motion state of wheel, whether monitoring brake machine wheel 9 goes out to detect wheel rotary speed
Existing slipping phenomenon；Wheel spin-up transducer 8 is mounted in brake machine wheel 9, is rotated, will be stopped with brake machine wheel 9 by machine driving
The rate conversion of vehicle device wheel 9 inputs to control box 4 for electric signal, as the input of anti-sliding control, judges that wheel is by control box 4
It is no to have skidded；In case of skidding, control box 4, which will brake, controls electric current and anti-sliding control electric current to integrate, and reduction is issued
The control electric current signal of electrohydraulic servo valve 6 according to the wheel skidding depth, discharges water brake pressure of corresponding size, makes the machine
Wheel restores rotation, avoids quick-fried tire of stopping；Anti-sliding control is implemented by the prior art；
During emergency brake, driver pulls out 2 control crank of emergency brake valve, meanwhile, 3 mechanical linkage of normally closed switch is broken
It opens；At this moment, no matter normal braking system is either with or without output brake pressure, the electrical connection circuits of 3 control of switch are go the rounds route quilt
It disconnects, 5 locking of solenoid hydraulic lock, 6 delivery outlet of electrohydraulic servo valve does not have pressure output, and delivery outlet is linked up with oil return opening, delivery outlet
Pressure is released completely；7 normal input port of changeover valve does not have pressure, is converted completely under the effect of emergency brake pressure, it is ensured that should
The implementation brought to a halt.
Since normal braking system is using brake valve but brake instruction transducer, this system belongs to electricity
Brake system is passed, electrohydraulic servo valve used is postiive gain valve, and is matched with solenoid hydraulic lock；During normal braking, when
When control box is connected to the brake instruction request signal that brake instruction transducer is sent, control box is sent out out first to solenoid hydraulic lock
The control signal of lock, solenoid hydraulic lock must establish lock by cable, and hydraulic power source is connected to the input port of electrohydraulic servo valve；Control box is almost same
When to electrohydraulic servo valve send out brake control electric current signal, electrohydraulic servo valve exports corresponding hydraulic pressure.
Claims (5)
1. a kind of prevent the improper aircraft brake-by-wire system using emergency brake, which is characterized in that including normal braking system and
Emergency brake system；The normal braking system includes brake instruction transducer, solenoid hydraulic lock, electrohydraulic servo valve, control box
And wheel spin-up transducer；The emergency brake system includes emergency brake valve, changeover valve and switch；Normal braking system and
Emergency brake system is contacted and is converted by changeover valve；
During normal braking, when control box is connected to the brake instruction request signal that brake instruction transducer is sent, control box is first
The control signal of unlocking is sent out to solenoid hydraulic lock, solenoid hydraulic lock, which is powered, unlocks, and hydraulic power source is connected to electrohydraulic servo valve
Input port；Control box sends out brake control electric current signal to electrohydraulic servo valve simultaneously, and electrohydraulic servo valve exports corresponding hydraulic pressure pressure
Power；
During emergency brake, driver pulls out emergency brake valve control crank, while normally closed switch mechanical linkage is disconnected so that
The electrical connection circuit route of go the rounds of switch control is disconnected, and solenoid hydraulic lock locking, electrohydraulic servo valve delivery outlet does not have pressure
Output, delivery outlet are linked up with oil return opening, and delivery outlet pressure is released completely；The normal input port of changeover valve does not have pressure, emergent
The lower conversion completely of brake pressure effect, it is ensured that the implementation of emergency brake；
The normal braking system and emergency brake system use two sets of independent pressure source systems；In solenoid hydraulic lock and control
Normally closed switch is in series between box.
2. the improper aircraft brake-by-wire system using emergency brake is prevented as described in claim 1, which is characterized in that described normal
In brake system, brake instruction transducer generates brake instruction signal, for controlling wheel normal braking institute by pilot control
The brake pressure needed；The delivery outlet of brake instruction transducer is coupled with the first input port of control box by electrical electric wire, will be stopped
Vehicle command voltage signal is sent to control box；The input port of the solenoid hydraulic lock joins with airplane brake system pressure source pipeline
It connects, the delivery outlet of solenoid hydraulic lock couples with the input port pipeline of electrohydraulic servo valve；Electrohydraulic servo valve delivery outlet and changeover valve
One normal input port pipeline connection；The input port of electrohydraulic servo valve and the brake mouth electric wire of control box connect, and receive control box
The brake anti-sliding control current signal sent out；The input port of the solenoid hydraulic lock and the electrical electric wire of the brake mouth of control box join
It connects；The unlocking of the solenoid hydraulic lock is controlled by control box；Solenoid hydraulic lock, which is powered, unlocks, and solenoid hydraulic lock delivery outlet has the pressure defeated
Go out；Solenoid hydraulic lock powers off locking, the output of solenoid hydraulic lock delivery outlet no pressure.
3. the improper aircraft brake-by-wire system using emergency brake is prevented as described in claim 1, which is characterized in that described emergent
Brake system includes emergency brake valve, changeover valve and switch；Wherein：The delivery outlet of emergency brake valve and changeover valve it is normal
Input port connects；The delivery outlet of changeover valve couples with wheel brake pressure inlet pipeline；Switch is connected on solenoid hydraulic lock
Between control box；The switch is closed type, with emergency brake valve control crank mechanical linkage.
4. the improper aircraft brake-by-wire system using emergency brake is prevented as claimed in claim 3, which is characterized in that the switch
The electrical connection circuit of the solenoid hydraulic lock of control route of go the rounds is：Control box anode-switch-solenoid hydraulic lock-control box is born
Pole is grounded by control box bonding.
5. the improper aircraft brake-by-wire system using emergency brake is prevented as described in claim 1, which is characterized in that wheel speed
Sensor is mounted in brake machine wheel, is rotated by machine driving with brake machine wheel；Wheel spin-up transducer and control box electric wire
Connection provides the speed signal of brake machine wheel to control box.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610902427.XA CN106364668B (en) | 2016-10-18 | 2016-10-18 | It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610902427.XA CN106364668B (en) | 2016-10-18 | 2016-10-18 | It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106364668A CN106364668A (en) | 2017-02-01 |
| CN106364668B true CN106364668B (en) | 2018-07-03 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610902427.XA Expired - Fee Related CN106364668B (en) | 2016-10-18 | 2016-10-18 | It is a kind of to prevent the improper aircraft brake-by-wire system using emergency brake |
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| CN (1) | CN106364668B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481764A (en) * | 2019-09-02 | 2019-11-22 | 西安航空制动科技有限公司 | The aircraft brake instruction sensor and its design method of brake electric current are controlled with stroke |
| CN110606195B (en) * | 2019-09-17 | 2024-05-24 | 西安航空制动科技有限公司 | Airplane emergency braking system and design method thereof |
| CN114313235B (en) * | 2021-12-17 | 2023-08-22 | 北京航空航天大学 | Aircraft braking system and switching method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| CN103708027A (en) * | 2012-10-09 | 2014-04-09 | 梅西耶-布加蒂-道提公司 | Electromechanical braking system architecture |
| CN203889062U (en) * | 2014-05-13 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic antiskid braking system of airplane |
| EP2871104A1 (en) * | 2013-11-07 | 2015-05-13 | Goodrich Corporation | System and method for independent braking system enablement |
| EP2899079A1 (en) * | 2014-01-22 | 2015-07-29 | The Boeing Company | Optimized real-time antiskid control initialization for travel surfaces as a function of wheel spinup |
| CN104859626A (en) * | 2015-05-28 | 2015-08-26 | 西北工业大学 | Aircraft electro hydrostatic brake actuator |
-
2016
- 2016-10-18 CN CN201610902427.XA patent/CN106364668B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN103708027A (en) * | 2012-10-09 | 2014-04-09 | 梅西耶-布加蒂-道提公司 | Electromechanical braking system architecture |
| EP2871104A1 (en) * | 2013-11-07 | 2015-05-13 | Goodrich Corporation | System and method for independent braking system enablement |
| EP2899079A1 (en) * | 2014-01-22 | 2015-07-29 | The Boeing Company | Optimized real-time antiskid control initialization for travel surfaces as a function of wheel spinup |
| CN203889062U (en) * | 2014-05-13 | 2014-10-22 | 哈尔滨飞机工业集团有限责任公司 | Hydraulic antiskid braking system of airplane |
| CN104859626A (en) * | 2015-05-28 | 2015-08-26 | 西北工业大学 | Aircraft electro hydrostatic brake actuator |
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| Publication number | Publication date |
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| CN106364668A (en) | 2017-02-01 |
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