CN109319096A - It can ensure the aircraft brake-by-wire system and control method of take-off line brake - Google Patents
It can ensure the aircraft brake-by-wire system and control method of take-off line brake Download PDFInfo
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- CN109319096A CN109319096A CN201811377151.3A CN201811377151A CN109319096A CN 109319096 A CN109319096 A CN 109319096A CN 201811377151 A CN201811377151 A CN 201811377151A CN 109319096 A CN109319096 A CN 109319096A
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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
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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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- Regulating Braking Force (AREA)
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Abstract
A kind of aircraft brake-by-wire system and control method that can ensure take-off line brake.Control box receives the wheel velocity voltage signal that the brake instruction voltage signal that brake instruction transducer is sent and wheel spin-up transducer provide respectively；It controls box and issues brake anti-sliding control current signal to electrohydraulic servo valve；Box control motor-driven valve is controlled to be powered or power off.Motor-driven valve is mounted on the fluid pressure line between electrohydraulic servo valve and brake machine wheel.The judgement that the present invention passes through take-off line brake condition, that is, air speed and electrohydraulic servo valve brake control current signal, switch oil circuit in time with motor-driven valve, meet the brake pressure for transporting to brake machine wheel to take off line and brake big pressure requirements to realize, so that it is guaranteed that taking off line brake, it is not in fall pressure and take-off line brake pressure does not reach requirement value problem in brake, take-off line brake reliability is effectively increased, guarantees that aircraft safety reliably uses.
Description
Technical field
The present invention relates to aircraft brake-by-wire system, being specifically related to a kind of application motor-driven valve ensures take-off line braking quality
With the airplane wheel brake-by-wire system of reliability.
Background technique
Airplane wheel brake system is the composition part of modern aircraft take-off and landing device, is to take off, alighting run and ground
The basic guarantee equipment of face taxiing control safe operation, main task are to shorten ground run distance after guaranteeing aircraft landing, are made as early as possible
Aircraft stops, while preventing quick-fried tire of stopping.Brake control and anti-slip control of the airplane wheel brake system for airplane wheel
It makes, widely applied on current aircraft is electronic anti-skid braking system, and aircraft brake-by-wire system is the anti-skidding brake of aircraft electronic
The further development of vehicle system.Aircraft brake-by-wire system mainly includes brake instruction transducer, electrohydraulic servo valve, wheel speed
Sensor, antiskid braking control box (hereinafter referred to as control box), compared with conventional hydraulic brake system, brake instruction transducer
Instead of water brake valve, airplane wheel brake pressure size is directly exported by brake instruction transducer manipulation electrohydraulic servo valve,
Electrohydraulic servo valve is both brake control valve and anti-sliding control valve.This electrohydraulic servo valve is pressure postiive gain valve, in certain model
It encloses, brake pressure and control electric current linear proportional relationship.Aircraft is that aircraft normal braking uses in take-off line shutdown brake
A kind of form or state, only take-off line brake pressure is higher than normal braking pressure.As aircraft thrust increases, aircraft is taking off
Brake pressure needed for line shutdown brake significantly increases, and especially carbon brakes, and more normal brake pressure is doubled also by force, this is to winged
Machine wheel brake system brake pressure itself brings huge challenge with regard to high design and use especially high pressure electrohydraulic servo valve.By
In the inherent characteristic of torque-motor magnetic material, the brake pressure of electrohydraulic servo valve output reaches after certain value with control electric current not
It is that linear proportional relationship increases again, into so-called saturation region, brake pressure increases slowly, or even if is further added by control electricity
Stream, brake pressure no longer increase.Take-off line brake is that aircraft is saved up strength to start out, and AB takeoff likes an arrow released from the bowstring and immediately projects, empties
It takes off, takes off process to shorten, this is highly beneficial to military aircraft fighting capacity.Using practice discovery, existing aircraft fax
Reliability is low sometimes for the brake of brake system take-off line, the reason is that the brake pressure that electrohydraulic servo valve exports under maximum controlling current
Lower than the maximum brake pressure of desired corresponding maximum controlling current, brake pressure value needed for take-off line brake is not achieved is full
The not growing line brake of taking off of foot requires.Take-off line brake pressure is low, and will lead to reliably to check completely
Rolling or play occur when aircraft thrust increases for wheel, influence airborne combat training use and safe operation, for example, forming into columns
It takes off, it is ensured that take-off line brake normal reliable use is the problem of airplane design is using that must take seriously.
The design of electrohydraulic servo valve structure and material is improved, increases control electric current, it is expected to ensure that the pressure of electrohydraulic servo valve is defeated
Characteristic out expands electrohydraulic servo valve and linearly uses area, meets big pressure take-off line brake pressure requirement, still, non-linear saturation
Area still remains, and increase control electric current can bring torque-motor fever and power consumption problem.Rational deployment brake system
Design and control method will be to ensure that the feasible convenient way of take-off line brake reliability.
Xi'an Aviation Brake Technology Co., Ltd. discloses one in the innovation and creation of Patent No. 201610902427.X
Kind prevents the improper aircraft brake-by-wire system using emergency brake；It is public in the innovation and creation application No. is 201610876509.1
A kind of aircraft brake-by-wire system of brake instruction direct controlled type is opened；In the innovation and creation of Patent No. 201610436991.7
Disclose a kind of brake-by-wire system of aircraft single-wheel double-brake that can select brake modes；In Patent No.
A kind of Flight By Wire brake system that can select brake mode is disclosed in the innovation and creation of CN201610436552.6；Special
A kind of aircraft single-wheel double-brake optional Flight By Wire brake system is disclosed in the innovation and creation that benefit number is 201610436698.0
System；A kind of airplane wheel electricity that can select brake modes is disclosed in the innovation and creation of Patent No. 201610436553.0
Pass manipulation brake system；It is anti-skidding that a kind of aircraft brake-by-wire is disclosed in the innovation and creation of Patent No. 201310070226.4
Control system.But above-mentioned each innovation and creation and unresolved take-off line brake integrity problem, it equally exists because take-off line brakes
Pressure it is low and cause cannot the reliably deficiency of chomp on the binders completely, reduce the reliability of take-off line brake, can not meet day
What benefit increased takes off line brake requirement.
Xi'an Aviation Brake Technology Co., Ltd. proposes one kind in the patent of invention of Patent No. 01510152590.4
Aircraft normal braking system, the system include water brake valve, motor-driven valve and travel switch.The travel switch is mounted on hydraulic
It brakes in valve chest or shell holder, the sleeve machinery of the compression bar and water brake valve that make travel switch is crosslinked, for manipulating electricity
Dynamic valve carries out oil circuit switching.When the stroke of water brake valve cage is greater than predetermined value, motor-driven valve is controlled by travel switch, it will
The hydraulic circuit pressure supply come through the decompression of water brake valve, is switched on hydraulic brake system pressure source oil circuit, makes from liquid
The high-pressure and hydraulic pressure for pressing brake system pressure source, is directly output to wheel brake, to realize take-off line brake function.
The technical solution of the patent is suitable for conventional mechanical handling brake system, is not suitable for brake-by-wire system.
Summary of the invention
To overcome the shortcomings of to occur in existing aircraft brake-by-wire system take-off line brake, reliability is low, and the present invention proposes
A kind of aircraft brake-by-wire system and control method that can ensure take-off line brake.
The present invention includes brake instruction transducer, control box, electrohydraulic servo valve, motor-driven valve and wheel spin-up transducer.Its
In: control box electrically couples with brake instruction transducer and wheel spin-up transducer respectively, receives brake instruction transducer and sends
Brake instruction voltage signal and wheel spin-up transducer provide wheel velocity voltage signal；Control box also with electrohydraulic servo valve
Electrical connection issues brake anti-sliding control current signal to electrohydraulic servo valve.Control box also electrically couples with motor-driven valve, control electricity
Dynamic valve is powered or power-off.Electrohydraulic servo valve is arranged close in the aircraft main landing gear compartment of brake machine wheel on fluid pressure line.It is electronic
Valve is mounted on the fluid pressure line between electrohydraulic servo valve and brake machine wheel.
The oil inlet of the electrohydraulic servo valve couples with airplane brake system pressure source pipeline；The brake mouth of electrohydraulic servo valve
Couple with the first oil inlet A pipeline of motor-driven valve；The oil return opening of electrohydraulic servo valve couples with airplane brake system oil return line.It is logical
Cross the conversion of the brake pressure control motor-driven valve of electrohydraulic servo valve brake mouth output.
The motor-driven valve control terminal that the electric interfaces of the motor-driven valve pass through shielding insulation conducting wire and the electric interfaces for controlling box
Implement electrical connection；First oil inlet A of the motor-driven valve couples with the brake mouth pipeline of electrohydraulic servo valve, and the second of motor-driven valve
Oil inlet B couples with airplane brake system pressure source pipeline, the oil outlet of motor-driven valve and the oil inlet of brake machine wheel brake gear
Pipeline connection.
In the case where inactive implementation take-off line brake, the electromagnet coil of motor-driven valve is not powered on the motor-driven valve, electricity
Dynamic the first oil inlet of valve A is kept unimpeded between the oil outlet of motor-driven valve always, make the motor-driven valve just correspond to one it is hydraulic logical
Road exports the hydraulic pressure of the first oil inlet of motor-driven valve A；After take-off line brake is implemented in starting, i.e. the electromagnetism iron wire of motor-driven valve
When circle is powered, motor-driven valve energization movement, mobile slide valve switches pressure supply coming oil oil circuit, closes the first oil inlet of motor-driven valve A, opens electricity
Second oil inlet B of dynamic valve, the oil outlet of the second oil inlet B of motor-driven valve and motor-driven valve is linked up, and motor-driven valve exports motor-driven valve
The hydraulic pressure that second oil inlet B comes；Switching on and off for the electromagnet coil circuit of motor-driven valve is controlled by control box；It is taking off
Under line brake condition meets, control box connects motor-driven valve power supply circuit, makes the electromagnet coil power of motor-driven valve, starts motor-driven valve
Carry out hydraulic circuit switching.
The control process of the aircraft brake-by-wire system that can ensure take-off line brake proposed by the present invention, specific mistake
Cheng Shi:
Step 1 checks whether take-off line brake condition meets.The take-off line brake condition are as follows:
Air speed V=0；Electrohydraulic servo valve brake control current signal I > Is；Is is electrohydraulic servo valve brake control electricity
Flow signal predetermined value.
The electrohydraulic servo valve brake control current signal predetermined value Is=85%Imax；
Air speed signal is provided by wheel spin-up transducer, or is provided by aircraft FDR system；Electrohydraulic servo valve brake
Current signal is controlled to be provided by control box itself；Judge whether take-off line brake condition meets to be executed by control box；
If take-off line brake condition is satisfied, step 2 is executed；
Step 2, take-off line brake is implemented in starting.When meeting take-off line brake condition, control box connects motor-driven valve power supply
Circuit makes the electromagnet coil power of motor-driven valve, and starting motor-driven valve carries out hydraulic circuit switching, and take-off line required for exporting is stopped
Vehicle pressure completes take-off line brake task.
Check that judging whether to need to control box starts the condition that electronic Vavle switching oil circuit implements take-off line brake, by control box
It executes.
When airplane brake system pressure source uses two sets of pressure supply, the second oil inlet B and airplane brake system of motor-driven valve
Second set of pressure source pipeline connection takes off line brake pressure by second set of pressure source offer of airplane brake system；
Brake instruction transducer, controls box, and electrohydraulic servo valve and wheel spin-up transducer constitute aircraft fax electronic anti-breaking
Brake control system.Brake instruction transducer controls box, and electrohydraulic servo valve and wheel spin-up transducer are all made of the prior art.
When brake machine wheel has skidded in brake or will skid, control box implements control by scheduled control law,
Generate corresponding anti-sliding control electric current, brake instruction, that is, brake instruction control electricity of the anti-sliding control electric current and pilot control
Stream synthesis, the effective control current signal actually reduced are sent to the torque-motor coil of electrohydraulic servo valve, control electric current
Reduce, the brake mouth output hydraulic pressure pressure of electrohydraulic servo valve accordingly reduces or releases, and eliminates wheel in time and skids, prevents quick-fried wheel of stopping
Tire.
When wheel does not have skidded, effective control current signal of electrohydraulic servo valve is exactly the brake of pilot control
Instruction control electric current, driver jam on the brake instruction signal that brake pedal is heavier, stroke is bigger, and brake instruction transducer exports
Bigger, the brake pressure of the output of electrohydraulic servo valve is bigger, and aircraft brake intensity is heavier.
Shutting down when aircraft taxi in take-off line air speed is zero, and driver touches on the brake again, electro-hydraulic the watching of control box output
The brake control current signal for taking valve reaches 47mA, is greater than predetermined value 40mA, meets take-off line brake condition, and control box starts
Electronic Vavle switching pressure supply oil circuit, by airplane brake system pressure source, the present embodiment is that second set of pressure source of airplane brake system mentions
For brake pressure needed for take-off line brake, realize that reliable and stable line of taking off brakes, brake needed for take-off line brake
Pressure is no longer provided by electrohydraulic servo valve.
So far, the control process of take-off line brake is completed.
To achieve the purpose of the present invention, fluid pressure line motor-driven valve being mounted between electrohydraulic servo valve and brake machine wheel
On.Motor-driven valve has an electric interfaces and three hydraulic interfaces, and three hydraulic interfaces are the first oil inlet of motor-driven valve respectively
Mouth, the second oil inlet of motor-driven valve and motor-driven valve oil outlet.The electric interfaces of motor-driven valve are by shielding insulation conducting wire and control box
The motor-driven valve control terminal of electric interfaces implements electrical connection；First oil inlet of motor-driven valve and the brake mouth pipeline of electrohydraulic servo valve
Connection, the second oil inlet of motor-driven valve couple with airplane brake system pressure source pipeline, the oil outlet and brake machine wheel of motor-driven valve
The oil inlet pipeline of brake gear couples.
Motor-driven valve switches for hydraulic circuit, is the attachment for executing take-off line brake；In inactive implementation take-off line brake
In the case where, i.e. when the electromagnet coil of motor-driven valve is not powered on, the first oil inlet of motor-driven valve is protected with the oil outlet of motor-driven valve always
Hold unimpeded, motor-driven valve just corresponds to a hydraulic channel, and motor-driven valve exports the hydraulic pressure that the first oil inlet of motor-driven valve comes；It is opening
It is dynamic implement take-off line brake after, i.e., the electromagnet coil power of motor-driven valve when, motor-driven valve energization movement, mobile slide valve switches pressure supply
Coming oil oil circuit closes the first oil inlet of motor-driven valve, opens the second oil inlet of motor-driven valve, by the second oil inlet of motor-driven valve and electricity
The oil outlet of dynamic valve is linked up, and motor-driven valve exports the hydraulic pressure that the second oil inlet of motor-driven valve comes；The electromagnet coil electricity of motor-driven valve
Switching on and off for road is controlled by control box；Under take-off line brake condition satisfaction, control box connects motor-driven valve power supply circuit, makes
The electromagnet coil power of motor-driven valve, starting motor-driven valve carry out hydraulic circuit switching；Take-off line brake pressure required for exporting,
Complete take-off line brake task.
The present invention controls the oil circuit switching of motor-driven valve by control box, and when meeting take-off line brake condition, control box is connect
Logical motor-driven valve power supply circuit carries out hydraulic circuit switching, it is ensured that executes take-off line brake.Box is controlled to sense with brake instruction respectively
Device and wheel spin-up transducer electrically couple, and receive brake instruction voltage signal and wheel speed that brake instruction transducer is sent
The wheel velocity voltage signal that sensor provides；Control box also electrically couples with electrohydraulic servo valve, issues and stops to electrohydraulic servo valve
Vehicle anti-sliding control current signal；Control box also electrically couples with motor-driven valve, and control motor-driven valve is powered or power-off.
The present invention controls the judgement of current signal by take-off line brake condition, that is, air speed and electrohydraulic servo valve brake,
Switch oil circuit in time with motor-driven valve, meets the brake pressure for transporting to brake machine wheel and take off the big pressure requirements of line brake
It realizes, so that it is guaranteed that taking off line brake.In the case where meeting take-off line brake condition, cut in time by control box starting motor-driven valve
Pressure supply oil circuit is changed to airplane brake system pressure source, exports the take-off line brake pressure of needs.The present invention has rational design, easy to be easy
Row, take-off line brake pressure can not depend on electrohydraulic servo valve, by electronic Vavle switching pressure supply oil circuit, by airplane brake system pressure supply
Brake pressure needed for source provides take-off line brake realizes that reliable and stable line of taking off brakes, needed for take-off line brake
Brake pressure is no longer provided by electrohydraulic servo valve, it is ensured that the output of take-off line brake pressure is permanent steady, meets take-off line brake needs, no
It will appear in brake and fall pressure and take-off line brake pressure does not reach requirement value problem, it is reliable to effectively increase take-off line brake
Property, guarantee that aircraft safety reliably uses.
Detailed description of the invention
Attached drawing 1 is the aircraft brake-by-wire system figure for ensuring take-off line brake of the invention；
In figure:
1. brake instruction transducer；2. controlling box；3. electrohydraulic servo valve；4. motor-driven valve；5. wheel spin-up transducer；6. stopping
Vehicle device wheel.
Specific embodiment
Referring to Fig. 1.Aircraft nose landing gear wheel not strap brake is furnished with brake gear on the wheel of two main landing gears.
Two aircraft main landing gears are typically placed symmetrically in airframe two sides.The present embodiment is with one of main landing gear and installation one
Illustrate the present invention for a wheel.
What the present embodiment proposed ensures that the aircraft brake-by-wire system of take-off line brake includes brake instruction transducer 1, control
Box 2, electrohydraulic servo valve 3, motor-driven valve 4 and wheel spin-up transducer 5 processed.Wherein:
Control box 2 electrically couples with brake instruction transducer 1 and wheel spin-up transducer 5 respectively, receives brake instruction and passes
The wheel velocity voltage signal that the brake instruction voltage signal and wheel spin-up transducer 5 that sensor 1 is sent provide；Control box 2 also
Electrically couple with electrohydraulic servo valve 3, issues brake anti-sliding control current signal to electrohydraulic servo valve 3.Control box 2 is gone back and motor-driven valve
4 electrical connections, control motor-driven valve 4 is powered or power-off.
Control box 2 is mounted in aircraft main landing gear compartment, by power supply power supply on aircraft.The control box 2 is digital, tool
There are antiskid brake control and take-off line brake function.
Brake instruction transducer 1 is mounted on cockpit floor in the following, being manipulated by driver to it.Brake instruction transducer 1
Operating voltage is by power supply on machine.
Electrohydraulic servo valve 3 is arranged close in the aircraft main landing gear compartment of brake machine wheel 6 on fluid pressure line.Electrohydraulic servo valve
3 oil inlet couples with airplane brake system pressure source pipeline；First oil inlet of the brake mouth and motor-driven valve 4 of electrohydraulic servo valve 3
Mouth A pipeline connection；The oil return opening of electrohydraulic servo valve 3 couples with airplane brake system oil return line.It is braked by electrohydraulic servo valve 3
The conversion of the brake pressure control motor-driven valve of mouth output.
Wheel spin-up transducer 5 is mounted on plane axletree, is coupled by machine driving with brake machine wheel 6.
Motor-driven valve 4 is mounted on the fluid pressure line between electrohydraulic servo valve 3 and brake machine wheel 6.Motor-driven valve 4 have one it is electrical
Interface and three hydraulic interfaces, three hydraulic interfaces are 4 first oil inlet A of motor-driven valve, 4 second oil inlet of motor-driven valve respectively
Mouth B and 4 oil outlet of motor-driven valve.The electric interfaces of motor-driven valve 4 by shielding insulation conducting wire with control box 2 electric interfaces it is electronic
Valve control terminal implements electrical connection；First oil inlet A of motor-driven valve 4 couples with the brake mouth pipeline of electrohydraulic servo valve 3, motor-driven valve
4 the second oil inlet B couples with airplane brake system pressure source pipeline, the oil outlet and 6 brake gear of brake machine wheel of motor-driven valve 4
Oil inlet pipeline connection.
The motor-driven valve uses the prior art, switches for hydraulic circuit, is the attachment for executing take-off line brake.The electricity
Dynamic valve 4 includes electromagnet and slide valve；Motor-driven valve 4 is in the case where inactive implementation take-off line brake, i.e. the electromagnet of motor-driven valve 4
When coil is not powered on, 4 first oil inlet A of motor-driven valve is kept unimpeded between the oil outlet of motor-driven valve 4 always, makes the motor-driven valve 4
A hydraulic channel is just corresponded to, the hydraulic pressure of 4 first oil inlet A of motor-driven valve is exported；After take-off line brake is implemented in starting,
I.e. the electromagnet coil power of motor-driven valve 4 when, 4 energization of motor-driven valve movement, mobile slide valve switches pressure supply coming oil oil circuit, closes electronic
4 first oil inlet A of valve opens the second oil inlet B of motor-driven valve 4, by the fuel-displaced of the second oil inlet B of motor-driven valve 4 and motor-driven valve 4
Oral groove is logical, and motor-driven valve 4 exports the hydraulic pressure that 4 second oil inlet B of motor-driven valve comes；The electromagnet coil circuit of motor-driven valve 4 connects
On and off is opened to be controlled by control box 2；Under take-off line brake condition satisfaction, control box 2 connects motor-driven valve power supply circuit, makes electronic
The electromagnet coil power of valve 4, starting motor-driven valve 4 carry out hydraulic circuit switching.
The take-off line brake condition are as follows:
Air speed is zero, i.e. V=0,
Electrohydraulic servo valve brake control current signal I is greater than predetermined value Is, i.e. I > Is；Is is electrohydraulic servo valve brake control
Current signal predetermined value processed.
The take-off line brake that electrohydraulic servo valve brake control current signal predetermined value Is is 85% is corresponding electro-hydraulic to be watched
Take valve brake control current signal maximum value, i.e. Is=85%Imax.
Air speed signal is provided by wheel spin-up transducer 5, or is provided by aircraft FDR system；Electrohydraulic servo valve brake
Current signal is controlled to be provided by control box 2 itself.
The present embodiment also proposed a kind of control process for ensuring take-off line brake, comprising:
The first step checks whether take-off line brake condition meets.The take-off line brake condition are as follows:
Air speed is zero, i.e. V=0；
Electrohydraulic servo valve brake control current signal I is greater than predetermined value Is, i.e. I > Is；
The take-off line brake that electrohydraulic servo valve brake control current signal predetermined value Is is 85% is corresponding electro-hydraulic to be watched
Take valve brake control current signal maximum value, i.e. Is=85%Imax；
Air speed signal is provided by wheel spin-up transducer, or is provided by aircraft FDR system；Electrohydraulic servo valve brake
Current signal is controlled to be provided by control box itself；Judge whether take-off line brake condition meets to be executed by control box；
If take-off line brake condition is satisfied, second step is executed；
Take-off line brake is implemented in second step, starting.When meeting take-off line brake condition, control box connects motor-driven valve power supply
Circuit makes the electromagnet coil power of motor-driven valve, and starting motor-driven valve carries out hydraulic circuit switching, and take-off line required for exporting is stopped
Vehicle pressure completes take-off line brake task.
In the present embodiment, the electrohydraulic servo valve brake control current signal predetermined value Is is 40mA, air speed signal
It is provided by wheel spin-up transducer 5.
Check that judging whether to need to control box 2 starts the condition that motor-driven valve 4 switches oil circuit implementation take-off line brake, by controlling
Box 2 executes.
When airplane brake system pressure source uses two sets of pressure supply, the second oil inlet B and airplane brake system of motor-driven valve 4
Second set of pressure source pipeline connection takes off line brake pressure by second set of pressure source offer of airplane brake system；
In the present embodiment, airplane brake system pressure source uses two sets, the second oil inlet B and aircraft brake of motor-driven valve 4
Second set of pressure source pipeline connection of system, second set of pressure source of airplane brake system provide 24MPa and take off line brake pressure；
Brake instruction transducer 1, control box 2, electrohydraulic servo valve 3 and wheel spin-up transducer 5 constitute aircraft fax electronics
Antiskid brake control system.Brake instruction transducer 1, control box 2, electrohydraulic servo valve 3 and wheel spin-up transducer 5 are all made of existing
There is technology.
When brake machine wheel 6 has skidded in brake or will skid, control box 2 implements control by scheduled control law
System generates corresponding anti-sliding control electric current, brake instruction, that is, brake instruction control electricity of described, control electric current and pilot control
Stream synthesis, the effective control current signal actually reduced are sent to the torque-motor coil of electrohydraulic servo valve 3, control electric current
Reduce, the brake mouth output hydraulic pressure pressure of electrohydraulic servo valve 3 accordingly reduces or releases, and eliminates wheel in time and skids, prevents from stopping quick-fried
Tire.When wheel does not have skidded, effective control current signal of electrohydraulic servo valve 3 is exactly the brake instruction of pilot control
Electric current is controlled, driver jams on that brake pedal is heavier, stroke is bigger, and the brake instruction signal that brake instruction transducer 1 exports is got over
Greatly, the brake pressure of the output of electrohydraulic servo valve 3 is bigger, and aircraft brake intensity is heavier.
Aircraft brake-by-wire anti-sliding control uses the prior art.
In the present embodiment, take-off line brake operating system is made of control box 2, motor-driven valve 4 and wheel spin-up transducer 5.
Shutting down when aircraft taxi in take-off line air speed is zero, and driver touches on the brake again, electro-hydraulic the watching of the control output of box 2
The brake control current signal for taking valve 3 reaches 47mA, is greater than the present embodiment predetermined value 40mA, meets take-off line brake condition, controls
Box 2 processed starts motor-driven valve 4 and switches pressure supply oil circuit, and by airplane brake system pressure source, the present embodiment is airplane brake system the
Brake pressure needed for two sets of pressure sources provide take-off line brake realizes that reliable and stable line of taking off brakes, and take-off line is stopped
Brake pressure needed for vehicle is no longer provided by electrohydraulic servo valve 3.
The motor-driven valve 4 uses the prior art.
Claims (5)
1. one kind can ensure take-off line brake aircraft brake-by-wire system, which is characterized in that including brake instruction transducer,
Control box, electrohydraulic servo valve, motor-driven valve and wheel spin-up transducer；Wherein: control box respectively with brake instruction transducer and machine
Wheel speed sensor electrically couples, and receives brake instruction voltage signal and wheel spin-up transducer that brake instruction transducer is sent
The wheel velocity voltage signal of offer；Control box also electrically couples with electrohydraulic servo valve, and it is anti-skidding to issue brake to electrohydraulic servo valve
Control current signal；Control box also electrically couples with motor-driven valve, and control motor-driven valve is powered or power-off；Electrohydraulic servo valve, which is mounted on, to be leaned on
In the aircraft main landing gear compartment of nearly brake machine wheel on fluid pressure line；Motor-driven valve is mounted between electrohydraulic servo valve and brake machine wheel
On fluid pressure line.
2. can ensure the aircraft brake-by-wire system of take-off line brake as described in claim 1, which is characterized in that described electro-hydraulic
The oil inlet of servo valve couples with airplane brake system pressure source pipeline；Electrohydraulic servo valve brake mouth and motor-driven valve first into
The connection of hydraulic fluid port A pipeline；The oil return opening of electrohydraulic servo valve couples with airplane brake system oil return line；It is braked by electrohydraulic servo valve
The conversion of the brake pressure control motor-driven valve of mouth output.
3. can ensure the aircraft brake-by-wire system of take-off line brake as described in claim 1, which is characterized in that described electronic
The electric interfaces of valve are electrically coupled by shielding insulation conducting wire with the implementation of the motor-driven valve control terminal of the electric interfaces of anti-sliding control box；
First oil inlet A of the motor-driven valve couples with the brake mouth pipeline of electrohydraulic servo valve, the second oil inlet B and aircraft of motor-driven valve
The connection of brake system pressure source pipeline, the oil outlet of motor-driven valve couple with the oil inlet pipeline of brake machine wheel brake gear.
4. can ensure the aircraft brake-by-wire system of take-off line brake as claimed in claim 3, which is characterized in that described electronic
In the case where inactive implementation take-off line brake, the electromagnet coil of motor-driven valve is not powered on valve, and motor-driven valve the first oil inlet A begins
It is kept unimpeded between end and the oil outlet of motor-driven valve, the motor-driven valve is made to just correspond to a hydraulic channel, export motor-driven valve first
The hydraulic pressure of oil inlet A；After take-off line brake is implemented in starting, i.e., the electromagnet coil power of motor-driven valve when, motor-driven valve is logical
Electronic work, mobile slide valve switch pressure supply coming oil oil circuit, close the first oil inlet of motor-driven valve A, open the second oil inlet of motor-driven valve
B links up the oil outlet of the second oil inlet B of motor-driven valve and motor-driven valve, and motor-driven valve exports the liquid that motor-driven valve the second oil inlet B comes
Pressure pressure；Switching on and off for the electromagnet coil circuit of motor-driven valve is controlled by control box；Under take-off line brake condition satisfaction,
It controls box and connects motor-driven valve power supply circuit, make the electromagnet coil power of motor-driven valve, starting motor-driven valve carries out hydraulic circuit switching.
5. can ensure the control process of the aircraft brake-by-wire system of take-off line brake, feature described in a kind of claim 1
It is, detailed process is:
Step 1 checks whether take-off line brake condition meets；The take-off line brake condition are as follows:
Air speed V=0；Electrohydraulic servo valve brake control current signal I > Is；Is is electrohydraulic servo valve brake control electric current letter
Number predetermined value；
The electrohydraulic servo valve brake control current signal predetermined value Is=85%Imax；
Air speed signal is provided by wheel spin-up transducer, or is provided by aircraft FDR system；Electrohydraulic servo valve brake control
Current signal is provided by control box itself；Judge whether take-off line brake condition meets to be executed by control box；
If take-off line brake condition is satisfied, step 2 is executed；
Step 2, take-off line brake is implemented in starting；When meeting take-off line brake condition, control box connects motor-driven valve power supply circuit,
Make the electromagnet coil power of motor-driven valve, starting motor-driven valve carries out hydraulic circuit switching, the brake pressure of take-off line required for exporting
Power completes take-off line brake task；
Check that judging whether to need to control box starts the condition that electronic Vavle switching oil circuit implements take-off line brake, is held by control box
Row；
When airplane brake system pressure source uses two sets of pressure supply, the second oil inlet B and airplane brake system second of motor-driven valve
The connection of pressure source pipeline is covered, line brake pressure is taken off by second set of pressure source offer of airplane brake system；Brake instruction passes
Sensor, anti-sliding control box, electrohydraulic servo valve and wheel spin-up transducer constitute aircraft fax electronic anti-breaking brake control system；It stops
Vehicle instruction sensor, anti-sliding control box, electrohydraulic servo valve and wheel spin-up transducer are all made of the prior art；
When brake machine wheel has skidded in brake or will skid, anti-sliding control box implements control by scheduled control law,
Generate corresponding anti-sliding control electric current, brake instruction, that is, brake instruction control electricity of the anti-sliding control electric current and pilot control
Stream synthesis, the effective control current signal actually reduced are sent to the torque-motor coil of electrohydraulic servo valve, control electric current
Reduce, the brake mouth output hydraulic pressure pressure of electrohydraulic servo valve accordingly reduces or releases, and eliminates wheel in time and skids, prevents quick-fried wheel of stopping
Tire；
When wheel does not have skidded, effective control current signal of electrohydraulic servo valve is exactly the brake instruction of pilot control
Electric current is controlled, driver jams on that brake pedal is heavier, stroke is bigger, and the brake instruction signal of brake instruction transducer output is got over
Greatly, the brake pressure of the output of electrohydraulic servo valve is bigger, and aircraft brake intensity is heavier；
Shutting down when aircraft taxi in take-off line air speed is zero, and driver touches on the brake again, the electrohydraulic servo valve of control box output
Brake control current signal reach 47mA, be greater than predetermined value 40mA, meet take-off line brake condition, control box starts electronic
Vavle switching pressure supply oil circuit, by airplane brake system pressure source, the present embodiment provides for second set of pressure source of airplane brake system
Brake pressure needed for fly line brake realizes that reliable and stable line of taking off brakes, brake pressure needed for take-off line brake
No longer provided by electrohydraulic servo valve；
So far, the control process of take-off line brake is completed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811377151.3A CN109319096A (en) | 2018-11-19 | 2018-11-19 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811377151.3A CN109319096A (en) | 2018-11-19 | 2018-11-19 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109319096A true CN109319096A (en) | 2019-02-12 |
Family
ID=65258447
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811377151.3A Pending CN109319096A (en) | 2018-11-19 | 2018-11-19 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
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| CN (1) | CN109319096A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111516861A (en) * | 2020-04-22 | 2020-08-11 | 西安航空制动科技有限公司 | Double-channel multifunctional integrated brake device |
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| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
| CN104787310A (en) * | 2015-04-01 | 2015-07-22 | 西安航空制动科技有限公司 | Normal brake system used for airplane and having take-off line brake capability |
| CN105905281A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Airplane wheel fly-by-wire operation brake system capable of selecting braking modes |
| CN106394525A (en) * | 2016-10-08 | 2017-02-15 | 西安航空制动科技有限公司 | Airplane telex brake system directly controlled by brake instruction |
| CN209192212U (en) * | 2018-11-19 | 2019-08-02 | 西安航空制动科技有限公司 | A kind of aircraft brake-by-wire system of take-off line brake |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104760692A (en) * | 2015-04-01 | 2015-07-08 | 西安航空制动科技有限公司 | Normal aircraft brake system |
| CN104787310A (en) * | 2015-04-01 | 2015-07-22 | 西安航空制动科技有限公司 | Normal brake system used for airplane and having take-off line brake capability |
| CN105905281A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Airplane wheel fly-by-wire operation brake system capable of selecting braking modes |
| CN106394525A (en) * | 2016-10-08 | 2017-02-15 | 西安航空制动科技有限公司 | Airplane telex brake system directly controlled by brake instruction |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111516861A (en) * | 2020-04-22 | 2020-08-11 | 西安航空制动科技有限公司 | Double-channel multifunctional integrated brake device |
| CN111516861B (en) * | 2020-04-22 | 2022-11-18 | 西安航空制动科技有限公司 | Double-channel multifunctional integrated brake device |
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