CN209192212U - A kind of aircraft brake-by-wire system of take-off line brake - Google Patents
A kind of aircraft brake-by-wire system of take-off line brake Download PDFInfo
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- CN209192212U CN209192212U CN201821903467.7U CN201821903467U CN209192212U CN 209192212 U CN209192212 U CN 209192212U CN 201821903467 U CN201821903467 U CN 201821903467U CN 209192212 U CN209192212 U CN 209192212U
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Abstract
A kind of aircraft brake-by-wire system of 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 utility model 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, compared with conventional hydraulic brake system, brake instruction transducer is instead of water brake
Valve, airplane wheel brake pressure size are directly exported by brake instruction transducer manipulation electrohydraulic servo valve, and electrohydraulic servo valve is both
Brake control valve, and be anti-sliding control valve.This electrohydraulic servo valve is pressure postiive gain valve, in a certain range, brake pressure with
Control electric current linear proportional relationship.Aircraft is in a kind of form or shape that take-off line shutdown brake is that aircraft normal braking uses
State, only generally, take-off line brake pressure are higher than normal braking pressure.As aircraft thrust increases, aircraft stops in take-off line
Brake pressure needed for machine brakes significantly increases, and especially carbon brakes, and more normal brake pressure is doubled also by force, this is to aircraft machine
Wheel brake system brake pressure itself brings huge challenge with regard to high design and use especially high pressure electrohydraulic servo valve.Due to power
The inherent characteristic of square motor magnetic material, the brake pressure of electrohydraulic servo valve output reaches after certain value is no longer with control electric current
Linear proportional relationship increases, and into so-called saturation region, brake pressure increases slowly, or even if being further added by control electric current, stops
Vehicle pressure no longer increases.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 and take off,
Process is taken off to shorten, this is highly beneficial to military aircraft fighting capacity.Using practice discovery, existing aircraft brake-by-wire system
Uniting, reliability is low sometimes for take-off line brake, the reason is that the brake pressure that electrohydraulic servo valve exports under maximum controlling current is lower than the phase
The maximum brake pressure of the correspondence maximum controlling current of prestige, brake pressure value needed for take-off line brake is not achieved, can not meet
Growing line brake of taking off requires.Take-off line brake pressure is low, will lead to cannot reliably chomp on the binders completely,
Rolling or play occur when aircraft thrust increases, influences airborne combat training use and safe operation, for example, formation takeoff, really
Protecting 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 increases the problem of control electric current can bring torque-motor fever and power consumption.Rational deployment brake system
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 that it is low that reliability can occur for the brake of existing aircraft brake-by-wire system take-off line, the invention proposes
A kind of aircraft brake-by-wire system of 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 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.
In the present invention, motor-driven valve switches for hydraulic circuit, is the attachment for executing take-off line brake；Implement inactive
Fly 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 always with motor-driven valve
Oil outlet is kept unimpeded, and motor-driven valve just corresponds to a hydraulic channel, and motor-driven valve output the first oil inlet of motor-driven valve comes hydraulic
Pressure；After take-off line brake is implemented in starting, i.e., the electromagnet coil power of motor-driven valve when, motor-driven valve energization movement is mobile to slide
Vavle switching pressure supply coming oil oil circuit closes the first oil inlet of motor-driven valve, the second oil inlet of motor-driven valve is opened, by the second of motor-driven valve
The oil outlet of oil inlet and motor-driven valve is linked up, and motor-driven valve exports the hydraulic pressure that the second oil inlet of motor-driven valve comes；The electricity of motor-driven valve
Switching on and off for magnet coil circuit 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, and starting motor-driven valve carries out hydraulic circuit switching.The present invention passes through control box
The oil circuit switching for controlling motor-driven valve, when meeting take-off line brake condition, it is hydraulic that control box connects the progress of motor-driven valve power supply circuit
Oil circuit switching, meets the brake pressure for transporting to brake machine wheel and takes off line and brake big pressure requirements to realize, thus really
It protects and executes take-off line brake.In the case where meeting take-off line brake condition, by control box starting motor-driven valve switch in time pressure supply oil circuit to
Airplane brake system pressure source exports the take-off line brake pressure of needs.The present invention has rational design, simple and easy to do, and take-off line is stopped
Vehicle pressure can not depend on electrohydraulic servo valve, by electronic Vavle switching pressure supply oil circuit, be taken off by the offer of airplane brake system pressure source
Brake pressure needed for line brake realizes that reliable and stable line of taking off brakes, and brake pressure needed for take-off line brake is not
It is provided again 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, is not in brake
In fall pressure and take-off line brake pressure does not reach requirement value problem, effectively increase take-off line brake reliability, guarantee aircraft
It is safe and reliable to use.
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 generally not strap brake, equipped with brake dress on the wheel of two main landing gears
It sets.Two aircraft main landing gears are typically placed symmetrically in airframe two sides.The present embodiment is with one of main landing gear and peace
It fills and illustrates 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.
Claims (4)
1. a kind of aircraft brake-by-wire system of take-off line brake, 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 is passed with brake instruction transducer and wheel speed respectively
Sensor electrically couples, and receives the brake instruction voltage signal that brake instruction transducer is sent and the machine that wheel spin-up transducer provides
Wheel speed voltage signal；Control box also electrically couples with electrohydraulic servo valve, issues brake anti-sliding control electric current to electrohydraulic servo valve
Signal；Control box also electrically couples with motor-driven valve, and control motor-driven valve is powered or power-off；Electrohydraulic servo valve is arranged close to braking machine
In the aircraft main landing gear compartment of wheel on fluid pressure line；Motor-driven valve is mounted on the fluid pressure line between electrohydraulic servo valve and brake machine wheel
On.
2. a kind of aircraft brake-by-wire system of take-off line brake as described in claim 1, which is characterized in that the electro-hydraulic servo
The oil inlet of valve couples with airplane brake system pressure source pipeline；First oil inlet of the brake mouth and motor-driven valve of electrohydraulic servo valve
The connection of A pipeline；The oil return opening of electrohydraulic servo valve couples with airplane brake system oil return line；It is defeated by electrohydraulic servo valve brake mouth
The conversion of brake pressure control motor-driven valve out.
3. a kind of aircraft brake-by-wire system of take-off line brake as described in claim 1, which is characterized in that the motor-driven valve
Electric interfaces 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；It is described
First oil inlet A of motor-driven valve couples with the brake mouth pipeline of electrohydraulic servo valve, the second oil inlet B and aircraft brake of motor-driven valve
The connection of system pressure source pipeline, the oil outlet of motor-driven valve couple with the oil inlet pipeline of brake machine wheel brake gear.
4. a kind of aircraft brake-by-wire system of take-off line brake as claimed in claim 3, which is characterized in that the motor-driven valve exists
In the case where inactive implementation take-off line brake, the electromagnet coil of motor-driven valve is not powered on, the first oil inlet of motor-driven valve A always with
It is kept unimpeded between the oil outlet of motor-driven valve, the motor-driven valve is made to just correspond to a hydraulic channel, export the first oil inlet of motor-driven valve
The hydraulic pressure of mouth 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 powered dynamic
Make, mobile slide valve switches pressure supply coming oil oil circuit, closes the first oil inlet of motor-driven valve A, opens the second oil inlet B of motor-driven valve, will
Second oil inlet B of motor-driven valve and the oil outlet of motor-driven valve are linked up, and motor-driven valve exports the hydraulic pressure that motor-driven valve the second oil inlet B comes
Power；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, 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；
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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821903467.7U CN209192212U (en) | 2018-11-19 | 2018-11-19 | A kind of aircraft brake-by-wire system of take-off line brake |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821903467.7U CN209192212U (en) | 2018-11-19 | 2018-11-19 | A kind of aircraft brake-by-wire system of take-off line brake |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209192212U true CN209192212U (en) | 2019-08-02 |
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ID=67424758
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821903467.7U Expired - Fee Related CN209192212U (en) | 2018-11-19 | 2018-11-19 | A kind of aircraft brake-by-wire system of take-off line brake |
Country Status (1)
| Country | Link |
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| CN (1) | CN209192212U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319096A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
-
2018
- 2018-11-19 CN CN201821903467.7U patent/CN209192212U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109319096A (en) * | 2018-11-19 | 2019-02-12 | 西安航空制动科技有限公司 | It can ensure the aircraft brake-by-wire system and control method of take-off line brake |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190802 Termination date: 20191119 |