CN103158867A - Airplane electrical signal transmission brake antiskid control system - Google Patents
Airplane electrical signal transmission brake antiskid control system Download PDFInfo
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- CN103158867A CN103158867A CN2013100702264A CN201310070226A CN103158867A CN 103158867 A CN103158867 A CN 103158867A CN 2013100702264 A CN2013100702264 A CN 2013100702264A CN 201310070226 A CN201310070226 A CN 201310070226A CN 103158867 A CN103158867 A CN 103158867A
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Abstract
The invention relates to an airplane electrical signal transmission brake antiskid control system. When brake is carried out, an electro hydraulic servo valve can not output brake pressure, a control box emits a control signal to an electromagnetic hydraulic lock, the electromagnetic hydraulic lock unlocks by energization, the hydraulic power source is switched on, and the brake is carried out on a brake machine wheel with maximum brake pressure. During a brake process, if the machine wheel slips, the control box controls the electromagnetic valve for energization to release pressure. The system is simple and easy to be carried out, the reliability and security of the brake system operation can be greatly increased during taking off, landing rollout processes, the work load of a driver is reduced, even the electro hydraulic servo valve generates fault, the tire burst can be effectively avoided, and the airplane usage safety is ensured.
Description
Technical field
The present invention relates to a kind of aircraft fax brake antiskid control system, still have the aircraft fax brake antiskid control system of fail safe function when specifically relating to a kind of electrohydraulic servo valve fault.
Background technology
The airplane wheel brake system is the component part of present generation aircraft take-off and landing device, to take off, alighting run the basic guarantee equipment that moves with the ground taxi manoeuvring safety, in order to guarantee shortening ground run distance after aircraft landing, aircraft is stopped, quick-fried tire simultaneously prevents from stopping.Modern Advanced Aircraft widespread use electronic anti-breaking brake control system, and with traditional hydraulic pressure drive control system brake, develop into by electric wire and control brake, be i.e. fax brake.Under the Flight By Wire mode, the brake instruction sensor has replaced the water brake valve.The basic comprising of aircraft fax brake antiskid control system comprises brake instruction sensor, speed sensor, control capsule and four annexes of electrohydraulic servo valve.The brake instruction sensor is a variable potentiometer, by pilot control, and output brake instruction electric signal, the brake of operating aircraft.Particularly, when brake, control capsule sends brake according to the brake command voltage signal that receives to electrohydraulic servo valve and controls current signal, controls the required brake pressure of electrohydraulic servo valve output, leads to wheel brake, realizes the brake of wheel is controlled.Electrohydraulic servo valve is the postiive gain valve, and the control electric current that its torque motor coil passes through is larger, and the brake pressure of electrohydraulic servo valve output is larger, controls electric current and brake pressure linear in efficient working range, and is corresponding one by one.For fax behaviour brake, brake and anti-skidding control are all carried out by electrohydraulic servo valve.
Speed sensor and braking machine wheel mechanical contact, and in order to detect the wheel rotative speed, provide the wheel speed signal to control capsule, the state that rotatablely moves of reflection wheel, and whether monitoring brake wheel skidding occurs.After control capsule is received the wheel speed signal, usually it and aircraft datum velocity are compared, whether wheel is skidded or be about to occur skid judges.If think that wheel skids, control capsule sends anti-skidding control current signal to electrohydraulic servo valve immediately, i.e. the pine control current signal of stopping discharges the water brake pressure of corresponding size according to skid level, make this wheel recover to rotate, the quick-fried tire of avoiding stopping.At this moment, control capsule sends to the control current signal of electrohydraulic servo valve, and actual is that electric current and the effective control current signal of anti-skidding control current both after comprehensive are controlled in brake.
Electrohydraulic servo valve is to implement the crucial annex of servocontrolled, and is very big to the Performance And Reliability safety effects of electronic anti-breaking brake control system.Because the high precision construction features of the spray block valve that forms electrohydraulic servo valve and guiding valve have determined that it is to the sensivity of environment for use, easily be subject to the infringement of pollutants in fluid in actual use and reduce performance, even loss of function, for example, it is stuck that guiding valve clamping stagnation or moment appear, nozzle blocks, the quick-fried tire or gun off the runway of usually causing stopping, the sign that causes the accident or serious consequence.And in sliding race process particularly high regime use artificial the releasing to drag the reliability of tire too poor, therefore, just in case the electro-hydraulic servo defective valve occurs, how to guarantee that antiskid brake control system can reliability service be still that engineering staff need to be in the face of the problem of solution.
Summary of the invention
For overcoming the deficiency of the reliability poor stability that exists in prior art, the present invention proposes a kind of aircraft fax brake antiskid control system.
The present invention includes brake instruction sensor, control capsule, electrohydraulic servo valve, solenoid valve, brake wheel, speed sensor, solenoid hydraulic lock and brake pressure sensor.The input end of control capsule receives respectively brake command voltage signal, the wheel speed signal of speed sensor transmission and the brake pressure signal that brake pressure sensor sends that the brake instruction sensor sends.The mouth of control capsule sends brake and anti-skidding control current signal, sends energising pressure release control signal and send to solenoid hydraulic lock the control signal of delivery pressure of unblanking of switching on to solenoid valve to electrohydraulic servo valve respectively.
The oil inlet of electrohydraulic servo valve, brake mouth and return opening connect by pipeline with oil inlet and the airplane brake system oil return pipe of aircraft pressure source, solenoid valve respectively.
The oil inlet of solenoid hydraulic lock connects by pipeline with the oil inlet of electrohydraulic servo valve; The brake mouth of solenoid hydraulic lock connects to the pipeline between the oil inlet of solenoid valve with the brake mouth of electrohydraulic servo valve, makes the voltage supply pipeline of solenoid hydraulic lock in parallel with the voltage supply pipeline of electrohydraulic servo valve.
The oil inlet of solenoid valve, brake mouth and return opening connect by pipeline with the brake mouth of electrohydraulic servo valve, brake gear oil inlet and the aircraft oil return pipe of brake wheel respectively.
The electric interfaces of described speed sensor, electrohydraulic servo valve, solenoid hydraulic lock, solenoid valve, brake pressure sensor connects with control capsule is electric respectively.
Described control capsule receives after brake command voltage signal through processing, current signal is controlled in torque motor coil output brake to electrohydraulic servo valve, this brake is controlled current signal and is directly proportional to the brake command signal, by the corresponding brake pressure of electrohydraulic servo valve output, the brake wheel is implemented brake, aircraft is slowed down.Control capsule is the wheel speed signal that sends of inbound pacing sensor also, through processing, the sliding mode of brake wheel is judged, and then implement anti-skidding control.
In anti-skidding control, when electrohydraulic servo valve does not discharge brake pressure, send control signal by control capsule to solenoid valve, make solenoid valve energising pressure release, remove the slipping state of brake wheel.
When brake, when electrohydraulic servo valve is not exported brake pressure, send control signal by control capsule to solenoid hydraulic lock, the solenoid hydraulic lock energising is unblanked, connect hydraulic power source, with the brake pressure of maximum, the brake wheel is implemented brake.In brake process, if wheel skids, control solenoid valve energising pressure release by control capsule.
The present invention be in the situation that the electro-hydraulic servo defective valve can be guaranteed the antiskid braking control system for airplane reliability service, and can automatically transfer standby brake mode to by current normal braking pattern, and do not need the chaufeur intervention, to alleviate the workload of chaufeur.Simultaneously, the present invention can in the situation that the electro-hydraulic servo defective valve records the fault condition mode in such circumstances of electrohydraulic servo valve automatically, be convenient to maintenance after flight personnel troubleshooting maintenance.
In the present invention, solenoid valve is connected on hydraulic tubing between electrohydraulic servo valve and wheel brake, and solenoid hydraulic lock is in parallel with electrohydraulic servo valve.For determining whether electrohydraulic servo valve breaks down, on the hydraulic tubing of the brake mouth of electrohydraulic servo valve, brake pressure sensor is set.
The effect of solenoid hydraulic lock is that energising is unblanked, output hydraulic pressure pressure; The outage locking, the cutting-off liquid pressure pressure.Solenoid valve pressure release when energising, and often open when not switching on, only play the hydraulic channel effect.Electrohydraulic servo valve is the normal braking passage, and solenoid hydraulic lock and solenoid valve consist of standby brake passage.Under the electrohydraulic servo valve reference performance, brake and anti-skidding control are completed by electrohydraulic servo valve; Under electrohydraulic servo valve broke down situation, brake and anti-skidding control were completed by solenoid hydraulic lock and solenoid valve.
The brake instruction sensor is arranged on below the driving compartment base plate, with the pedal mechanism mechanical attachment, it is handled to jamming on brake pedal by chaufeur, under step on heavylier, stroke is larger, the brake command voltage signal value of brake instruction sensor output is larger.The brake instruction sensor has an electric interfaces, connects by cable and control capsule are electric, and the command voltage signal that will brake sends to control capsule.The required power supply of brake instruction sensor work is provided by machine power source system by cable.
Control capsule is used respectively cable connection with brake instruction sensor, electrohydraulic servo valve, speed sensor, brake pressure sensor, solenoid hydraulic lock and solenoid valve, receive brake command signal, wheel speed signal and the brake pressure signal of brake instruction sensor, speed sensor and brake pressure sensor input, to electrohydraulic servo valve, solenoid hydraulic lock and solenoid valve send control signal.
The solenoid hydraulic lock energising is unblanked, and makes brake mouthful unlatching, output hydraulic pressure pressure; Locking after outage, the brake mouth is closed, the output of cutting-off liquid pressure pressure.The solenoid valve energising, oil inlet is closed, and simultaneously, brake mouth and return opening are linked up pressure release.The solenoid valve outage, return opening is closed, and oil inlet is logical with the brake oral groove, therefore, is a brake passage after the solenoid valve outage.
The characteristics that have one-to-one relationship according to the brake pressure of the control electric current that inputs to electrohydraulic servo valve and electrohydraulic servo valve output, the corresponding brake pressure of control current signal that the brake pressure that detects and control capsule are issued electrohydraulic servo valve compares, can judge the running state of electrohydraulic servo valve, namely whether occur to brake and the fault that can not get off the brakes.If the brake pressure that the brake pressure sensor on electrohydraulic servo valve brake mouthful pipeline detects, the permanent corresponding brake pressure of control current signal greater than electrohydraulic servo valve, namely think not discharge the brake pressure fault when skidding appears in electrohydraulic servo valve, and by control capsule or fly to join system log (SYSLOG).If the brake pressure that the brake pressure sensor on electrohydraulic servo valve brake mouthful pipeline detects, the permanent corresponding brake pressure of control current signal less than electrohydraulic servo valve, namely think and do not export the brake pressure fault when brake appears in electrohydraulic servo valve, and by control capsule or fly to join system log (SYSLOG).
When not discharging the brake pressure fault when skidding appears in electrohydraulic servo valve, send control signal by control capsule to solenoid valve, make solenoid valve energising pressure release; When not exporting the brake pressure fault when brake appears in electrohydraulic servo valve, send control signal by control capsule to solenoid hydraulic lock, the solenoid hydraulic lock energising is unblanked, the brake mouth is opened, output hydraulic pressure pressure is implemented brake.Brake in this case if wheel skids, is controlled solenoid valve energising pressure release by control capsule.
Technique scheme because the present invention takes makes the present invention have system simple and easy to do, can significantly improve aircraft in the characteristics of taking off, alightinging run the safety of middle brake system reliability of operation.Aircraft fax brake antiskid control system of the present invention has alleviated the workload of chaufeur, even the electrohydraulic servo valve et out of order, the quick-fried tire of effectively avoiding stopping has been guaranteed aircraft utilization safety.
Description of drawings
Accompanying drawing 1 is aircraft fax brake antiskid control system structural representation of the present invention.
Accompanying drawing 2 is control flow charts of the present invention.In figure:
1. brake instruction sensor; 2. control capsule; 3. electrohydraulic servo valve; 4. solenoid valve; 5. brake wheel; 6. speed sensor; 7. solenoid hydraulic lock; 8. brake pressure sensor.
The specific embodiment
The present embodiment describes technical scheme of the present invention in detail by the control to an Aircraft Main alighting gear brake wheel.
The present embodiment comprises brake instruction sensor 1, control capsule 2, electrohydraulic servo valve 3, solenoid valve 4, brake wheel 5, speed sensor 6, solenoid hydraulic lock 7 and brake pressure sensor 8.
Brake instruction sensor 1 is arranged on below the driving compartment base plate, with the pedal mechanism mechanical attachment, by the chaufeur pedal that touches on the brake, it is handled, and produces brake command voltage signal.Brake instruction sensor 1 has an electric interfaces, connects with control capsule 2 is electric by cable, and the command voltage signal that will brake sends to control capsule 2.The required operating voltage of brake instruction sensor 1 can be provided by control capsule 2.
Speed sensor 6 is arranged on plane axletree, connect with brake wheel 5 by the trundle on brake wheel 5, brake wheel 5 drives speed sensor 6 when rotating rotor rotates, and the rotative speed of impression brake wheel 5 is converted to electric signal output with the wheel rotative speed.Speed sensor 6 has an electric interfaces, connects with control capsule 2 is electric by cable, and the wheel rotational speed signal that detects is offered control capsule 2.
Electrohydraulic servo valve 3 has an electrical outlets and three hydraulic interfaces: oil inlet, brake mouth and return opening, and electrical outlets is implemented electric connections by connectorized cable and control capsule 2, receives the anti-skidding control current signal that control capsule 2 is sent; Oil inlet connects with aircraft pressure source pipeline; The brake mouth connects with the oil inlet pipeline of solenoid valve 4; Return opening connects with the airplane brake system oil return line, passes to oil sump tank.
Solenoid hydraulic lock 7 has an electric interfaces and two hydraulic interfaces: oil inlet, brake mouth.The electric interfaces of solenoid hydraulic lock 7 is implemented electric connections by cable and control capsule 2, receives the unblank control signal of delivery pressure of energising that control capsule 2 sends.The hydraulic tubing at the oil inlet place of the oil inlet of solenoid hydraulic lock 7 and electrohydraulic servo valve 3 connects, the brake mouth of solenoid hydraulic lock 7 connects to the pipeline between the oil inlet of solenoid valve 4 with the brake mouth of electrohydraulic servo valve 3, that is to say, the voltage supply pipeline of solenoid hydraulic lock 7 is in parallel with the voltage supply pipeline of electrohydraulic servo valve 3.Solenoid hydraulic lock 7 energisings are unblanked, and make brake mouthful unlatching, output hydraulic pressure pressure; Locking after outage, the brake mouth is closed, the output of cutting-off liquid pressure pressure.
Solenoid valve 4 has an electric interfaces and three hydraulic interfaces: oil inlet, brake mouth and return opening, and its electric interfaces is implemented electric connections by cable and control capsule 2, receives the energising pressure release control signal that control capsule 2 is sent; Its oil inlet connects with the brake mouth pipeline of electrohydraulic servo valve 3, and brake mouthful connects with the brake gear oil inlet pipeline of the wheel 5 that brakes, and return opening connects with the aircraft oil return line and passes to oil sump tank.Solenoid valve 4 is in "on" position, and oil inlet is closed, and simultaneously, brake mouth and return opening are linked up, and therefore, is in the pressure release state after solenoid valve 4 energisings.Solenoid valve 4 outages, return opening is closed, and oil inlet is logical with the brake oral groove, therefore, is a brake passage after solenoid valve 4 outages.
Brake pressure sensor 8 is arranged on the hydraulic tubing of brake mouth of electrohydraulic servo valve 2, converts the oil liquid pressure of experiencing to current signal output.Whether brake pressure sensor 8 has an electric interfaces, implements electric the connection by cable with control capsule 2, for control capsule 2 provides the brake pressure signal, to determine the running state of electrohydraulic servo valve 3, namely occur to brake and the fault that can not get off the brakes.The required operating voltage of brake pressure sensor 8 can be provided by control capsule 2.
Because the brake pressure of the control electric current that inputs to electrohydraulic servo valve 3 and electrohydraulic servo valve 3 outputs has one-to-one relationship, therefore, the corresponding brake pressure of control current signal that the brake pressure that detects and control capsule 2 are issued electrohydraulic servo valve 3 compares, can judge the running state of electrohydraulic servo valve 3, namely whether occur to brake and the fault that can not get off the brakes.
As shown in Figure 2, the operational process of the present embodiment is as follows:
In the sliding race process of aircraft landing, chaufeur is stepped on brake pedal, sends brake command voltage signal by brake instruction sensor 1.Control capsule 2 receives after brake command voltage signal through processing, be proportional to the brake control current signal of brake command signal to the torque motor coil output of electrohydraulic servo valve 3, by the electrohydraulic servo valve 3 corresponding brake pressures of output, brake wheel 5 is implemented brake, aircraft is slowed down.Control capsule 2 is the wheel speed signal that sends of inbound pacing sensor 6 also, through processing, the sliding mode of brake wheel 5 is judged, and then implement anti-skidding control.Anti-skidding control has the whole bag of tricks, and the present embodiment adopts the velocity contrast biasing to control.When the difference that forms when speed and the datum velocity of brake wheel 5 surpasses the velocity contrast of being scheduled to, think that namely brake wheel 5 skids, 2 anti-skidding control current signals of output of control capsule, this signal is after controlling the comprehensive calculation process of current signal with brake, give electrohydraulic servo valve 3 output the anti-skidding control current signal of brake, the brake pressure of electrohydraulic servo valve 3 outputs is reduced, prevent that wheel from skidding.In the present embodiment, set the difference that forms when the speed of brake wheel 5 and datum velocity and surpass the velocity contrast be scheduled to for example 15% the time, control capsule 2 is exported anti-skidding control current signals.
In anti-skidding control, if electrohydraulic servo valve 3 et out of orders do not discharge brake pressure, send control signal for solenoid valve 4 by control capsule 2, make solenoid valve 4 energising pressure releases, remove the slipping state of brake wheel 5.
When brake, if electrohydraulic servo valve 3 et out of orders are not exported brake pressure, send control signal for solenoid hydraulic lock 7 by control capsule 2, solenoid hydraulic lock 7 energisings are unblanked, connect hydraulic power source, with the brake pressure of maximum, brake wheel 5 is implemented brake.In brake process, if wheel skids, control solenoid valve 4 energising pressure releases by control capsule 2.
Be in operation, the fault of 2 pairs of electrohydraulic servo valves 3 of control capsule is carried out record, and sends to the aircraft parameter register system.
Under standby brake mode, to be unblanked to brake by solenoid hydraulic lock 7 energisings, brake pressure is the maximum brake pressure of system, anti-skidding control is switching regulator.For the braking efficiency that guarantees that brake process is steady and higher, can set higher slip and control thresholding, for example, adopt 20～25% slippages.
Claims (5)
1. aircraft fax brake antiskid control system, it is characterized in that, comprise brake instruction sensor (1), control capsule (2), electrohydraulic servo valve (3), solenoid valve (4), brake wheel (5), speed sensor (6), solenoid hydraulic lock (7) and brake pressure sensor (8); The input end of control capsule (2) receives respectively brake command voltage signal, the wheel speed signal of speed sensor (6) transmission and the brake pressure signal that brake pressure sensor (8) sends that brake instruction sensor (1) sends; The mouth of control capsule (2) sends brake and anti-skidding control current signal, sends energising pressure release control signal and send to solenoid hydraulic lock (7) control signal of delivery pressure of unblanking of switching on to solenoid valve (4) to electrohydraulic servo valve (3) respectively;
The oil inlet of electrohydraulic servo valve (3), brake mouth and return opening connect by pipeline with oil inlet and the airplane brake system oil return pipe of aircraft pressure source, solenoid valve (4) respectively; The oil inlet of solenoid hydraulic lock (7) connects by pipeline with the oil inlet of electrohydraulic servo valve (3); The brake mouth of solenoid hydraulic lock (7) connects to the pipeline between the oil inlet of solenoid valve (4) with the brake mouth of electrohydraulic servo valve (3), makes the voltage supply pipeline of solenoid hydraulic lock (7) in parallel with the voltage supply pipeline of electrohydraulic servo valve (3); The oil inlet of solenoid valve (4), brake mouth and return opening connect by pipeline with the brake mouth of electrohydraulic servo valve (3), brake gear oil inlet and the aircraft oil return pipe of brake wheel (5) respectively.
2. a kind of aircraft fax brake antiskid control system as claimed in claim 1, it is characterized in that, the electric interfaces of speed sensor (6), electrohydraulic servo valve (3), solenoid hydraulic lock (7), solenoid valve (4), brake pressure sensor (8) respectively with electric connection of control capsule (2).
3. a kind of aircraft fax brake antiskid control system as claimed in claim 1, it is characterized in that, control capsule (2) receives after brake command voltage signal through processing, be proportional to the brake control current signal of brake command signal to the torque motor coil output of electrohydraulic servo valve (3), export corresponding brake pressure by electrohydraulic servo valve (3), brake wheel (5) is implemented brake, aircraft is slowed down; Control capsule (2) is the wheel speed signal that sends of inbound pacing sensor (6) also, through processing, the sliding mode of brake wheel (5) is judged, and then implement anti-skidding control.
4. a kind of aircraft fax brake antiskid control system as claimed in claim 3, it is characterized in that, in anti-skidding control, when electrohydraulic servo valve (3) when not discharging brake pressure, send control signal for solenoid valve (4) by control capsule (2), make solenoid valve (4) energising pressure release, remove the slipping state of brake wheel (5).
5. a kind of aircraft fax brake antiskid control system as claimed in claim 3, it is characterized in that, when brake, when electrohydraulic servo valve (3) when not exporting brake pressure, send control signal for solenoid hydraulic lock (7) by control capsule (2), solenoid hydraulic lock (7) energising is unblanked, connected hydraulic power source, with the brake pressure of maximum, brake wheel (5) is implemented brake; In brake process, if wheel skids, control solenoid valve (4) energising pressure release by control capsule (2).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310070226.4A CN103158867B (en) | 2013-03-06 | 2013-03-06 | Airplane electrical signal transmission brake antiskid control system |
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| CN201310070226.4A CN103158867B (en) | 2013-03-06 | 2013-03-06 | Airplane electrical signal transmission brake antiskid control system |
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| CN103158867A true CN103158867A (en) | 2013-06-19 |
| CN103158867B CN103158867B (en) | 2015-06-10 |
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| 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 |
| CN105253299A (en) * | 2015-09-07 | 2016-01-20 | 西安航空制动科技有限公司 | Antiskid brake control method suitable for undercarriage characteristic frequency |
| CN105905282A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Airplane single-wheel dual-brake-alternative fly-by-wire braking system |
| CN105905283A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Braking system with selectable airplane brake mode |
| 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 |
| CN104986154B (en) * | 2015-06-03 | 2017-11-03 | 西安航空制动科技有限公司 | One kind brake valve assembly |
| CN107477035A (en) * | 2017-07-18 | 2017-12-15 | 中国航空工业集团公司西安飞行自动控制研究所 | A kind of double remaining hydraulic machinery clutches for mechanical backup actuator |
| CN108116667A (en) * | 2017-12-06 | 2018-06-05 | 西安航空制动科技有限公司 | Airplane hydraulic pressure brake system with independent antiskid function |
| CN108146623A (en) * | 2017-12-06 | 2018-06-12 | 西安航空制动科技有限公司 | The self-stopping aircraft brake-by-wire system of two level and brake method |
| CN108897269A (en) * | 2018-07-09 | 2018-11-27 | 西北工业大学 | Electrical Break System of Aircraft pressure sensor fault tolerant control method |
| CN109250075A (en) * | 2018-09-25 | 2019-01-22 | 陕西飞机工业（集团）有限公司 | A kind of aircraft adaptive braking servo valve module |
| CN111976961A (en) * | 2020-07-08 | 2020-11-24 | 西安航空制动科技有限公司 | 6-wheel frame main landing gear aircraft brake control system and method |
| CN112622863A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Fault processing method for airplane anti-skid brake system |
| CN113044207A (en) * | 2020-12-29 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Method for improving safety of airplane antiskid brake system |
| CN113428123A (en) * | 2021-07-15 | 2021-09-24 | 西安航空制动科技有限公司 | Tire burst prevention airplane brake system and control method thereof |
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| 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 |
| CN104787310B (en) * | 2015-04-01 | 2016-10-26 | 西安航空制动科技有限公司 | A kind of aircraft normal braking system with take-off line braking ability |
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| CN105253299A (en) * | 2015-09-07 | 2016-01-20 | 西安航空制动科技有限公司 | Antiskid brake control method suitable for undercarriage characteristic frequency |
| CN105253299B (en) * | 2015-09-07 | 2017-12-12 | 西安航空制动科技有限公司 | A kind of antiskid brake control method suitable for undercarriage characteristic frequency |
| CN105905282A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Airplane single-wheel dual-brake-alternative fly-by-wire braking system |
| CN105905283A (en) * | 2016-06-17 | 2016-08-31 | 西安航空制动科技有限公司 | Braking system with selectable airplane brake mode |
| 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 |
| CN105905282B (en) * | 2016-06-17 | 2017-10-20 | 西安航空制动科技有限公司 | The optional Flight By Wire brake system of aircraft single-wheel double-brake |
| CN105905281B (en) * | 2016-06-17 | 2017-12-12 | 西安航空制动科技有限公司 | The airplane wheel Flight By Wire brake system of brake modes can be selected |
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| CN108116667A (en) * | 2017-12-06 | 2018-06-05 | 西安航空制动科技有限公司 | Airplane hydraulic pressure brake system with independent antiskid function |
| CN108146623A (en) * | 2017-12-06 | 2018-06-12 | 西安航空制动科技有限公司 | The self-stopping aircraft brake-by-wire system of two level and brake method |
| CN108146623B (en) * | 2017-12-06 | 2020-11-10 | 西安航空制动科技有限公司 | Airplane fly-by-wire brake system with two-stage automatic brake and brake method |
| CN108897269A (en) * | 2018-07-09 | 2018-11-27 | 西北工业大学 | Electrical Break System of Aircraft pressure sensor fault tolerant control method |
| CN109250075A (en) * | 2018-09-25 | 2019-01-22 | 陕西飞机工业（集团）有限公司 | A kind of aircraft adaptive braking servo valve module |
| CN111976961A (en) * | 2020-07-08 | 2020-11-24 | 西安航空制动科技有限公司 | 6-wheel frame main landing gear aircraft brake control system and method |
| CN112622863A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Fault processing method for airplane anti-skid brake system |
| CN113044207A (en) * | 2020-12-29 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Method for improving safety of airplane antiskid brake system |
| CN113044207B (en) * | 2020-12-29 | 2022-09-20 | 中国航空工业集团公司西安飞机设计研究所 | Method for improving safety of airplane antiskid brake system |
| CN113428123A (en) * | 2021-07-15 | 2021-09-24 | 西安航空制动科技有限公司 | Tire burst prevention airplane brake system and control method thereof |
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