CN105523179A - Aircraft brake pressure feedback regulation system and aircraft brake pressure feedback regulation method - Google Patents
Aircraft brake pressure feedback regulation system and aircraft brake pressure feedback regulation method Download PDFInfo
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- CN105523179A CN105523179A CN201410508293.4A CN201410508293A CN105523179A CN 105523179 A CN105523179 A CN 105523179A CN 201410508293 A CN201410508293 A CN 201410508293A CN 105523179 A CN105523179 A CN 105523179A
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- antiskid braking
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Abstract
The present invention relates to an aircraft brake pressure feedback regulation system and an aircraft brake pressure feedback regulation method. The aircraft brake pressure feedback regulation system comprises a brake command sensor, an anti-skid brake control box, an electro-hydraulic pressure servo valve, a wheel speed sensor and a brake pressure sensor. Compared with the conventional anti-skid brake system, the aircraft brake pressure feedback regulation system of the present invention has the following characteristics that the brake pressure sensor is additionally arranged in the brake pipeline, the brake pressure signal is fed back to the anti-skid brake control box, the brake pressure is used to perform feedback regulation in the anti-skid brake control box, and the anti-skid brake control box regulates the drive current of the electro-hydraulic pressure servo valve, such that the error caused by the zero offset of the electro-hydraulic pressure servo valve is reduced, the aircraft anti-skid brake control precision is improved, and the safety of the aircraft landing is improved.
Description
Technical field
The present invention relates to aircraft brake technical field, particularly relate to a kind of aircraft brake pressure feedback control system and method.
Background technology
Aircraft Anti-skid Break Control is as the important mobile system of aircraft, can anti-skid brake system (ABS) normally work and will have a strong impact on aircraft safety, at present, aircraft anti-skid braking all adopts wheel speed as the feedback command of skid control system, the object of brake system anti-lock can be reached like this, in brake process, adopt Electric hydraulic pressure servo valve as brake pressure control device part.Usually brake pressure sensor is provided with in anti-skid brake system (ABS), be used to indicate brake pressure, brake pressure has neither part nor lot in control, and usually there is the phenomenon of unstable properties in current Electric hydraulic pressure servo valve, be mainly manifested in Electric hydraulic pressure servo valve and dead band drift easily occurs, change in gain, it directly affects antiskid brake performance, can jeopardize aircraft landing safety time serious.
Summary of the invention
The object of the invention is: a kind of aircraft brake pressure feedback control system and method are provided.By by brake pressure sensor signal feedback to antiskid braking control box, reduce the error that partially causes of Electric hydraulic pressure servo valve zero, improve airplane antiskid braking control accuracy.
Technical scheme of the present invention is: a kind of aircraft brake pressure feedback control system, comprises brake instruction transducer 1, antiskid braking control box 2, Electric hydraulic pressure servo valve 3, wheel spin-up transducer 4 and brake pressure sensor 5; Brake instruction transducer 1 and antiskid braking control box 2 are electrically connected, antiskid braking control box 2 and Electric hydraulic pressure servo valve 3 are electrically connected, antiskid braking control box 2 and wheel spin-up transducer 4 are electrically connected, and antiskid braking control box 2 and brake pressure sensor 5 are electrically connected.
Under brake instruction transducer 1 is arranged on brake pedal, it is handled by the brake pedal experiencing chaufeur, exports corresponding voltage signal to antiskid braking control box 2.
Antiskid braking control box 2 receives the signal of brake instruction transducer 1, wheel spin-up transducer 4 and brake pressure sensor 5, judges whether airplane wheel is in slip state and regulates to the control signal size of Electric hydraulic pressure servo valve 3.
Electric hydraulic pressure servo valve 3 receives the control signal of antiskid braking control box 2, exports corresponding brake pressure to wheel brake.
Wheel spin-up transducer 4 is rotated by self thus obtains main airplane wheel rotative speed.
Output signal for measuring Electric hydraulic pressure servo valve 3 delivery pressure, and is sent to antiskid braking control box 2 by brake pressure sensor 5.
A kind of aircraft brake pressure feedback control method, comprises the steps:
The first step, chaufeur touches on the brake pedal, and drive brake instruction transducer 1 to move after the motion of brake pedal, brake instruction transducer 1 exports corresponding brake instruction to antiskid braking control box 2;
Second step, antiskid braking control box 2, according to brake instruction transducer 1 output signal, calculates theoretical delivery pressure value P (v), and applies corresponding control signal to Electric hydraulic pressure servo valve 3;
3rd step, Electric hydraulic pressure servo valve 3, according to the control signal of antiskid braking control box 2, exports corresponding brake pressure to brake gear;
4th step, main wheel rotative speed measured by wheel spin-up transducer 4, and output signal is sent to antiskid braking control box 2;
5th step, antiskid braking control box 2 is according to the rotary regimes of wheel spin-up transducer 4, judge whether airplane wheel is in slip state, if airplane wheel is in slip state, then antiskid braking control box 2 discharges system brake pressure by the instruction being applied to Electric hydraulic pressure servo valve 3; If airplane wheel is in non-slip state, then enter next step;
6th step, brake pressure sensor 5 measures the brake pressure acted on brake gear, and actual delivery pressure value P ' (v) is sent to antiskid braking control box 2;
7th step, antiskid braking control box 2 carries out calculating to theoretical delivery pressure value P (v) and actual delivery pressure value P ' (v) and compares, if P (v) is greater than P ' (v), antiskid braking control box (2) changes the control signal of Electric hydraulic pressure servo valve 3, until P (v) equals P ' (v); If P (v) is less than P ' (v), antiskid braking control box 2 changes the control signal of Electric hydraulic pressure servo valve 3, until P (v) equals P ' (v); If P (v) equals P ' (v), antiskid braking control box 2 keeps the control signal to Electric hydraulic pressure servo valve 3.
For the Electric hydraulic pressure servo valve 3 adopting postiive gain mode, if P (v) is greater than P ' (v), then antiskid braking control box 2 increases the control signal to Electric hydraulic pressure servo valve 3; If P (v) is less than in P ' (v), then antiskid braking control box 2 reduces the control signal to Electric hydraulic pressure servo valve 3;
For the Electric hydraulic pressure servo valve 3 adopting negative gain mode, if P (v) is greater than P ' (v), then antiskid braking control box 2 reduces the control signal to Electric hydraulic pressure servo valve 3; If P (v) is less than in P ' (v), then antiskid braking control box 2 increases the control signal to Electric hydraulic pressure servo valve 3.
The advantage that the present invention has and beneficial effect are: the present invention by by brake pressure sensor signal feedback to antiskid braking control box, reduce the error that Electric hydraulic pressure servo valve zero causes partially, improve airplane antiskid braking control accuracy, improve the safety of aircraft landing.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is that in the present invention, pressure feedback regulates schematic diagram.
Detailed description of the invention
Below in conjunction with Figure of description, the present invention is illustrated.
As shown in Figure 1, a kind of aircraft brake pressure feedback control system, comprises brake instruction transducer 1, antiskid braking control box 2, Electric hydraulic pressure servo valve 3, wheel spin-up transducer 4 and brake pressure sensor 5; Brake instruction transducer 1 and antiskid braking control box 2 are electrically connected, antiskid braking control box 2 and Electric hydraulic pressure servo valve 3 are electrically connected, antiskid braking control box 2 and wheel spin-up transducer 4 are electrically connected, and antiskid braking control box 2 and brake pressure sensor 5 are electrically connected.
Brake instruction transducer 1 is arranged on brake pedal, pilot control brake pedal, and the corresponding brake instruction transducer 1 of different brake travel exports different level values, and the level value that brake instruction transducer 1 exports represents the size that chaufeur brakes.
Antiskid braking control box 2 can realize controlling Electric hydraulic pressure servo valve 3 according to the output signal of brake instruction transducer signal 1, wheel spin-up transducer 4 and brake pressure sensor 5.According to the output signal of wheel spin-up transducer 4, first antiskid braking control box 2 judges whether aircraft is in slip state, as aircraft is in slip state, then reduce the control signal of antiskid braking control box 2 pairs of Electric hydraulic pressure servo valve 3; As aircraft is in non-slip state, antiskid braking control box 2, according to the signal of brake instruction transducer 1 signal and brake pressure sensor 5, exports corresponding control signal to Electric hydraulic pressure servo valve 3.
The size of the control signal that Electric hydraulic pressure servo valve 3 can export according to antiskid braking control box 2 exports corresponding brake pressure signal to wheel brake.
Wheel spin-up transducer 4 is rotated by self thus obtains main airplane wheel rotative speed.During concrete enforcement, this wheel spin-up transducer 4 can be directly installed on main wheel wheel shaft.
Brake pressure sensor 5, by being connected on the brake line of wheel brake front end, can measure the brake pressure be applied on wheel brake.
Described feedback regulation method as shown in Figure 2
Brake instruction and brake pressure corresponding relation P (v) are stored in control capsule internal memory by antiskid braking control box 2, when antiskid braking control box 2 receives a brake instruction signal v, it controls Electric hydraulic pressure servo valve 3 and exports the brake pressure that should be P (v).
Carrying out in working control process, due to Electric hydraulic pressure servo valve 3 zero drift, its output does not meet theoretical curve corresponding relation, that is, when antiskid braking control box 2 receives the brake instruction v of brake instruction transducer 1, it sends corresponding brake control signal to Electric hydraulic pressure servo valve 3, and Electric hydraulic pressure servo valve 3 is due to zero drift, and the pressure signal of output is P ' (v).Brake pressure signal P ' (v) is fed back to antiskid braking control box 2 by brake pressure sensor 5.Antiskid braking control box 2 exports theory and actual output calculates, and computing formula is as follows:
△P＝P(v)-P′(v)(1)
If △ P be on the occasion of, then represent that actual output is less than theoretical output, antiskid brake control to increase Electric hydraulic pressure servo valve 3 control signal until, actual delivery pressure signal P ' (v) equals theoretical delivery pressure signal P (v); If △ P is negative value, then represent that actual output is greater than theoretical output, antiskid brake control to reduce Electric hydraulic pressure servo valve 3 control signal until, actual delivery pressure signal P ' (v) equals theoretical delivery pressure signal P (v).
Claims (3)
1. an aircraft brake pressure feedback control system, it is characterized in that, native system comprises brake instruction transducer (1), antiskid braking control box (2), Electric hydraulic pressure servo valve (3), wheel spin-up transducer (4) and brake pressure sensor (5), brake instruction transducer (1) and antiskid braking control box (2) are electrically connected, antiskid braking control box (2) and Electric hydraulic pressure servo valve (3) are electrically connected, antiskid braking control box (2) and wheel spin-up transducer (4) are electrically connected, antiskid braking control box (2) and brake pressure sensor (5) are electrically connected, under brake instruction transducer (1) is arranged on brake pedal, it is handled by the brake pedal experiencing chaufeur, export corresponding voltage signal to antiskid braking control box (2), antiskid braking control box (2) receives brake instruction transducer (1), the signal of wheel spin-up transducer (4) and brake pressure sensor (5), judge whether airplane wheel is in slip state, and regulate to the control signal size of Electric hydraulic pressure servo valve (3), Electric hydraulic pressure servo valve (3) receives the control signal of antiskid braking control box (2), export corresponding brake pressure to wheel brake, wheel spin-up transducer (4) obtains main airplane wheel rotative speed, brake pressure sensor (5) is for measuring Electric hydraulic pressure servo valve (3) delivery pressure, and output signal is sent to antiskid braking control box (2).
2. an aircraft brake pressure feedback control method, is characterized in that, this method comprises the following steps:
The first step, chaufeur touches on the brake pedal, and drive brake instruction transducer (1) to move after the motion of brake pedal, brake instruction transducer (1) exports corresponding brake instruction to antiskid braking control box (2);
Second step, antiskid braking control box (2), according to brake instruction transducer (1) output signal, calculates theoretical delivery pressure value P (v), and applies corresponding control signal to Electric hydraulic pressure servo valve (3);
3rd step, Electric hydraulic pressure servo valve (3), according to the control signal of antiskid braking control box (2), exports corresponding brake pressure to brake gear;
4th step, main wheel rotative speed measured by wheel spin-up transducer (4), and output signal is sent to antiskid braking control box (2);
5th step, antiskid braking control box (2) is according to the rotary regimes of wheel spin-up transducer (4), judge whether airplane wheel is in slip state, if airplane wheel is in slip state, then antiskid braking control box (2) discharges system brake pressure by the instruction being applied to Electric hydraulic pressure servo valve (3); If airplane wheel is in non-slip state, then enter next step;
6th step, brake pressure sensor (5) measures the brake pressure acted on brake gear, and actual delivery pressure value P ' (v) is sent to antiskid braking control box (2);
7th step, antiskid braking control box (2) carries out calculating to theoretical delivery pressure value P (v) and actual delivery pressure value P ' (v) and compares, if P (v) is greater than P ' (v), antiskid braking control box (2) changes the control signal of Electric hydraulic pressure servo valve (3), until P (v) equals P ' (v); If P (v) is less than P ' (v), antiskid braking control box (2) changes the control signal of Electric hydraulic pressure servo valve (3), until P (v) equals P ' (v); If P (v) equals P ' (v), antiskid braking control box (2) keeps the control signal to Electric hydraulic pressure servo valve (3).
3. a kind of aircraft brake pressure feedback control method as claimed in claim 2, is characterized in that, the antiskid braking control box (2) described in the 5th step changes the control signal of Electric hydraulic pressure servo valve (3), comprising:
For the Electric hydraulic pressure servo valve (3) adopting postiive gain mode, if P (v) is greater than P ' (v), then antiskid braking control box (2) increases the control signal to Electric hydraulic pressure servo valve (3); If P (v) is less than in P ' (v), then antiskid braking control box (2) reduces the control signal to Electric hydraulic pressure servo valve (3);
For the Electric hydraulic pressure servo valve (3) adopting negative gain mode, if P (v) is greater than P ' (v), then antiskid braking control box (2) reduces the control signal to Electric hydraulic pressure servo valve (3); If P (v) is less than in P ' (v), then antiskid braking control box (2) increases the control signal to Electric hydraulic pressure servo valve (3).
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| CN201410508293.4A CN105523179A (en) | 2014-09-28 | 2014-09-28 | Aircraft brake pressure feedback regulation system and aircraft brake pressure feedback regulation method |
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| CN201410508293.4A CN105523179A (en) | 2014-09-28 | 2014-09-28 | Aircraft brake pressure feedback regulation system and aircraft brake pressure feedback regulation method |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108100241A (en) * | 2017-12-06 | 2018-06-01 | 西安航空制动科技有限公司 | It can self-stopping aircraft brake-by-wire system and brake method |
| CN108216595A (en) * | 2016-12-14 | 2018-06-29 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of efficient brake pressure control method |
| CN108945401A (en) * | 2018-05-07 | 2018-12-07 | 西安航空制动科技有限公司 | A kind of aircraft brake compress control method |
| CN109515698A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of various dimensions constant speed antiskid control system |
| CN109849881A (en) * | 2018-12-07 | 2019-06-07 | 西安飞机工业（集团）有限责任公司 | A kind of antiskid braking control system for airplane and control method |
| CN110116800A (en) * | 2019-05-14 | 2019-08-13 | 西安航空制动科技有限公司 | Brake control method of the Aircraft Anti-skid Break Control under anti-skidding failure |
| CN110816820A (en) * | 2019-10-30 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Brake deceleration control system |
| CN112249310A (en) * | 2020-09-28 | 2021-01-22 | 西安航空学院 | An aircraft brake pressure feedback adjustment system and method |
| CN113428127A (en) * | 2021-07-15 | 2021-09-24 | 西安航空制动科技有限公司 | Airplane brake system residual pressure monitoring and protecting method capable of avoiding tire explosion |
| CN113753226A (en) * | 2021-08-18 | 2021-12-07 | 西安航空制动科技有限公司 | Integrated embedded aircraft braking system |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108216595A (en) * | 2016-12-14 | 2018-06-29 | 中国航空工业集团公司西安航空计算技术研究所 | A kind of efficient brake pressure control method |
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| CN109515698A (en) * | 2018-03-16 | 2019-03-26 | 陕西飞机工业（集团）有限公司 | A kind of various dimensions constant speed antiskid control system |
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| CN108945401B (en) * | 2018-05-07 | 2021-09-14 | 西安航空制动科技有限公司 | Airplane brake pressure control method |
| CN109849881A (en) * | 2018-12-07 | 2019-06-07 | 西安飞机工业（集团）有限责任公司 | A kind of antiskid braking control system for airplane and control method |
| CN110116800A (en) * | 2019-05-14 | 2019-08-13 | 西安航空制动科技有限公司 | Brake control method of the Aircraft Anti-skid Break Control under anti-skidding failure |
| CN110816820A (en) * | 2019-10-30 | 2020-02-21 | 中国航空工业集团公司沈阳飞机设计研究所 | Brake deceleration control system |
| CN112249310A (en) * | 2020-09-28 | 2021-01-22 | 西安航空学院 | An aircraft brake pressure feedback adjustment system and method |
| CN113428127A (en) * | 2021-07-15 | 2021-09-24 | 西安航空制动科技有限公司 | Airplane brake system residual pressure monitoring and protecting method capable of avoiding tire explosion |
| CN113428127B (en) * | 2021-07-15 | 2022-07-22 | 西安航空制动科技有限公司 | Airplane brake system residual pressure monitoring protection method capable of avoiding tire explosion |
| CN113753226A (en) * | 2021-08-18 | 2021-12-07 | 西安航空制动科技有限公司 | Integrated embedded aircraft braking system |
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