CN103523217A - Nose-wheel steering system of aircraft - Google Patents
Nose-wheel steering system of aircraft Download PDFInfo
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- CN103523217A CN103523217A CN201210232898.6A CN201210232898A CN103523217A CN 103523217 A CN103523217 A CN 103523217A CN 201210232898 A CN201210232898 A CN 201210232898A CN 103523217 A CN103523217 A CN 103523217A
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- 239000002775 capsule Substances 0.000 description 11
- 238000013016 damping Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- IWEDIXLBFLAXBO-UHFFFAOYSA-N dicamba Chemical compound COC1=C(Cl)C=CC(Cl)=C1C(O)=O IWEDIXLBFLAXBO-UHFFFAOYSA-N 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 238000007747 plating Methods 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002457 bidirectional effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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Abstract
本发明属于航空工程领域，提供一种飞机前轮转弯系统，其中，转弯控制盒通过电缆线路与指令传感器、组合液压阀和反馈传感器连接；指令传感器的一端用螺栓固定在飞机驾驶舱地板下，另一端通过螺栓与脚蹬铰接；组合液压阀通过螺栓固定在前起落架舱壁板上；反馈传感器安装在转弯作动器上；反馈传感器的一端通过卡箍固定在转弯作动器壳体上，另一端通过夹片与转弯作动器活塞杆连接；转弯作动器安装在飞机前起落架上，转弯作动器活塞杆通过关节轴承和螺栓与前起落架旋转套筒铰接。本发明提供的飞机前轮转弯系统，用于飞机滑行低速阶段的转弯和高速阶段的防摆，具有良好的操纵灵活性和防摆稳定性。
The invention belongs to the field of aeronautical engineering and provides an aircraft front wheel steering system, wherein the steering control box is connected with a command sensor, a combined hydraulic valve and a feedback sensor through a cable line; one end of the command sensor is fixed under the floor of the aircraft cockpit with bolts, The other end is hinged with the pedal through bolts; the combined hydraulic valve is fixed on the bulkhead of the front landing gear through bolts; the feedback sensor is installed on the turning actuator; one end of the feedback sensor is fixed on the turning actuator housing through a clamp , the other end is connected with the piston rod of the turning actuator through a clip; the turning actuator is installed on the nose landing gear of the aircraft, and the piston rod of the turning actuator is hinged with the rotating sleeve of the nose landing gear through joint bearings and bolts. The aircraft nose wheel steering system provided by the invention is used for the aircraft taxiing low-speed turning and high-speed anti-swing, and has good control flexibility and anti-swing stability.
Description
Technical field
The invention belongs to aeronautical engineering field, relate to a kind of aircraft nose wheel turning system.
Background technology
Nose Wheel Steering system improves as a kind of the device that aircraft floor slides manoevreability and landing safety, in airplane design, is widely used.Nose Wheel Steering system has experienced the stages such as mechanical type, mechanical-hydraulic formula, simulation fax formula, digital FBW formula in evolution.The simulation fax formula that the mostly is Nose Wheel Steering system that China's aircraft adopts at present, its shortcoming is that volume is larger, poor expandability, turn control is not steady.
Summary of the invention
The technical problem to be solved in the present invention: the object of this invention is to provide a kind of digital FBW formula aircraft nose wheel turning system, direction for the aircraft low speed slide stage is controlled, and taking off, landing period provides front-wheel anti-sway required damping, while running, there is shimmy of front wheels phenomenon in anti-on-slip.
Technical scheme of the present invention: a kind of aircraft nose wheel turning system, comprising: turning control capsule, instruction sensor, assembled hydraulic valve, turning actuator, feedback transducer and cable link, hydraulic tubing;
Turning control capsule is fixed by bolts in aircraft electrical equipment cabin, by cable line and instruction sensor, assembled hydraulic valve, is connected with feedback transducer; One end of instruction sensor is fixed by bolts under aircraft cockpit floor, and the other end is hinged by bolt and pedal; Assembled hydraulic valve is bolted in nose-gear bulkhead plating, and 4 hydraulic pressure ozzles above it are connected with 2 ozzles, oil-feed and oil returns of turning actuator by hydraulic tubing respectively;
Feedback transducer is arranged in turning actuator; One end of feedback transducer is fixed on turning actuator housing by clip, and the other end is connected with turning actuator piston rod by intermediate plate, and servo-actuated with piston rod;
Turning actuator is arranged on aircraft nose-gear; 2 concentric shafts on turning actuator housing are arranged on respectively in the hole of nose-gear urceolus and auricle, and auricle is bolted on urceolus, and turning actuator can be rotated around the axis of concentric shafts.Turning actuator piston rod is hinged by oscillating bearing and bolt and nose-gear turnbarrel.
Beneficial effect of the present invention: the invention provides a kind of aircraft nose wheel turning system, anti-sway for the turning of aircraft taxi low-speed stage and high speed stage, has good yarage and anti-pendulum stability.This system has following features:
1) volume is little, lightweight, and extensibility is strong;
2) turn control is steady, and integrated level is high, arrangement convenience;
3) feasible system self check and failure monitoring, safety is higher;
4) combine valve and compensator integrate, and make more compact structure, weight lighter, and oil circuit arranges more advantages of simple, and anti-sway performance is better.
Accompanying drawing explanation
Fig. 1 is Nose Wheel Steering system functional block diagram of the present invention.
Fig. 2 is that Nose Wheel Steering system of the present invention forms and connection diagram.
Fig. 3 is turn actuator and feedback transducer of the present invention.
Fig. 4 is the present invention's connection of actuator on nose-gear of turning.
The specific embodiment
The present invention is a kind of digital FBW formula Nose Wheel Steering system, below it is described in further details.
Functional block diagram of the present invention and composition connection diagram are respectively as depicted in figs. 1 and 2.This system comprises: the accessories such as 4,1 feedback transducer 5 of 3,1 turning actuator of 2,1 assembled hydraulic valve of 1,1 instruction sensor of 1 turning control capsule and cable link, hydraulic tubing.
Turning control capsule 1 is fixed by bolts in aircraft electrical equipment cabin, is connected, and introduces source switch, turning button and wheel load on-off signal by cable line and instruction sensor 2, assembled hydraulic valve 3 and feedback transducer 5.One end of instruction sensor 2 is fixed by bolts under aircraft cockpit floor, and the other end is hinged by bolt and pedal, guarantees that instruction sensor links together with pedal.Assembled hydraulic valve 3 is bolted in nose-gear bulkhead plating, and 4 hydraulic pressure ozzles above it are connected with 2 ozzles, oil-feed and oil returns of turning actuator 4 by hydraulic tubing respectively.
Feedback transducer 5 is arranged in turning actuator 4, as shown in Figure 3.One end of feedback transducer is fixed on turning actuator housing 6 by clip, and the other end is connected with turning actuator piston rod 7 by intermediate plate, and servo-actuated with piston rod.
Turning actuator 4 is arranged on aircraft nose-gear, as shown in Figure 4.2 concentric shafts on turning actuator housing 6 are arranged on respectively in the hole of nose-gear urceolus 8 and auricle 9, and auricle 9 is bolted on urceolus 8, and turning actuator can be rotated around the axis of concentric shafts.Turning actuator piston rod 7 is hinged by oscillating bearing and bolt and nose-gear turnbarrel 10.Turning actuator piston rod 7 stretches out or retracts under hydraulic pressure effect, and driven rotary sleeve 10 rotates around nose-gear pillar axes, by upper anti-arm 11 and the lower anti-arm 12 of turning round turned round, drives front wheel 13 deflections, realizes the turning function of aircraft.
The overall plan of system is the turn control while adopting digital electric-hydraulic Positioning Servo System to realize aircraft low speed slide, the anti-sway control while adopting hydraulic damping to realize aircraft taxi.
It is core component that turning control capsule adopts micro controller system, is equipped with the devices such as D/A conversion chip, power amplifier, relay, has performance good, and adjustable is large, adaptable advantage.Turning control capsule sends control command by certain control law to assembled hydraulic valve according to the signal of instruction sensor, and receives the signal of feedback transducer, with the implementation status to instruction, judges.The requirement of as prescribed is simultaneously carried out self check to system, if any fault, provides alarm indication, as working properly in trouble free reporting system.
Instruction sensor provides turning electric signal by aviator's pedal Control requirements to turning control capsule.
Assembled hydraulic valve is formed by component integrations such as electromagnetic valve, servovalve, dash pot valve, safety valve, compensator, state change-over valves, by the state conversion (turning or anti-sway) of the control command actuating system of turning control capsule.When turn condition, by control command, to turning actuator, distribute hydraulic energy source to turn with operating aircraft left and right; When anti-sway state, with the anti-sway loop of the common composition of turning actuator, provide anti-pendulum damper.
Turning actuator is the execution unit of Nose Wheel Steering system, realizes and turning, and jointly form anti-sway loop with assembled hydraulic valve according to the hydraulic pressure operating aircraft front-wheel of assembled hydraulic valve output, realizes the anti-sway function of aircraft.
Feedback transducer is for providing turning actuator position feedback electric signal to turning control capsule.
This Nose Wheel Steering system has turns and anti-sway two kinds of mode of operations.
1) turn condition
After aircraft soft strip, wheel load switch is in on-state.Now as need to be changed to slide, run direction, aviator can connect turning source switch, and presses the turning button on control wheel, and electronic circuit is after supervisory circuit detects trouble free, and electromagnetic valve is switched on, and state change-over valve forwards turning station to, and system is in turn condition.
When aviator is pedaled pedal, instruction sensor output pedal displacement signal, after turning control capsule is processed, become turn command, be input to assembled hydraulic valve, the servovalve that makes to turn divides oil to turning actuator, drives turning actuator piston rod movement, wheel deflection before driving, realizes the turning of aircraft.The feedback transducer of simultaneously turning in actuator is synchronized with the movement with turning actuator piston rod, the displacement signal of turning actuator is fed back to turning control capsule and carry out error synthesis, the position (being front wheel slip angle) of the actuator that makes to turn keeps accompanying with pedal position.
2) anti-sway state
When aircraft high speed slide, aviator unclamps turning button or disconnects turning source switch, electromagnetic valve power-off, and state change-over valve is in anti-sway state.If now nose-gear occurs shimmyly, will force fluid by bidirectional damper valve, to flow to another chamber from a chamber of turning actuator, the shock damping action of dash pot valve is that thermal energy consumption dissipates by shimmy transformation of energy, thereby makes shimmyly weaken rapidly and stop.
In anti-sway loop, be provided with compensator and safety valve, when the hypotony of system, compensator adds to loop fluid at any time by certain pressure, prevents air pocket, guarantees the damping force characteristics in loop.When system pressure is during higher than limit, safety valve is opened, and system pressure is no longer raise, and guarantees the safety of system.
In addition, native system also has self check and failure monitor function, exports breakdown signal when system breaks down, and the state change-over valve of making is converted to anti-sway state, realizes the safety control of fault.
Claims (1)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210232898.6A CN103523217A (en) | 2012-07-06 | 2012-07-06 | Nose-wheel steering system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210232898.6A CN103523217A (en) | 2012-07-06 | 2012-07-06 | Nose-wheel steering system of aircraft |
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| Publication Number | Publication Date |
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| CN103523217A true CN103523217A (en) | 2014-01-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210232898.6A Pending CN103523217A (en) | 2012-07-06 | 2012-07-06 | Nose-wheel steering system of aircraft |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104085528A (en) * | 2014-07-10 | 2014-10-08 | 中国商用飞机有限责任公司 | Airplane front wheel turning control system and airplane front wheel turning control method |
| CN105000172A (en) * | 2015-07-27 | 2015-10-28 | 江西洪都航空工业集团有限责任公司 | Launch and recovery electrical control system of aircraft landing gear |
| CN105564639A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Dual-redundancy nose-wheel steering and shimmy-damping system |
| CN105810040A (en) * | 2016-05-18 | 2016-07-27 | 袁芫 | Airplane flying ground sliding trainer |
| CN105905284A (en) * | 2016-04-28 | 2016-08-31 | 江西洪都航空工业集团有限责任公司 | Front wheel turning anti-swing system with medium speed correction function |
| CN106043674A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding shimmy of main undercarriage under high-speed condition |
| CN106364669A (en) * | 2016-09-08 | 2017-02-01 | 北京精密机电控制设备研究所 | Lead screw-shifting fork type electromechanical servo mechanism |
| CN106697268A (en) * | 2016-12-28 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft nose wheel steering control system |
| CN107054630A (en) * | 2016-02-10 | 2017-08-18 | 赛峰起落架系统公司 | Aircraft landing gear including main damper and antidetonation time damper |
| CN107738743A (en) * | 2017-10-12 | 2018-02-27 | 中国商用飞机有限责任公司 | Aircraft nose landing gear turning system |
| CN108001671A (en) * | 2017-11-08 | 2018-05-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of aircraft nose wheel turning actuator |
| CN108860652A (en) * | 2018-06-27 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A method of improving Nose Wheel Steering drive system precision |
| CN110606192A (en) * | 2019-10-24 | 2019-12-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane front wheel turning control method |
| CN110697032A (en) * | 2019-10-18 | 2020-01-17 | 中国商用飞机有限责任公司 | Low-leakage hydraulic swing reduction compensation circuit for airplane front wheel steering system |
| CN112810805A (en) * | 2021-01-20 | 2021-05-18 | 同济大学 | Multi-wheel multi-support wide-body airplane main wheel cooperative turning asymmetric control system |
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| US2814452A (en) * | 1950-10-26 | 1957-11-26 | Bendix Aviat Corp | Aircraft steering control system |
| GB791101A (en) * | 1955-11-16 | 1958-02-26 | Jarry Automobile Ltd | Improvements in or relating to steering mechanism for aircraft nose wheels, or the like |
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Non-Patent Citations (2)
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104085528B (en) * | 2014-07-10 | 2016-08-24 | 中国商用飞机有限责任公司 | Airplane front wheel turning control system and airplane front wheel turning control method |
| CN104085528A (en) * | 2014-07-10 | 2014-10-08 | 中国商用飞机有限责任公司 | Airplane front wheel turning control system and airplane front wheel turning control method |
| CN105564639A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Dual-redundancy nose-wheel steering and shimmy-damping system |
| CN105000172A (en) * | 2015-07-27 | 2015-10-28 | 江西洪都航空工业集团有限责任公司 | Launch and recovery electrical control system of aircraft landing gear |
| CN107054630A (en) * | 2016-02-10 | 2017-08-18 | 赛峰起落架系统公司 | Aircraft landing gear including main damper and antidetonation time damper |
| CN105905284A (en) * | 2016-04-28 | 2016-08-31 | 江西洪都航空工业集团有限责任公司 | Front wheel turning anti-swing system with medium speed correction function |
| CN105810040A (en) * | 2016-05-18 | 2016-07-27 | 袁芫 | Airplane flying ground sliding trainer |
| CN106043674A (en) * | 2016-05-31 | 2016-10-26 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding shimmy of main undercarriage under high-speed condition |
| CN106364669A (en) * | 2016-09-08 | 2017-02-01 | 北京精密机电控制设备研究所 | Lead screw-shifting fork type electromechanical servo mechanism |
| CN106697268A (en) * | 2016-12-28 | 2017-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Aircraft nose wheel steering control system |
| CN106697268B (en) * | 2016-12-28 | 2019-05-10 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft nose wheel turning control system |
| CN107738743A (en) * | 2017-10-12 | 2018-02-27 | 中国商用飞机有限责任公司 | Aircraft nose landing gear turning system |
| CN108001671A (en) * | 2017-11-08 | 2018-05-08 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of aircraft nose wheel turning actuator |
| CN108860652A (en) * | 2018-06-27 | 2018-11-23 | 成都飞机工业（集团）有限责任公司 | A method of improving Nose Wheel Steering drive system precision |
| CN108860652B (en) * | 2018-06-27 | 2021-06-08 | 成都飞机工业（集团）有限责任公司 | Method for improving transmission precision of front wheel steering system |
| CN110697032A (en) * | 2019-10-18 | 2020-01-17 | 中国商用飞机有限责任公司 | Low-leakage hydraulic swing reduction compensation circuit for airplane front wheel steering system |
| CN110606192A (en) * | 2019-10-24 | 2019-12-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane front wheel turning control method |
| CN112810805A (en) * | 2021-01-20 | 2021-05-18 | 同济大学 | Multi-wheel multi-support wide-body airplane main wheel cooperative turning asymmetric control system |
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Application publication date: 20140122 |