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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Abstract
The invention belongs to the field of aircraft engineering, and provides a nose-wheel steering system of an aircraft. According to the nose-wheel steering system, a steering control box is connected with an instruction sensor, a combined hydraulic valve and a feedback sensor through cables; one end of the instruction sensor is fixedly arranged below a floor of a cockpit of the aircraft by using bolts, and the other end of the instruction sensor is hinged to a foot pedal through bolts; the combined hydraulic valve is fixedly arranged on a bulkhead plate of a nose landing gear through bolts; the feedback sensor is arranged on a steering actuator; one end of the feedback sensor is fixedly arranged on a steering actuator shell through a hoop, and the other end of the feedback sensor is connected with a piston rod of the steering actuator through a clamping piece; the steering actuator is arranged on the nose landing gear of the aircraft; a piston rod of the steering actuator is hinged to a rotary sleeve of the nose landing gear through a joint bearing and a bolt. The nose-wheel steering system of the aircraft is used for steering at a low-speed stage and swing prevention at a high-speed stage during sliding of the aircraft, and has good operation 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)
1. an aircraft nose wheel turning system, is characterized in that, 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.
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 |
Publications (1)
| 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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| CN (1) | CN103523217A (en) |
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 |
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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 |