CN105564639A - Dual-redundancy nose-wheel steering and shimmy-damping system - Google Patents
Dual-redundancy nose-wheel steering and shimmy-damping system Download PDFInfo
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- CN105564639A CN105564639A CN201410535712.3A CN201410535712A CN105564639A CN 105564639 A CN105564639 A CN 105564639A CN 201410535712 A CN201410535712 A CN 201410535712A CN 105564639 A CN105564639 A CN 105564639A
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- control valve
- steering
- servo control
- turning
- pressurized strut
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Abstract
The invention provides a dual-redundancy nose-wheel steering and shimmy-damping system. The dual-redundancy nose-wheel steering and shimmy-damping system is characterized by comprising a steering control unit (1), a steering instruction sensor (2), a first steering control valve (3), a second steering control valve (4), a steering position feedback transducer (5), a first steering actuating drum (6) and a second steering actuating drum (7), wherein the steering instruction sensor (2) inputs a pedal instruction of a driver into the system, the steering control unit (1) receives a steering instruction and detects the steering position feedback transducer (5), then the steering control unit (1) sends driving signals according to detection results so as to control the first steering control valve (3) and the second steering control valve (4), and the first steering control valve (3) and the second steering control valve (4) independently carry out pressure supply and oil-way switching on the first steering actuating drum (6) and the second steering actuating drum (7).
Description
Technical field
The present invention belongs to aircraft turn/subtract pendulum technical field, particularly relates to two remaining Nose Wheel Steering/subtract pendulum technical field.
Background technology
Aircraft turn/subtract oscillation control system is the important control system of aircraft floor when sliding, the direct direction controlling affected when aircraft floor cunning is run, important effect is equipped with to aircraft, at present, aircraft nose wheel turn/subtract oscillator system mostly be single remaining control, during pressurized strut campaign, the switching of part stage oil circuit adopts rotovalve mechanical switch, which decreases safety and the control accuracy of system.
Summary of the invention
The object of the invention is: provide a kind of two remaining Nose Wheel Steering to subtract oscillator system, add the remaining of oscillator system of turning/subtract, improve safety and the control accuracy of system.
Technical scheme of the present invention is: a kind of two remaining Nose Wheel Steering subtracts oscillator system, it is characterized in that, comprise Servo Control unit (1), turn command sensor (2), first Servo Control valve (3), second Servo Control valve (4), turning position feedback transducer (5), first turning pressurized strut (6) and the second turning pressurized strut (7), wherein turn command sensor (2) is the pedal instruction of system input chaufeur, Servo Control unit (1) receives turn command and detects turning position feedback transducer (5), Servo Control unit (1) sends according to testing result the control that drive singal realizes the first Servo Control valve (3) and the second Servo Control valve (4), first Servo Control valve (3) and the second Servo Control valve (4) realize the first turning pressurized strut (6) and the voltage supply of the second turning pressurized strut (7) and the conversion of oil circuit independently of each other respectively according to driving instruction.Adopt two covers Servo Control valve (3) effectively to improve the stability of system, adopt fax structure can improve the precision of control simultaneously.
Further, also comprise the first hydraulic power source (8) and the second hydraulic power source (9), first hydraulic power source (8) is connected with the first turning pressurized strut (6) by the first Servo Control valve (3), and the second hydraulic power source (9) is connected with the second turning pressurized strut (7) by the second Servo Control valve (4).Adopt two cover hydraulic power source (9) effectively can improve the reliability of system, avoid one of them hydraulic power source to lose efficacy and cause system not work.
The advantage that the present invention has and beneficial effect are: the turning that employing two cover Servo Control valves, two overlap hydraulic energy sources, two cover turning pressurized struts realize system/subtract pendulum function; Position feedback transducer detects front wheel positions and is transferred to control unit, and control unit controls the activated position of pressurized strut and the conversion opportunity of oil circuit.Achieve two remaining abilities of oscillator system of turning/subtract like this, instead of the function that mechanical rotary valve switches oil circuit, improve safety and the control accuracy of system.
Accompanying drawing explanation
Fig. 1 is the functional schematic of present system, and the direction of arrow represents direction, course.
Detailed description of the invention
With reference to figure 1, a kind of two remaining Nose Wheel Steering subtracts oscillator system, it is characterized in that, comprise Servo Control unit 1, turn command sensor 2, first Servo Control valve 3, second Servo Control valve 4, turning position feedback transducer 5, first turning pressurized strut 6 and the second turning pressurized strut 7, wherein turn command sensor 2 is the pedal instruction of system input chaufeur, Servo Control unit 1 receives turn command and detects turning position feedback transducer 5, Servo Control unit 1 sends according to testing result the control that drive singal realizes the first Servo Control valve 3 and the second Servo Control valve 4, first Servo Control valve 3 and the second Servo Control valve 4 realize the first turning pressurized strut 6 and the voltage supply of the second turning pressurized strut 7 and the conversion of oil circuit independently of each other respectively according to driving instruction.Adopt two cover Servo Control valves 3 effectively to improve the stability of system, adopt fax structure can improve the precision of control simultaneously.
Further, also comprise the first hydraulic power source 8 and the second hydraulic power source 9, first hydraulic power source 8 is connected with the first turning pressurized strut 6 by the first Servo Control valve 3, the second hydraulic power source 9 passes through the second Servo Control valve 4 and is connected with the second turning pressurized strut 7.Adopt two cover hydraulic power source 9 effectively can improve the reliability of system, avoid one of them hydraulic power source to lose efficacy and cause system not work.
Claims (2)
1. a two remaining Nose Wheel Steering subtracts oscillator system, it is characterized in that, comprise Servo Control unit (1), turn command sensor (2), first Servo Control valve (3), second Servo Control valve (4), turning position feedback transducer (5), first turning pressurized strut (6) and the second turning pressurized strut (7), wherein turn command sensor (2) is the pedal instruction of system input chaufeur, Servo Control unit (1) receives turn command and detects turning position feedback transducer (5), Servo Control unit (1) sends according to testing result the control that drive singal realizes the first Servo Control valve (3) and the second Servo Control valve (4), first Servo Control valve (3) and the second Servo Control valve (4) realize the first turning pressurized strut (6) and the voltage supply of the second turning pressurized strut (7) and the conversion of oil circuit independently of each other respectively according to driving instruction.
2. according to claim 1 pair of remaining Nose Wheel Steering subtracts oscillator system, it is characterized in that, also comprise the first hydraulic power source (8) and the second hydraulic power source (9), first hydraulic power source (8) is connected with the first turning pressurized strut (6) by the first Servo Control valve (3), and the second hydraulic power source (9) is connected with the second turning pressurized strut (7) by the second Servo Control valve (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535712.3A CN105564639A (en) | 2014-10-11 | 2014-10-11 | Dual-redundancy nose-wheel steering and shimmy-damping system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410535712.3A CN105564639A (en) | 2014-10-11 | 2014-10-11 | Dual-redundancy nose-wheel steering and shimmy-damping system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105564639A true CN105564639A (en) | 2016-05-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410535712.3A Pending CN105564639A (en) | 2014-10-11 | 2014-10-11 | Dual-redundancy nose-wheel steering and shimmy-damping system |
Country Status (1)
| Country | Link |
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| CN (1) | CN105564639A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216599A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of big nose wheel steering mechanism for manipulating angle of Double-linkage |
| CN110435881A (en) * | 2019-08-20 | 2019-11-12 | 中航飞机起落架有限责任公司 | It is a kind of for aircraft nose wheel electric turning and the composite control method for subtracting pendulum |
| CN110550194A (en) * | 2019-09-06 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | cooperative turning control method and cooperative turning control system for airplane |
| CN111071436A (en) * | 2019-12-12 | 2020-04-28 | 四川凌峰航空液压机械有限公司 | Mechanical-hydraulic type airplane front wheel turning anti-swing system |
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| RU2070140C1 (en) * | 1992-05-06 | 1996-12-10 | Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина" | Aircraft nose undercarriage control system |
| CN101410295A (en) * | 2006-03-27 | 2009-04-15 | 空中客车英国有限公司 | Aircraft steering angle warning system |
| CN101797978A (en) * | 2009-12-23 | 2010-08-11 | 中国航空工业集团公司第六三一研究所 | Brake integrated controller of unmanned plane |
| CN102849208A (en) * | 2011-06-27 | 2013-01-02 | 梅西耶-布加蒂-道提公司 | Method of controlling the steering of a steerable portion of an aircraft undercarriage |
| CN103105857A (en) * | 2011-11-10 | 2013-05-15 | 梅西耶-布加蒂-道提公司 | A method of resetting the orientation of an aircraft undercarriage having a steerable bottom portion |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
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2014
- 2014-10-11 CN CN201410535712.3A patent/CN105564639A/en active Pending
Patent Citations (6)
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| RU2070140C1 (en) * | 1992-05-06 | 1996-12-10 | Акционерное общество открытого типа "Авиационный комплекс им.С.В.Ильюшина" | Aircraft nose undercarriage control system |
| CN101410295A (en) * | 2006-03-27 | 2009-04-15 | 空中客车英国有限公司 | Aircraft steering angle warning system |
| CN101797978A (en) * | 2009-12-23 | 2010-08-11 | 中国航空工业集团公司第六三一研究所 | Brake integrated controller of unmanned plane |
| CN102849208A (en) * | 2011-06-27 | 2013-01-02 | 梅西耶-布加蒂-道提公司 | Method of controlling the steering of a steerable portion of an aircraft undercarriage |
| CN103105857A (en) * | 2011-11-10 | 2013-05-15 | 梅西耶-布加蒂-道提公司 | A method of resetting the orientation of an aircraft undercarriage having a steerable bottom portion |
| CN103523217A (en) * | 2012-07-06 | 2014-01-22 | 哈尔滨飞机工业集团有限责任公司 | Nose-wheel steering system of aircraft |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216599A (en) * | 2017-12-14 | 2018-06-29 | 中国航空工业集团公司成都飞机设计研究所 | A kind of big nose wheel steering mechanism for manipulating angle of Double-linkage |
| CN108216599B (en) * | 2017-12-14 | 2021-04-20 | 中国航空工业集团公司成都飞机设计研究所 | Front wheel turning mechanism with double linkage and large operation angle |
| CN110435881A (en) * | 2019-08-20 | 2019-11-12 | 中航飞机起落架有限责任公司 | It is a kind of for aircraft nose wheel electric turning and the composite control method for subtracting pendulum |
| CN110550194A (en) * | 2019-09-06 | 2019-12-10 | 中国航空工业集团公司西安飞机设计研究所 | cooperative turning control method and cooperative turning control system for airplane |
| CN111071436A (en) * | 2019-12-12 | 2020-04-28 | 四川凌峰航空液压机械有限公司 | Mechanical-hydraulic type airplane front wheel turning anti-swing system |
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Application publication date: 20160511 |