CN101962075A - Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft - Google Patents
Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft Download PDFInfo
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- CN101962075A CN101962075A CN 201010510200 CN201010510200A CN101962075A CN 101962075 A CN101962075 A CN 101962075A CN 201010510200 CN201010510200 CN 201010510200 CN 201010510200 A CN201010510200 A CN 201010510200A CN 101962075 A CN101962075 A CN 101962075A
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- tilting
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- 230000007246 mechanism Effects 0.000 title claims abstract description 34
- 230000003466 anti-cipated effect Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000014759 maintenance of location Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
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- 230000001141 propulsive effect Effects 0.000 description 1
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Abstract
The invention relates to a tilting mechanism, a running mode of the tilting mechanism, and the application of the tilting mechanism in a tilting rotorcraft, belonging to the technical field of tilting mechanisms. The tilting mechanism drives a tilting shaft to tilt by using a steering engine through a worm gear device, and guarantees the tilting shaft after tilting is stabilized on a preset position by using the self-locking characteristics of the worm gear device in the process of rotation. The tilting mechanism is provided with a feedback loop, the tilting shaft is provided with a rotation ring, the rotation ring is connected with one end of a draw bar, and the other end of the draw bar is connected with an angular transducer; the rotation shaft of the angular transducer and the tilting shaft rotate synchronously, and the angular transducer transfers tilting angles into electrical signals and then provides the electrical signals for a control system so as to realize feedback control.
Description
Affiliated technical field
The present invention relates to a kind of inclining rotary mechanism and mode of operation thereof and the application on tiltrotor, belong to the inclining rotary mechanism technical field.
Background technology
Inclining rotary mechanism is a kind of angle adjusting mechanism.All used dissimilar inclining rotary mechanisms such as crane, motor turning dish etc.Common mechanical reclining device is with the rotation of motor direct-drive tiliting axis, though this method is simple and practical, it is not high to handle precision, and the position after verting is subjected to external disturbance easily and out of position, is difficult to keep stable.For the technical field that needs accuracy control, inclining rotary mechanism commonly used is difficult to reach requirement.Such as tiltrotor, it is a kind of course of new aircraft that fixed wing aircraft and helicopter advantage are combined together, the design of rotor inclining rotary mechanism is one of its core technology, is the device of realizing that such aircraft is changed between helicopter flight pattern and fixed-wing offline mode.
Summary of the invention
Handle defectives such as the not high and poor stability of precision in order to overcome existing inclining rotary mechanism, the invention provides a kind of inclining rotary mechanism and mode of operation thereof.The rotor inclining rotary mechanism that this mechanism can be used as unmanned tiltrotor aircraft uses.
A kind of inclining rotary mechanism is characterized in that: comprise installing frame, be installed on tiliting axis on the installing frame by the bearing that verts, the tiliting axis outer ring also is equipped with worm gear and change; Also by the screw shaft bearing worm screw that cooperates with described worm gear is installed on the installing frame, worm screw is driven by steering wheel; Described change links to each other with angular transducer by pull bar, and angular transducer feeds back to control loop with angle of inclination with the form of electric signal.
The mode of operation of above-mentioned inclining rotary mechanism is characterized in that: the control signal band that steering wheel is sent according to receiver changes worm screw, and worm screw drives worm gear and rotates corresponding angle, thereby realizes that rotor verts; The latching characteristics of worm-and-wheel gear guarantees promptly to be stabilized in the desired location after rotor verts, and is not subjected to external disturbance and departs from this position; Driving change when worm screw is rotated rotates, change is rotated synchronously by pull bar and the rotating shaft and the tiliting axis that drive angular transducer, angular transducer is converted to electric signal with angle of inclination, feed back to control system, thereby judge that whether the rotor tilt angle reaches anticipated value, has accomplished the accuracy control to the rotor tilt angle.
The rotor that above-mentioned inclining rotary mechanism is applied to tiltrotor aircraft verts.
The invention has the beneficial effects as follows: worm gearing is compared required propulsive effort with through-coupling little, can realize mechanism's self-locking, simultaneously can realize accuracy control to tilt angle by the backfeed loop of component set-ups such as angular transducer.This mechanism can accuracy control rotor tilt angle, and mechanism's self-locking after rotor reaches the desired location, has eliminated the influence of external disturbance.
Description of drawings
Fig. 1 is the inclining rotary mechanism overall diagram;
Number in the figure title: 1. worm gear, 2. worm screw, 3. change, the bearing that 4. verts, 5. tiliting axis, 6. steering wheel, 7. angular transducer, 8. pull bar, 9. worm shaft bearing, 10. installing frame.
The specific embodiment
Two secondary rotors link to each other by tiliting axis 5 among Fig. 1, and waist is installed inclining rotary mechanism, and its inner structure as shown in the figure.Worm gear 1 links to each other with tiliting axis 5, passes through screw retention.Worm screw 2 is driven by steering wheel 6, and two ends are supported with bearing seat 9.Change 3 links to each other with tiliting axis 5, passes through screw retention.Pull bar 8 connection angle sensors 7 and change 3, tiliting axis 5 drives angular transducers 7 by change 3 and pull bar 8 and rotates, and angular transducer 7 feeds back to control loop with angle of inclination with the form of electric signal.The assembly relation of whole inclining rotary mechanism as shown in the figure, tiliting axis 5 links to each other by bearing 4 with installing frame 10, worm shaft bearing 9 is fixed by bolts to the bottom surface of installing frame 10.
Claims (3)
1. inclining rotary mechanism is characterized in that:
Comprise installing frame (10), be installed on tiliting axis (5) on the installing frame (10) by the bearing that verts (4), tiliting axis (5) outer ring also is equipped with worm gear (1) and change (3);
Also by worm shaft bearing (9) worm screw (2) that cooperates with described worm gear (1) is installed on the installing frame (10), worm screw (2) is driven by steering wheel (6);
Described change (3) links to each other with angular transducer (7) by pull bar (8), and angular transducer (7) feeds back to control loop with angle of inclination with the form of electric signal.
2. according to the mode of operation of the described inclining rotary mechanism of claim 1, it is characterized in that:
The control signal band that steering wheel (6) is sent according to receiver changes worm screw (2), and worm screw (2) drives worm gear (1) and rotates corresponding angle, thereby realizes that rotor verts; The latching characteristics of worm-and-wheel gear guarantees promptly to be stabilized in the desired location after rotor verts, and is not subjected to external disturbance and departs from this position;
Driving change (3) when worm screw (2) is rotated rotates, change (3) is rotated synchronously by rotating shaft and the tiliting axis that pull bar (8) drives angular transducer (7), angular transducer (7) is converted to electric signal with angle of inclination, feed back to control system, thereby judge that whether the rotor tilt angle reaches anticipated value, has accomplished the accuracy control to the rotor tilt angle.
3. inclining rotary mechanism according to claim 1 is as the application of the rotor inclining rotary mechanism of tiltrotor aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010510200 CN101962075A (en) | 2010-10-18 | 2010-10-18 | Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010510200 CN101962075A (en) | 2010-10-18 | 2010-10-18 | Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101962075A true CN101962075A (en) | 2011-02-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010510200 Pending CN101962075A (en) | 2010-10-18 | 2010-10-18 | Tilting mechanism, running mode of tilting mechanism, application of tilting mechanism in tilting rotorcraft |
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| CN (1) | CN101962075A (en) |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431646A (en) * | 2011-11-29 | 2012-05-02 | 南京航空航天大学 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
| CN103010450A (en) * | 2012-11-20 | 2013-04-03 | 无锡市万凌钢铁有限公司 | Synchronous rotating mechanism for left and right wings of transport helicopter |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN103935510A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft |
| CN105364191A (en) * | 2015-12-08 | 2016-03-02 | 天津市轩宇机床设备有限公司 | Indexing alignment device and spiral bevel gear milling machine |
| CN106132825A (en) * | 2013-12-23 | 2016-11-16 | 李尚泫 | Many rotor flyings body |
| CN106314771A (en) * | 2015-06-27 | 2017-01-11 | 深圳市大疆创新科技有限公司 | Aircraft and power device |
| CN106427439A (en) * | 2016-10-18 | 2017-02-22 | 南京航空航天大学 | Rotor hub lifting system and control method thereof |
| CN106628167A (en) * | 2016-12-22 | 2017-05-10 | 西北工业大学 | Tilting mechanism for tilt rotor |
| CN106672204A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Tilting mechanism for tilting rotor wing airplane |
| CN107097938A (en) * | 2017-03-20 | 2017-08-29 | 长光卫星技术有限公司 | A kind of inclining rotary mechanism for the quadrotor that verts |
| CN108820203A (en) * | 2018-05-29 | 2018-11-16 | 中山星图航空航天技术有限公司 | A kind of unmanned plane and flight control system of tilting type VTOL fixed-wing |
| CN109204806A (en) * | 2017-07-06 | 2019-01-15 | 深圳市道通智能航空技术有限公司 | Aircraft, driving mechanism of verting and its control method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN2687725Y (en) * | 2003-05-20 | 2005-03-23 | 上海工业自动化仪表研究所 | Corner type intelligent electric actuating mechanism |
| CN2909519Y (en) * | 2006-04-26 | 2007-06-06 | 深圳市翠涛自动化设备有限公司 | Whole closed-loop high precision servo rotation workbench |
| CN201951711U (en) * | 2010-10-18 | 2011-08-31 | 南京航空航天大学 | Tilting mechanism |
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2010
- 2010-10-18 CN CN 201010510200 patent/CN101962075A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2687725Y (en) * | 2003-05-20 | 2005-03-23 | 上海工业自动化仪表研究所 | Corner type intelligent electric actuating mechanism |
| CN2909519Y (en) * | 2006-04-26 | 2007-06-06 | 深圳市翠涛自动化设备有限公司 | Whole closed-loop high precision servo rotation workbench |
| CN201951711U (en) * | 2010-10-18 | 2011-08-31 | 南京航空航天大学 | Tilting mechanism |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102431646A (en) * | 2011-11-29 | 2012-05-02 | 南京航空航天大学 | Dual-whirl wing tilting mechanism of single-engine tilting whirl wing aerocraft |
| CN103010450A (en) * | 2012-11-20 | 2013-04-03 | 无锡市万凌钢铁有限公司 | Synchronous rotating mechanism for left and right wings of transport helicopter |
| CN103072688A (en) * | 2013-01-22 | 2013-05-01 | 西安交通大学 | Tiltable four-rotor wing aircraft |
| CN106132825B (en) * | 2013-12-23 | 2018-05-11 | 李尚泫 | More rotor flying bodies |
| CN106132825A (en) * | 2013-12-23 | 2016-11-16 | 李尚泫 | Many rotor flyings body |
| CN103935510A (en) * | 2014-04-15 | 2014-07-23 | 西安交通大学 | Tilted four-rotor aircraft |
| CN106314771B (en) * | 2015-06-27 | 2019-10-29 | 深圳市大疆创新科技有限公司 | Aircraft and its power device |
| CN106314771A (en) * | 2015-06-27 | 2017-01-11 | 深圳市大疆创新科技有限公司 | Aircraft and power device |
| CN105364191B (en) * | 2015-12-08 | 2018-06-15 | 天津市轩宇机床设备有限公司 | Index adjusting mechanism and spiral bevel gear milling machine |
| CN105364191A (en) * | 2015-12-08 | 2016-03-02 | 天津市轩宇机床设备有限公司 | Indexing alignment device and spiral bevel gear milling machine |
| CN106427439A (en) * | 2016-10-18 | 2017-02-22 | 南京航空航天大学 | Rotor hub lifting system and control method thereof |
| CN106427439B (en) * | 2016-10-18 | 2018-11-09 | 南京航空航天大学 | A kind of rotor hub jacking system and its control method |
| CN106628167A (en) * | 2016-12-22 | 2017-05-10 | 西北工业大学 | Tilting mechanism for tilt rotor |
| CN106672204A (en) * | 2017-03-09 | 2017-05-17 | 北京天宇新超航空科技有限公司 | Tilting mechanism for tilting rotor wing airplane |
| CN107097938A (en) * | 2017-03-20 | 2017-08-29 | 长光卫星技术有限公司 | A kind of inclining rotary mechanism for the quadrotor that verts |
| CN109204806A (en) * | 2017-07-06 | 2019-01-15 | 深圳市道通智能航空技术有限公司 | Aircraft, driving mechanism of verting and its control method |
| CN108820203A (en) * | 2018-05-29 | 2018-11-16 | 中山星图航空航天技术有限公司 | A kind of unmanned plane and flight control system of tilting type VTOL fixed-wing |
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Application publication date: 20110202 |