CN101134506A - Helicopter rotor control mechanism - Google Patents
Helicopter rotor control mechanism Download PDFInfo
- Publication number
- CN101134506A CN101134506A CNA2007100661381A CN200710066138A CN101134506A CN 101134506 A CN101134506 A CN 101134506A CN A2007100661381 A CNA2007100661381 A CN A2007100661381A CN 200710066138 A CN200710066138 A CN 200710066138A CN 101134506 A CN101134506 A CN 101134506A
- Authority
- CN
- China
- Prior art keywords
- feathering
- distance
- rocker arm
- variable rocker
- dish
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Toys (AREA)
Abstract
The helicopter rotor controlling mechanism includes one pitch varying rocker mounted on the oar hub, one collective pitch varying rod located inside the hollow spindle of the rotor and connected to the pitch varying rocker through one rack, and one periodical pitch varying disc with link rod connected to the pitch varying rocker through one link rod. The present invention features that the pitch varying rocker without fixing fulcrum is controlled with one collective pitch varying rod and one periodical pitch varying disc as two independent mechanisms to drive the oar holder for collective pitch variation and periodical pitch variation. The periodical pitch varying disc completes inclination motion in horizontal plane and no axial motion, while the collective pitch varying rod completes axial motion to alter the position of the rocker without altering the position of the periodical pitch varying disc.
Description
Affiliated technical field
A kind of helicopter rotor control mechanism is the mechanism that a kind of rotor pitch that is used for helicopter changes control.
Technical background
It is to realize by the total pitch of its rotor of control and the feathering of rotor that helicopter is finished aerial mission.Its principle is, rotor control mechanism orders about that the feathering dish is done vertically and lateral deflection moves realizes the feathering of rotor, do the move variation of total pitch of realizing rotor of axial direction by the feathering dish, the helicopter of countries in the world adopts this manipulation mode mostly at present.Be characterized in that cyclic pitch stick always reaches and drives the comparatively complicated link gear of a cover simultaneously apart from Adjustable length rod, link gear drives the feathering dish again and does axially, laterally reaches vertical yaw motion, realizes that total pitch of lifting airscrew changes and feathering.
Its shortcoming mainly shows as:
1. the coordinated control mechanism of feathering dish too complicated (bulb, connecting rod, connection support and distance-variable rocker arm are more) makes the reliability decrease of rotor control mechanism, and weight increases and makes maintenance cost and increases.
2. some helicopters are when changing the total pitch of rotor, and link gear has certain influence to the angle of feather, thereby make the angle control of feather lose particularity.
3. directly interlock of the feathering dish of some helicopters and oar folder, the seismic wave that rotor is produced when work is delivered to fuselage by the feathering dish easily, causes helicopter fuselage resonance easily.(the as easy as rolling off a log helicopter catastrophic failure of bringing out of the resonance of helicopter fuselage.)
4. joystick reaches always too big apart from the required moment of Adjustable length rod drive feathering dish.
Summary of the invention
The phase displacement links to each other with rocking arm by the feathering connecting rod, the control cycle displacement, it is characterized in that: distance-variable rocker arm does not have fixed pivot, always apart from displacement and feathering, overlap independently mechanism by two, total Adjustable length rod and feathering dish are controlled respectively, act on one group of distance-variable rocker arm simultaneously, drive the oar folder and always carry out apart from displacement and feathering, the feathering dish is only done the banking motion of horizontal surface, does not axially move, always apart from the axial motion of Adjustable length rod, only change the position of rocking arm, do not change feathering dish position, distance-variable rocker arm always apart from displacement point of connection and feathering point of connection fulcrum each other.
Native system is by distance-variable rocker arm 1, and distance-variable rocker arm support 2 is always apart from Adjustable length rod 3, feathering dish 4 (auto-bank unit rotating disk), main rotor hollow spindle 5, oar folder connecting rod 6, oar folder 7, propeller hub 8, feathering connecting rod 9 is always apart from Adjustable length rod joystick 10, always apart from connecting rod 11, displacement dish connecting rod 12, cyclic pitch stick 13 formations such as grade.
Its work principle is:
One, always apart from pitch control bar 10, by always apart from connecting rod 11, drive is installed in always makes axial motion apart from Adjustable length rod 3 in the main rotor hollow spindle 5, always link to each other with distance-variable rocker arm support 2 apart from Adjustable length rod 3, distance-variable rocker arm support 2 with always make axial motion simultaneously apart from Adjustable length rod 3; Point of connection E is arranged on the distance-variable rocker arm support 2, A, B, three point of connection of C are arranged on the distance-variable rocker arm support 2, the A point links to each other with the top of distance-variable rocker arm connecting rod 9, and the B point links to each other with the E point of distance-variable rocker arm support 2, and the C point links to each other with an end of oar folder connecting rod 6; Operation is always apart from pitch control bar 10, and distance-variable rocker arm 1 is a fulcrum with A, and B point perpendicular movement changes C point position, rotates thereby drive oar folder 7, realizes total pitch pitch control of helicopter.
Two, cyclic pitch stick 13, by displacement dish connecting rod 12, drive feathering dish 4 and do the banking motion of horizontal surface, by displacement connecting rod 9, change A point position, distance-variable rocker arm 1 is a fulcrum with B, A point perpendicular movement, change C point position, do the Periodic Rotating motion, realize the cyclic pitch control of helicopter thereby drive oar folder 7.
Beneficial effect
1. total pitch pitch control of rotor does not have association with the feathering dish fully, so the displacement of total pitch can not be directed into cyclic pitch stick to the controlling of feathering dish, so do not need too complicated coordinated control mechanism to come control cycle displacement dish.The control of feathering dish only needs cyclic pitch stick by the direct coordinated control of displacement dish connecting rod (perhaps by fax and hydraulic gear).Thereby simplified the helicopter rotor control mechanism complexity, and improved the reliability of its steering unit and handling, thereby the particularity of blade angle when having guaranteed feather.
Blade when work the seismic wave that produces, the buffering by distance-variable rocker arm distance-variable rocker arm B point in addition has buffer rubber gasket D, the seismic wave that is delivered to the feathering dish can significantly be decayed.So can also reducing, this maneuvering system brings out helicopter fuselage resonance inducement.
3. the distance that the distance-variable rocker arm C point that connects the oar folder order to B than the distance-variable rocker arm C point that connects the feathering dish to the distance of B point (fulcrum) is short, according to the principle of lever, and required moment in the time of can reducing cyclic pitch stick and drive oar folder change pitch.
4. not only simple and reliable, manufacturing of the present invention and maintenance cost are lower, but also can improve the reliability of helicopter rotor control mechanism.Fundamentally reduced rotor control mechanism complexity, improved reliability, also strengthened and control sensitivity.The minimizing that alleviates and make maintenance cost of rotor control mechanism weight.
Description of drawings:
The title of accompanying drawing 1, each parts of rotor control system.
Distance-variable rocker arm 1, distance-variable rocker arm support 2, always apart from Adjustable length rod 3, feathering dish 4 (auto-bank unit rotating disk) main rotor hollow spindle 5, oar folder connecting rod 6, oar folder 7, propeller hub 8, distance-variable rocker arm connecting rod 9, always apart from Adjustable length rod joystick 10, always apart from connecting rod 11, displacement dish connecting rod 12, cyclic pitch stick 13.
Accompanying drawing 2, distance-variable rocker arm constructional drawing.
A. the feathering point of connection on the distance-variable rocker arm.
B. on the distance-variable rocker arm always apart from the displacement point of connection.
C. the S. A. on the distance-variable rocker arm presss from both sides rod connection point with oar.
D. buffer rubber gasket
Claims (2)
1. helicopter rotor control mechanism, distance-variable rocker arm is installed on helicopter hub, with always link to each other with feathering dish connecting rod apart from Adjustable length rod, in the middle of always being positioned at the rotor hollow spindle apart from Adjustable length rod, the top links to each other with distance-variable rocker arm by the distance-variable rocker arm support, control the displacement of total distance, feathering links to each other with rocking arm by the feathering connecting rod, and the control cycle displacement is characterized in that: distance-variable rocker arm does not have fixed pivot, always apart from displacement and feathering, overlap independently mechanism by two, total Adjustable length rod and feathering dish are controlled respectively, act on one group of distance-variable rocker arm simultaneously, driving the oar folder carries out always apart from displacement and feathering, the feathering dish is only done the banking motion of horizontal surface, does not axially move, always apart from the axial motion of Adjustable length rod, only change the position of rocking arm, do not change feathering dish position.
2. described by claim 1, distance-variable rocker arm does not have fixed pivot, it is characterized in that: distance-variable rocker arm always apart from displacement point of connection and feathering point of connection fulcrum each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007100661381A CN101134506A (en) | 2007-08-27 | 2007-08-27 | Helicopter rotor control mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007100661381A CN101134506A (en) | 2007-08-27 | 2007-08-27 | Helicopter rotor control mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101134506A true CN101134506A (en) | 2008-03-05 |
Family
ID=39158879
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007100661381A Pending CN101134506A (en) | 2007-08-27 | 2007-08-27 | Helicopter rotor control mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101134506A (en) |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102069907A (en) * | 2010-09-16 | 2011-05-25 | 孙为红 | Device for fixing rotor angle of rotorcraft |
| CN101716996B (en) * | 2009-11-27 | 2012-03-28 | 中国直升机设计研究所 | Fishhook-type distance-variable rocker arm |
| CN103661926A (en) * | 2013-12-24 | 2014-03-26 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch device and rotor wing assembly and multiple rotor wing aircraft adopting same |
| CN104802987A (en) * | 2015-05-27 | 2015-07-29 | 刘志军 | Rotor device and rotor machine with same |
| CN104973241A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Unmanned aerial vehicle with main and auxiliary multi-rotor structure |
| CN105501434A (en) * | 2016-01-28 | 2016-04-20 | 深圳清华大学研究院 | Helicopter tail rotor torque changing operating mechanism |
| CN105775123A (en) * | 2016-02-26 | 2016-07-20 | 天峋创新（北京）科技有限公司 | Three-rotor-wing main rotor hub of unmanned helicopter |
| CN105818981A (en) * | 2016-04-06 | 2016-08-03 | 江富余 | Helicopter with rotor, fixed wing and propellers |
| CN106467165A (en) * | 2015-08-19 | 2017-03-01 | 清远市清新区立丰航空植保科技有限公司 | A kind of agricultural depopulated helicopter main rotor system device |
| CN107600415A (en) * | 2017-09-19 | 2018-01-19 | 四川建筑职业技术学院 | It is a kind of can the high motor-driven unmanned plane of tilting type using intersect displacement rotor structure |
| CN108839799A (en) * | 2018-06-04 | 2018-11-20 | 北京海空行科技有限公司 | A kind of mixing operating mechanism based on Mini Tele-Copter |
| CN110723277A (en) * | 2019-11-28 | 2020-01-24 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN113247240A (en) * | 2021-06-25 | 2021-08-13 | 四川腾盾科技有限公司 | Unmanned helicopter tail rotor pitch adjusting and operating structure |
| CN113772118A (en) * | 2021-09-03 | 2021-12-10 | 南京航空航天大学 | Method for operating rotor mechanism of coaxial rigid double-rotor test bed |
-
2007
- 2007-08-27 CN CNA2007100661381A patent/CN101134506A/en active Pending
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101716996B (en) * | 2009-11-27 | 2012-03-28 | 中国直升机设计研究所 | Fishhook-type distance-variable rocker arm |
| CN102069907A (en) * | 2010-09-16 | 2011-05-25 | 孙为红 | Device for fixing rotor angle of rotorcraft |
| CN103661926B (en) * | 2013-12-24 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch-device and rotor external member and the multi-rotor aerocraft of applying this device |
| CN103661926A (en) * | 2013-12-24 | 2014-03-26 | 深圳市大疆创新科技有限公司 | Variable-screw-pitch device and rotor wing assembly and multiple rotor wing aircraft adopting same |
| CN104802987A (en) * | 2015-05-27 | 2015-07-29 | 刘志军 | Rotor device and rotor machine with same |
| CN104973241A (en) * | 2015-07-08 | 2015-10-14 | 芜湖万户航空航天科技有限公司 | Unmanned aerial vehicle with main and auxiliary multi-rotor structure |
| CN106467165A (en) * | 2015-08-19 | 2017-03-01 | 清远市清新区立丰航空植保科技有限公司 | A kind of agricultural depopulated helicopter main rotor system device |
| CN106467165B (en) * | 2015-08-19 | 2019-03-15 | 安徽天神农业航空科技有限公司 | A kind of agricultural unmanned helicopter main rotor system device |
| CN105501434A (en) * | 2016-01-28 | 2016-04-20 | 深圳清华大学研究院 | Helicopter tail rotor torque changing operating mechanism |
| CN105775123A (en) * | 2016-02-26 | 2016-07-20 | 天峋创新（北京）科技有限公司 | Three-rotor-wing main rotor hub of unmanned helicopter |
| CN105818981A (en) * | 2016-04-06 | 2016-08-03 | 江富余 | Helicopter with rotor, fixed wing and propellers |
| CN107600415A (en) * | 2017-09-19 | 2018-01-19 | 四川建筑职业技术学院 | It is a kind of can the high motor-driven unmanned plane of tilting type using intersect displacement rotor structure |
| CN107600415B (en) * | 2017-09-19 | 2023-09-29 | 四川建筑职业技术学院 | Tilting type high-mobility unmanned aerial vehicle adopting cross-pitch-variable rotor wing structure |
| CN108839799A (en) * | 2018-06-04 | 2018-11-20 | 北京海空行科技有限公司 | A kind of mixing operating mechanism based on Mini Tele-Copter |
| CN110723277A (en) * | 2019-11-28 | 2020-01-24 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN110723277B (en) * | 2019-11-28 | 2021-05-07 | 湖南捷飞科技有限公司 | Unmanned digital telex control mechanism based on mosquito manned helicopter |
| CN113247240A (en) * | 2021-06-25 | 2021-08-13 | 四川腾盾科技有限公司 | Unmanned helicopter tail rotor pitch adjusting and operating structure |
| CN113772118A (en) * | 2021-09-03 | 2021-12-10 | 南京航空航天大学 | Method for operating rotor mechanism of coaxial rigid double-rotor test bed |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101134506A (en) | Helicopter rotor control mechanism | |
| KR101731010B1 (en) | Anti-torque tail rotor for a rotorcraft providing lift and propulsion in translation | |
| CN101293568B (en) | System for controlling flight direction | |
| CN101376433B (en) | Helicopter rotor operation method and system | |
| CN104859854B (en) | Heavy-load low-structure-complexity double-coaxial-twin-rotor unmanned aerial vehicle | |
| CN106477040B (en) | A kind of axis is interior to manipulate rotor driver | |
| CN103318407A (en) | Standalone control system of coaxial double-rotor unmanned helicopter control system | |
| US20090230252A1 (en) | Aircraft flight control | |
| CN206288235U (en) | A kind of reclining device for tiltrotor aircraft | |
| CN106477032A (en) | Multi-axis aircraft | |
| US9457889B2 (en) | Rotorcraft rotor including primary pitch horns and secondary horns | |
| CN106275390A (en) | Unmanned plane vertical fin linkage | |
| KR102674232B1 (en) | Convertible aircraft and its control method | |
| CN206634198U (en) | A kind of inclining rotary mechanism for tiltrotor | |
| CN107380428A (en) | Dish-style rotor craft | |
| CN210047624U (en) | Novel roll control structure of flapping wing aircraft | |
| CN2889427Y (en) | Steering mechanism for model helicopter | |
| CN100534863C (en) | Four channel row two-bladed helicopter | |
| CN104477383A (en) | Three-dimensional flapping flapping-wing drive mechanism | |
| US2247034A (en) | Aircraft sustaining rotor | |
| CN217146353U (en) | Fixed wing aircraft aileron control mechanism and fixed wing aircraft | |
| CN109720550A (en) | A kind of sidebar mechanism for purely mechanic flight control system | |
| CN100427169C (en) | Steering mechanism assembly of model airplane | |
| US8226026B2 (en) | Human interface rotor system helicopter (HIR) | |
| CN208993922U (en) | Pitch Combined Control Unit for coaxial double-oar helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20080305 |