CN206171816U - Tail -rotor structure of unmanned helicopter - Google Patents
Tail -rotor structure of unmanned helicopter Download PDFInfo
- Publication number
- CN206171816U CN206171816U CN201621175493.3U CN201621175493U CN206171816U CN 206171816 U CN206171816 U CN 206171816U CN 201621175493 U CN201621175493 U CN 201621175493U CN 206171816 U CN206171816 U CN 206171816U
- Authority
- CN
- China
- Prior art keywords
- tail
- rotor
- rocking arm
- rocker arm
- variable rocker
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
The utility model belongs to unmanned helicopter field discloses a tail -rotor structure of unmanned helicopter. This tail -rotor structure includes the tail -rotor axle and installs in proper order the epaxial axle sleeve of tail -rotor, bearing, manipulation transmission shaft, driving sleeve, slip control ware and tail -rotor propeller hub, tail -rotor structure still include upper portion displacement rocking arm and lower part displacement rocking arm, upper portion displacement rocking arm with lower part displacement rocking arm passes through fork -join spare and installs on the supporting seat in unmanned helicopter frame, the Y -type rocking arm of lower part displacement rocking arm one end is connected with the push rod of steering wheel, and the sharp rocking arm and the sharp rocking arm of upper portion displacement rocking arm of the other end are connected respectively the upper and lower both ends of driving sleeve, all adopt bolt or screw connection between driving sleeve, upper portion displacement rocking arm, lower part displacement rocking arm and the fork -join spare, does tail -rotor paddle on the tail -rotor propeller hub personally submit 5 with vertical 10 the contained angle. The utility model provides a tail -rotor structure damping is effectual, and the reliability is higher, has improved the security of flight.
Description
Technical field
The utility model is related to depopulated helicopter field, the tail-rotor structure of more particularly to a kind of depopulated helicopter.
Background technology
Depopulated helicopter can more flexibly perform task due to having the functions such as hovering, VTOL, therefore in army
With being widely used with civil area.It is limited yet with the rotor load of depopulated helicopter, therefore to housing construction
There is very high requirement, do not require nothing more than architecture quality gently, also require reliable transmission and efficiency high.
Helicopter tail rotor is located on tail boom, is for balancing helicopter rotor reaction torque and stable and manipulation
The part in course.Toggle is generally stirred by the way of bulb using tail control arm in existing helicopter tail rotor structure, should
The mode of kind one side stress, and there is sliding friction.Traditional tail-rotor blade is generally aligned in the same plane, this tail-rotor wave can produce compared with
Big coning angle, can not only produce larger moment of flexure reduces the service life of tail-rotor, and can produce larger resistance and vibrations danger
And the flight safety of whole unmanned helicopter system.
Utility model content
To solve above-mentioned technical problem, the utility model provides a kind of tail-rotor structure of depopulated helicopter, is carried with reaching
For a kind of purpose of the tail-rotor structure of the higher depopulated helicopter of good damping effect, reliability.
To reach above-mentioned purpose, the technical solution of the utility model is as follows：
A kind of tail-rotor structure of depopulated helicopter, including tail-rotor axle and axle sleeve, the axle being sequentially arranged on the tail-rotor axle
Hold, manipulate power transmission shaft, driving sleeve, slip controller and tail-rotor propeller hub, tail-rotor structure also includes top distance-variable rocker arm and bottom
Distance-variable rocker arm, the top distance-variable rocker arm and the bottom distance-variable rocker arm are arranged on depopulated helicopter frame by fork-shaped connector
On support base on, the fork-shaped rocking arm of bottom distance-variable rocker arm one end is connected with the push rod of depopulated helicopter steering wheel, the other end it is straight
The straight line rocking arm of line rocking arm and top distance-variable rocker arm is connected to the upper and lower ends of the driving sleeve, the driving sleeve,
Using bolt or mode connects for screw between top distance-variable rocker arm, bottom distance-variable rocker arm and fork-shaped connector；On the tail-rotor propeller hub
Tail-rotor blade is installed, the tail-rotor blade is in 5-10 ° of angle with vertical plane.
In such scheme, the tail-rotor propeller hub is connected by plunger with the tail-rotor axle, and is drawn by bulb using plunger
Bar connection tail-rotor folder, the tail-rotor folder installs tail-rotor blade using bolt, pad and nut；Preferably, the tail-rotor propeller hub
By screw blanking cover is installed to ensure the position of the plunger in side.
In such scheme, described slip controller is connected by pitch-change-link and tail connection with tail-rotor folder.
In such scheme, in order that tail-rotor blade is in 5-10 ° of angle with vertical plane, opening up inside described tail-rotor propeller hub makes
Ball-head tension rod and ladder hole of the vertical plane in 5-10 ° of angle.
By above-mentioned technical proposal, shaken by bottom displacement in the tail-rotor structure of the depopulated helicopter that the utility model is provided
The toggle that arm, top distance-variable rocker arm, fork-shaped connector and driving sleeve are constituted, can be by the pendulum of bottom distance-variable rocker arm
The dynamic linear motion for being converted into driving sleeve, makes unmanned helicopter flight speed faster more accurate；Meanwhile, adopt between each part
Bolt or mode connects for screw, can not only make the uniform force between mechanism element but also substantially reduce sliding friction, so as to reduce
Parts depreciation, and make bending moment action more accurate, extend the service life of each action component.
The tail-rotor structure under static state tail-rotor blade and vertical plane in 5-10 ° of angle, the beneficial effect of this tail-rotor
It is really：Tail-rotor angle of flap first is less, and blade will not produce larger moment of flexure, so as to improve the service life of tail-rotor；Secondly
Angle of flap diminishes, then pitch can reduce, and is conducive to reducing the resistance in flight course；Last angle of flap diminishes, depopulated helicopter
Blade vibrations in flight course can diminish, until the vibrations suffered by control system all can subtract so from tail-rotor axle to motor
It is little, so as to ensure the flight safety of whole unmanned helicopter system.
Description of the drawings
In order to be illustrated more clearly that the utility model embodiment or technical scheme of the prior art, below will be to embodiment
Or the accompanying drawing to be used needed for description of the prior art is briefly described.
Fig. 1 is the couple schematic diagram for acting on depopulated helicopter provided by the utility model；
Fig. 2 is the front view of depopulated helicopter tail-rotor structure provided by the utility model；
Fig. 3 is the decomposing schematic representation of depopulated helicopter tail-rotor driving structure provided by the utility model；
Fig. 4 is the decomposing schematic representation of depopulated helicopter tail-rotor attachment structure provided by the utility model；
Fig. 5 a are the front views of tail-rotor propeller hub provided by the utility model；
Fig. 5 b are the sectional views in tail-rotor propeller hub inner step hole provided by the utility model.
In figure, 1. tail-rotor axle；2. axle sleeve；3. bearing；4. power transmission shaft is manipulated；5. top distance-variable rocker arm；6. driving sleeve；7.
Slip controller；8. pitch-change-link；9. fork-shaped connector；10. bottom distance-variable rocker arm；11. support bases；12. tail-rotor blades；13.
Tail-rotor is pressed from both sides；14. ball-head tension rods；15. tail-rotor propeller hubs；16. plungers；17. blanking covers；18. tails connect；19th, ladder hole.
Specific embodiment
The utility model aims to provide a kind of tail-rotor structure of depopulated helicopter, to solve prior art in solve existing skill
Tail-rotor structural damping effect in art is bad, the problem of security difference.
In order that those skilled in the art can be better understood from the utility model, with reference to specific embodiment and attached
The utility model is described in further detail for figure.
The tail-rotor structure of depopulated helicopter as shown in Figures 2 and 3, including tail-rotor axle 1 and be sequentially arranged on tail-rotor axle 1
On axle sleeve 2, bearing 3, manipulate power transmission shaft 4, driving sleeve 6, slip controller 7 and tail-rotor propeller hub 15, tail-rotor structure also includes
Top distance-variable rocker arm 5 and bottom distance-variable rocker arm 10, the top distance-variable rocker arm 5 and the bottom distance-variable rocker arm 10 are connected by fork-shaped
Fitting 9 is arranged on the support base 11 in depopulated helicopter frame, the fork-shaped rocking arm and steering wheel of the one end of bottom distance-variable rocker arm 10
Push rod connects, and the straight line rocking arm of the other end is connected to the upper of the driving sleeve 6 with the straight line rocking arm of top distance-variable rocker arm 5
Lower two ends, adopt bolt between the driving sleeve 6, top distance-variable rocker arm 5, bottom distance-variable rocker arm 10 and fork-shaped connector 9
Or mode connects for screw；Tail-rotor blade 12 is installed, the tail-rotor blade 12 is in 5-10 ° of angle with vertical plane on the tail-rotor propeller hub 15.
With reference to Fig. 4, tail-rotor propeller hub 15 is connected by plunger 16 with the tail-rotor axle 1, and is drawn by bulb using plunger 16
The connection tail-rotor of bar 14 folder 13, tail-rotor folder 13 installs tail-rotor blade 12 using bolt, pad and nut；The side of tail-rotor propeller hub 15 leads to
Cross mode connects for screw blanking cover 17 to ensure the position of the plunger 16；Described slip controller 7 is connected by pitch-change-link 8 and tail
18 are connected with tail-rotor folder 13, and the side of pitch-change-link 8 is connected using bolt and nut with slip controller 7, and opposite side is adopted
Screw is connected by tail connection 18 with tail-rotor folder 13.In order that tail-rotor blade and vertical plane are in 5-10 ° of angle, tail-rotor propeller hub
Inside opens up makes ball-head tension rod with ladder hole 19 of the vertical plane in 5-10 ° of angle.
During work, by steering wheel push-and-pull bottom distance-variable rocker arm 10, bottom distance-variable rocker arm 10 drive simultaneously fork-shaped connector 9, on
Portion's distance-variable rocker arm 5, driving sleeve 6 and slip controller 7 are for linear motion so as to realizing variable pitch contro l along tail-rotor axle 1.Bottom
Distance-variable rocker arm 10, top distance-variable rocker arm 5, fork-shaped connector 9 and driving sleeve 6 constitute toggle, can be by bottom
The swing of distance-variable rocker arm 10 is converted into the linear motion of driving sleeve 6, makes unmanned helicopter flight speed faster more accurate.At this
In utility model, bottom distance-variable rocker arm 10, top distance-variable rocker arm 5, fork-shaped connector 9 and driving sleeve 6 are with bolts, no
But can make the stress between mechanism element evenly and substantially reduce sliding friction, and make bending moment action more accurate, prolong
The service life of each action component of length.
In the tail-rotor structure of the depopulated helicopter provided with reference to Fig. 1, the utility model, tail-rotor blade is ensureing structure connection
On the premise of not conflicting, the angle for being presented 5-10 ° with vertical plane in the reverse direction of thrust is being produced.
Under static state with vertical plane in 5-10 ° of angle, this is due to the inner step through hole of tail-rotor propeller hub 15 to blade
Axis be not arranged on the same straight line (be specifically shown in Fig. 5 a and Fig. 5 b), so as to install during ball-head tension rod 14 with vertical plane generate 5-
10 ° of angle.
The foregoing description of the disclosed embodiments, enables professional and technical personnel in the field to realize or new using this practicality
Type.Various modifications to these embodiments will be apparent for those skilled in the art, determine herein
The General Principle of justice can in other embodiments be realized in the case of without departing from spirit or scope of the present utility model.Cause
This, the utility model is not intended to be limited to the embodiments shown herein, and is to fit to and principles disclosed herein
The most wide scope consistent with features of novelty.
Claims (5)
1. a kind of tail-rotor structure of depopulated helicopter, including tail-rotor axle and be sequentially arranged on the tail-rotor axle axle sleeve, bearing,
Manipulate power transmission shaft, driving sleeve, slip controller and tail-rotor propeller hub, it is characterised in that：The tail-rotor structure also becomes including top
Away from rocking arm and bottom distance-variable rocker arm, the top distance-variable rocker arm and the bottom distance-variable rocker arm are arranged on nothing by fork-shaped connector
On support base in people's helicopter frame, the fork-shaped rocking arm of bottom distance-variable rocker arm one end connects with the push rod of depopulated helicopter steering wheel
Connect, the straight line rocking arm of the other end is connected to the upper and lower ends of the driving sleeve with the straight line rocking arm of top distance-variable rocker arm,
Using bolt or mode connects for screw between the driving sleeve, top distance-variable rocker arm, bottom distance-variable rocker arm and fork-shaped connector；Institute
State and tail-rotor blade is installed on tail-rotor propeller hub, the tail-rotor blade is in 5-10 ° of angle with vertical plane.
2. tail-rotor structure according to claim 1, it is characterised in that：The tail-rotor propeller hub is by plunger and the tail-rotor axle
Connection, and tail-rotor folder is provided with by ball-head tension rod using plunger, the tail-rotor folder installs tail-rotor using bolt, pad and nut
Blade.
3. tail-rotor structure according to claim 2, it is characterised in that：The side of the tail-rotor propeller hub is provided with by screw
Blanking cover is ensureing the position of the plunger.
4. tail-rotor structure according to claim 2, it is characterised in that：Described slip controller is by pitch-change-link and tail
Connection is connected with tail-rotor folder.
5. tail-rotor structure according to claim 1, it is characterised in that：Open up inside tail-rotor propeller hub make ball-head tension rod with it is vertical
Ladder hole of the face in 5-10 ° of angle, makes tail-rotor blade be in 5-10 ° of angle with vertical plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621175493.3U CN206171816U (en) | 2016-10-26 | 2016-10-26 | Tail -rotor structure of unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621175493.3U CN206171816U (en) | 2016-10-26 | 2016-10-26 | Tail -rotor structure of unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206171816U true CN206171816U (en) | 2017-05-17 |
Family
ID=58683010
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621175493.3U Expired - Fee Related CN206171816U (en) | 2016-10-26 | 2016-10-26 | Tail -rotor structure of unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206171816U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107140199A (en) * | 2017-05-27 | 2017-09-08 | 昆山优尼电能运动科技有限公司 | Portable unmanned machine, blade runner assembly, rotation system and its assemble method |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
-
2016
- 2016-10-26 CN CN201621175493.3U patent/CN206171816U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107140199A (en) * | 2017-05-27 | 2017-09-08 | 昆山优尼电能运动科技有限公司 | Portable unmanned machine, blade runner assembly, rotation system and its assemble method |
| CN111547252A (en) * | 2020-04-21 | 2020-08-18 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
| CN111547252B (en) * | 2020-04-21 | 2021-12-24 | 中国航发湖南动力机械研究所 | Tail rotor pitch control shaft device and preparation method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205499338U (en) | Self -adaptation variable -pitch propeller oar and aircraft | |
| EP2062627A1 (en) | A model helicopter | |
| CN101433766A (en) | Counterbalance system of remote-control model helicopter | |
| CN206171816U (en) | Tail -rotor structure of unmanned helicopter | |
| CN105599898A (en) | Three-rotor-wing tail rotor hub of unmanned helicopter | |
| CN205524970U (en) | Three rotor tail -rotor hubs of unmanned helicopter | |
| CN205366061U (en) | 32 rotor crafts on eight arms of on -plane surface | |
| CN107985586A (en) | A kind of life-cycle pulp hub structure | |
| CN207466966U (en) | A kind of dynamic displacement quadrotor unmanned plane of oil | |
| CN201825236U (en) | Driving mechanism for steel-wire hinged minisize flapping-wing aircraft | |
| CN210047624U (en) | Novel roll control structure of flapping wing aircraft | |
| CN108033007B (en) | Flapping wing aircraft transmission part based on Y-shaped structure and implementation method | |
| CN109466749B (en) | Helicopter variable-pitch drive assembly and helicopter | |
| CN207015582U (en) | Depopulated helicopter displacement limit adjusting mechanism | |
| CN114394232B (en) | Flapping wing-flapping rotor wing multi-flight mode bionic aircraft | |
| CN109383788A (en) | A kind of cross flow fan lift-rising autogyro | |
| CN201086823Y (en) | Rank double-oar minitype helicopter | |
| CN209479973U (en) | A kind of cross flow fan lift-rising autogyro | |
| CN209617482U (en) | Seesaw type unmanned plane rotor and unmanned plane | |
| CN107600426A (en) | Single-power drives feather multi-rotor unmanned aerial vehicle | |
| CN105775123A (en) | Three-rotor-wing main rotor hub of unmanned helicopter | |
| CN109677603A (en) | Helicopter rotor operation device and rotor driver | |
| CN105599893A (en) | Variable pitch propeller mechanism | |
| CN106314772A (en) | Non-planar eight-arm thirty-two-rotor craft | |
| US20230091534A1 (en) | Link rotor head and unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170517 Termination date: 20191026 |