CN207000820U - A kind of centrifugal flapping hinge rotor head - Google Patents
A kind of centrifugal flapping hinge rotor head Download PDFInfo
- Publication number
- CN207000820U CN207000820U CN201720522507.2U CN201720522507U CN207000820U CN 207000820 U CN207000820 U CN 207000820U CN 201720522507 U CN201720522507 U CN 201720522507U CN 207000820 U CN207000820 U CN 207000820U
- Authority
- CN
- China
- Prior art keywords
- flapping hinge
- hinge
- blade
- centrifugal
- rotor head
- 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 provides a kind of centrifugal flapping hinge rotor head, belongs to unmanned air vehicle technique field.It includes rotor centers axle, middle, flapping hinge, transverse axis, lead lag hinge, the oar folder being sequentially connected from inside to outside；The flapping hinge and the oar folder between by be arranged on it is described it is middle in the transverse axis connect, the oar is pressed from both sides for installing blade, the lead lag hinge is arranged between the oar folder and the blade, the middle activity point of view for defining the flapping hinge, blade rotation and the flapping hinge are in same axial line, the lower section for the axial line that the central shaft of the flapping hinge rotates in the blade.Core type flapping hinge rotor head provided by the utility model, design a kind of new flapping hinge structure so that provide a downward power to blade when blade rotates, reduce the angle that blade raises up, increase oar effect, and then increase the stability of aircraft.
Description
Technical field
Unmanned air vehicle technique field is the utility model is related to, more particularly to a kind of with centrifugal flapping hinge rotor head.
Background technology
Multi-rotor unmanned aerial vehicle, it is a kind of special pilotless helicopter with three and above rotor shaft.It passes through
Motor rotation on each axle, drives rotor, so as to produce a liter thrust.Rotor always away from fixation, rather than general helicopter
It is variable like that.By changing the relative rotation speed between different rotors, thus it is possible to vary the size of single shaft propulsive force, so as to control flight
The running orbit of device.
Existing multi-rotor unmanned aerial vehicle part only has pitch hinge and lead lag hinge more, is seldom designed using flapping hinge.So that fly
The vibrations of aircraft are relatively large during row, and airframe is larger for the reacting condition of slight posture.Common shimmy device structure ratio
It is more complicated, it is heavy, be not suitable for applying on unmanned plane.Due to the linear velocity of blade periphery during the blade rotation of multi-rotor unmanned aerial vehicle
Higher than the linear velocity of inner circumferential, cause the lift of blade periphery larger, so as to which blade is influenceed when rotating by centrifugal force and lift,
Blade can cause oar effect to reduce into the state of raising up, kinetic energy loss, reduce the stability of aircraft.How to solve more rotors nobody
The blade of machine rotates, and is imitated with obtaining higher oar, the stability for improving aircraft is significant.
Utility model content
For above-mentioned technical problem, the utility model provides a kind of centrifugal flapping hinge rotor head, and design is a kind of new
Flapping hinge structure so that a downward power is provided to blade when blade rotates, reduces the angle that blade raises up, increase oar is imitated,
And then increase the stability of aircraft.
The utility model provides a kind of centrifugal flapping hinge rotor head, including the rotor centers being sequentially connected from inside to outside
Axle, middle, flapping hinge, transverse axis, lead lag hinge, oar folder；The flapping hinge and the oar folder between by be arranged on it is described it is middle in
Transverse axis connection, the oar pressed from both sides for installing blade, and the lead lag hinge is arranged between the oar folder and the blade, institute
Blade rotation is stated with the flapping hinge in same axial line, the axial line that the central shaft of the flapping hinge rotates in the blade
Lower section.
Further, the flapping hinge central shaft is arranged on the middle lower section, is raised up for reducing when blade rotates
Angle.
Further, it is described middle to be provided with upper limit axle and lower limit axle, the upper limit axle and the lower limit axle
It is arranged with rubber blanket；Middle flapping hinge central shaft, the upper limit axle and the lower limit axle of being provided with is waved around described
Dance hinge central axis so that the flapping hinge can move up and down.
Further, the transverse axis is provided with meshing point, and the meshing point is meshed with the flapping hinge central shaft.
Further, the middle insurance jackscrew being provided with for preventing the transverse axis from rocking.
Further, it is described it is middle be provided with insurance pin, the insurance pin is in an interference fit through described
Transverse axis.
Further, the insurance pin is provided with the pin jackscrew for preventing that the insurance pin from skidding off.
Further, it is provided with the transverse axis for preventing the rotor head from penetrating the jump ring of oar.
Further, the lead lag hinge is arranged on groove of the oar folder corresponding to the blade, and the lead lag hinge uses
Rubber is made.
Further, the centrifugal flapping hinge rotor head can be applied to the rotor structure of varying number blade.
A kind of centrifugal flapping hinge rotor head provided by the utility model, pass through middle, flapping hinge, the horizontal stroke being sequentially connected
Axle, lead lag hinge, oar folder, are arranged on the centrifugal flapping hinge rotor head by blade, are rotated by the blade and waved with described
Hinge is in same axial line, the lower section for the axial line that the central shaft of the flapping hinge rotate in the blade so that during blade rotation
A downward power is provided to blade, reduces the angle that blade raises up, increase oar effect, and then increase the stability of aircraft.
Brief description of the drawings
It is described in detail by way of example, and not by way of limitation with reference to the accompanying drawings hereinafter more of the present utility model specific real
Apply example.Identical reference denotes same or similar part or part in accompanying drawing.It should be appreciated by those skilled in the art that
What these accompanying drawings were not necessarily drawn to scale.In accompanying drawing：
Fig. 1 is the structural representation according to a kind of centrifugal flapping hinge rotor head of the utility model one embodiment；
Fig. 2 is a kind of partial structural diagram of centrifugal flapping hinge rotor head shown in Fig. 1；
Fig. 3 is the structural representation according to a kind of transverse axis of centrifugal flapping hinge rotor head of the utility model one embodiment
Figure；
Fig. 4 is the central shaft according to a kind of flapping hinge of centrifugal flapping hinge rotor head of the utility model one embodiment
Schematic view of the mounting position.
Embodiment
Fig. 1 is according to the structural representation of centrifugal flapping hinge rotor head of the utility model one embodiment a kind of.Such as Fig. 1
It is shown, a kind of centrifugal flapping hinge rotor head provided by the utility model, including the rotor centers axle being sequentially connected from inside to outside
9th, middle 1, flapping hinge 8, transverse axis 10 (figure 3 illustrates), lead lag hinge 5, oar folder 6；Between the flapping hinge 8 and oar folder 6
Connected by the transverse axis 10 being arranged in described middle 1, the oar folder 6 is used to install blade 12 (figure 4 illustrates), institute
State lead lag hinge 5 to be arranged between the oar folder 6 and the blade 12, described middle 1 defines the movable corner of the flapping hinge 8
Degree, with the flapping hinge 8 in same axial line, the axial line where it is the axle of rotor centers axle 9 for the rotation of blade 12
To.The central shaft of the flapping hinge 8 is arranged on the lower section of the axial line of the blade 12 rotation.Described middle 1 and the transverse axis
10 use redundance type structure, and the redundance type structure can be applicable to the varying numbers such as two oars, four oars, five oars, six oars, eight oars
The rotor structure of blade.
Fig. 4 is the central shaft according to a kind of flapping hinge of centrifugal flapping hinge rotor head of the utility model one embodiment
Schematic view of the mounting position.As shown in figure 4, blade 12 is influenceed by centrifugal force F1 and lift F2 when rotated, blade 12 can be in
Reveal the state to raise up, now, blade 12 is supplied to the lift of aircraft 11 to have a certain degree of loss, reduces oar effect, shadow
The kinetic energy of aircraft 11 is rung, and then reduces the stability of aircraft 11.In a specific embodiment, the center of flapping hinge 8
Axle is arranged on middle 1 lower section, for reducing the angle to be raised up when blade 12 rotates.So, the central shaft peace of flapping hinge 8
Mounted in the lower section of the axial line of the blade 12 rotation, blade 12 can be made when rotated, providing one to blade 12 pulls down
Power, the angle that blade 12 raises up is reduced, it is effective to increase oar effect, and then increase the stability of aircraft 11.
Fig. 2 is a kind of partial structural diagram of centrifugal flapping hinge rotor head shown in Fig. 1.Fig. 3 is according to this practicality
A kind of structural representation of the transverse axis of the centrifugal flapping hinge rotor head of new one embodiment.It is subject to reference to Fig. 2 and Fig. 3
Explanation.
Specifically, the redundance type structure be included in redundance type on the transverse axis 10 be provided with insurance jackscrew mount point 101,
Insure pin through hole 103, flapping hinge central shaft meshing point 108, jump ring mount point 102.
Described middle 1 is provided with the insurance jackscrew 4 for preventing the transverse axis 10 from rocking.Insure jackscrew 4 and pass through middle 1,
It is attached at the insurance jackscrew mount point 101 of transverse axis 10, prevents transverse axis 10 produces from rocking, simultaneously for preventing that penetrating oar also produces one
Determine effect.Described middle 1 is provided with insurance pin 3, and the insurance pin 3 runs through the transverse axis 10 in an interference fit.
The insurance pin 3 is provided with the pin jackscrew for preventing that the insurance pin 3 from skidding off.The transverse axis 10 is provided with meshing point 108,
The meshing point 108 is meshed with the central shaft of flapping hinge 8.The transverse axis 10 is provided with jump ring mount point 102, jump ring installation
Point 102 is installed for preventing the rotor head from penetrating the jump ring of oar.Jump ring plays protection jointly with insurance jackscrew 4 and insurance pin 3
Effect, prevent rotor head from rotating because penetrating oar caused by centrifugal force.The insurance jackscrew mount point 101, insurance pin pass through
Perforation 103, flapping hinge central shaft meshing point 108, the uniform force of jump ring mount point 102, mutually bear the rotations such as oar folder, propeller
The centrifugal force to get up, aerodynamic force, situations such as vibrations, even if being damaged at wherein three, remain to work at residue one, prevent from penetrating oar,
Ensure the normal landing of aircraft.
The redundance type structure also includes the upper limit axle 2, lower limit axle 7 and the central shaft of flapping hinge 8.Upper limit axle 2
It is the alignment pin of flapping hinge 8 with lower limit axle 7, rubber blanket, rubber blanket is arranged with the outside of upper limit axle 2 and lower limit axle 7
Elastic deformation is produced after stress, around the central axis of flapping hinge 8 so that flapping hinge 8 moves up and down.Upper limit axle 2, lower limit
Axle 7 and the axle uniform stressed of flapping hinge 8 three, flapping hinge mutually being born, oar presss from both sides, the centrifugal force that propeller etc. rotates, aerodynamic force,
Situations such as vibrations.Under limiting case, any one axle fracture of three axles, by other two axle stress.Even if any two axle fracture, also have
One root axle can prevent from penetrating oar with stress, ensure that aircraft can be with normal landing.
Further, the lead lag hinge 5 is arranged on the groove that the oar folder 6 corresponds to the blade, and the lead lag hinge 5 is adopted
It is made of rubber.Lead lag hinge 5 reaches shimmy effect using the elastic deformation of rubber.The structure of lead lag hinge 5 is simple, cost is low,
Effect is preferable, can be applicable to the rotor structure of the varying number blades such as two oars, four oars, five oars, six oars, eight oars.
Dual redundant design structure provided by the utility model, flapping hinge structure are applied to two oars, four oars, five oars, six oars,
The rotor structure of the varying number blade such as eight oars.
A kind of centrifugal flapping hinge rotor head provided by the utility model, pass through middle, flapping hinge, the horizontal stroke being sequentially connected
Axle, lead lag hinge, oar folder, the centrifugal flapping hinge rotor head is arranged on by blade, and oar folder and horizontal stroke are prevented by redundance type structure
Axle is disconnected de-, prevents from penetrating oar, to ensure the flight safety performance of unmanned plane.
A kind of centrifugal flapping hinge rotor head provided by the utility model, redundance type is provided with insurance top on the transverse axis
Silk mount point, insurance pin through hole, flapping hinge central shaft meshing point, jump ring mount point, the insurance jackscrew mount point, insurance
Pin through hole, flapping hinge central shaft meshing point, jump ring mount point uniform force, mutually bear the rotations such as oar folder, propeller and rise
The centrifugal force come, aerodynamic force, situations such as vibrations, even if being damaged at wherein three, remain to work at residue one, prevent from penetrating oar, protect
Demonstrate,prove the normal landing of aircraft.The redundance type structure also includes the upper limit axle, lower limit axle and flapping hinge central shaft, three axles
Uniform stressed, mutually bears flapping hinge, oar folder, the centrifugal force that propeller etc. rotates, aerodynamic force, situations such as vibrations.The limit
In the case of, any one axle fracture of three axles, by other two axle stress.Even if any two axle fracture, also root axle can be by
Power, prevent from penetrating oar, ensure that aircraft can be with normal landing.
A kind of centrifugal flapping hinge rotor head of the present utility model, simple in construction, cost is low, effect is preferable, and its redundancy is set
Meter improves flight safety, greatly reduces the generation for penetrating the security incidents such as oar.
A kind of centrifugal flapping hinge rotor head provided by the utility model, pass through middle, flapping hinge, the horizontal stroke being sequentially connected
Axle, lead lag hinge, oar folder, are arranged on the centrifugal flapping hinge rotor head by blade, are rotated by the blade and waved with described
Hinge is in same axial line, the lower section for the axial line that the central shaft of the flapping hinge rotate in the blade so that during blade rotation
A downward power is provided to blade, reduces the angle that blade raises up, increase oar effect, and then increase the stability of aircraft.
So far, although those skilled in the art will appreciate that detailed herein have shown and described of the present utility model show
Example property embodiment, still, still can be according to disclosed in the utility model in the case where not departing from the spirit and scope of the utility model
Content directly determines or derived many other variations or modifications for meeting the utility model principle.Therefore, it is of the present utility model
Scope is understood that and regarded as to cover other all these variations or modifications.
Claims (10)
- A kind of 1. centrifugal flapping hinge rotor head, it is characterised in that including be sequentially connected from inside to outside rotor centers axle, in Connection, flapping hinge, transverse axis, lead lag hinge, oar folder；The flapping hinge and the oar folder between by be arranged on it is described it is middle in described in Transverse axis is connected, and the oar is pressed from both sides for installing blade, and the lead lag hinge is arranged between the oar folder and the blade, the blade Rotation with the flapping hinge in same axial line, the lower section for the axial line that the central shaft of the flapping hinge rotates in the blade.
- 2. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that the flapping hinge central shaft is arranged on The middle lower section.
- 3. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that described middle to be provided with upper limit axle With lower limit axle, the upper limit axle and the lower limit axle sleeve are provided with rubber blanket；It is described it is middle be provided with flapping hinge central shaft, The upper limit axle and the lower limit axle surround the flapping hinge central axis so that the flapping hinge can be transported up and down It is dynamic.
- 4. centrifugal flapping hinge rotor head according to claim 3, it is characterised in that the transverse axis is provided with meshing point, The meshing point is meshed with the flapping hinge central shaft.
- 5. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that middle be provided with is used to prevent The insurance jackscrew that the transverse axis rocks.
- 6. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that described middle to be provided with safety plug Nail, the insurance pin run through the transverse axis in an interference fit.
- 7. centrifugal flapping hinge rotor head according to claim 6, it is characterised in that the insurance pin is provided with and prevented The pin jackscrew that the insurance pin skids off.
- 8. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that the transverse axis is provided with jump ring installation Point, install for preventing the rotor head from penetrating the jump ring of oar.
- 9. centrifugal flapping hinge rotor head according to claim 1, it is characterised in that the lead lag hinge is arranged on the oar Folder corresponds to the groove of the blade, and the lead lag hinge is made of rubber.
- 10. the centrifugal flapping hinge rotor head according to any one of claim 1-9, it is characterised in that described centrifugal Flapping hinge rotor head can be applied to the rotor structure of varying number blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720522507.2U CN207000820U (en) | 2017-05-12 | 2017-05-12 | A kind of centrifugal flapping hinge rotor head |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720522507.2U CN207000820U (en) | 2017-05-12 | 2017-05-12 | A kind of centrifugal flapping hinge rotor head |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207000820U true CN207000820U (en) | 2018-02-13 |
Family
ID=61443297
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720522507.2U Expired - Fee Related CN207000820U (en) | 2017-05-12 | 2017-05-12 | A kind of centrifugal flapping hinge rotor head |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207000820U (en) |
-
2017
- 2017-05-12 CN CN201720522507.2U patent/CN207000820U/en not_active Expired - Fee Related
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107140202A (en) | A kind of centrifugal flapping hinge rotor head | |
| US10933985B2 (en) | Rolling gimbal lock systems for rotorcraft | |
| US10384771B2 (en) | Gimbaled tail rotor hub with spherical elastomeric centrifugal force bearing for blade retention and pitch change articulation | |
| CN105000180B (en) | Aerodynamic configuration of aircraft device | |
| CN204660020U (en) | One is distributed independently controls multi-rotor aerocraft | |
| CN101984331A (en) | Dynamics comprehensive test bed for half-unfolding gas bomb with long tilting rotor wing | |
| US11396374B2 (en) | Aircraft having radially extendable tailboom assembly | |
| CN102673780A (en) | Double-configuration aircraft | |
| US20230415885A1 (en) | Teetering propulsor assembly of an electric vertical takeoff and landing aircraft | |
| CN102887222A (en) | Paddle with changeable torsion-angle distribution | |
| US9415866B2 (en) | Low drag rotor system | |
| CN207000819U (en) | A kind of redundance type flapping hinge rotor head | |
| EP3323720B1 (en) | Proprotor systems for tiltrotor aircraft | |
| CN207000820U (en) | A kind of centrifugal flapping hinge rotor head | |
| CN208007286U (en) | A kind of oil electric mixed dynamic active rotor vertically taking off and landing flyer | |
| CN102923301A (en) | Rotor composite propeller of helicopter | |
| CN216332756U (en) | Distributed electric tail rotor helicopter | |
| CN215323279U (en) | Aircraft | |
| US10589842B2 (en) | Spinners for use on tiltrotor aircraft | |
| CN107089326A (en) | A kind of redundance type flapping hinge rotor head | |
| CN209479973U (en) | A kind of cross flow fan lift-rising autogyro | |
| CN107539480A (en) | A kind of New Ring-like Type rotor | |
| CN205633025U (en) | Power wing helicopter | |
| CN102700709A (en) | Helicopter rotor | |
| KR102506693B1 (en) | Rotary wing assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180213 Termination date: 20180512 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |