CN207658033U - A kind of unmanned plane wing and winglet connection structure - Google Patents
A kind of unmanned plane wing and winglet connection structure Download PDFInfo
- Publication number
- CN207658033U CN207658033U CN201721812242.6U CN201721812242U CN207658033U CN 207658033 U CN207658033 U CN 207658033U CN 201721812242 U CN201721812242 U CN 201721812242U CN 207658033 U CN207658033 U CN 207658033U
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- winglet
- face
- anticreep
- unmanned plane
- bindiny mechanism
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Abstract
A kind of structure that unmanned plane wing is connected with winglet, including wing end face, winglet end face, anticreep bindiny mechanism；The anticreep bindiny mechanism is pasted onto at edge in face of wingtip 45%, and is connected through a screw thread and the anti-loosing screw in anticreep bindiny mechanism is fixed at winglet end face 45%.The connection structure light weight is small easy to install, and the length of the stretching end face of anti-loosing screw is adjustable, and threaded rod protrudes the exposed small of aerofoil surface after assembling, and reduces wing drag.There is certain self-locking function effect of the U-shaped sliding block of spring failure due to gravity.
Description
Technical field
The present invention relates to the technical field of structures of unmanned plane, and in particular to a kind of unmanned plane wing connects knot with winglet
Structure.
Background technology
Currently, the purposes of unmanned plane is very extensive and cost is relatively low, survival ability is strong, and mobility is good, easy to use, existing
For there is extremely important effect in war, or even also gathers around and hold out broad prospects in civil field.In use, most of nothings
Man-machine wing and winglet does not have anticreep bindiny mechanism or certain bindiny mechanisms Joint failure in high-frequency vibration in the air,
Winglet is detached from wing, and winglet, which falls off, can induce other aerodynamics problems, causes unmanned plane resistance to increase, it is difficult to control
System, then causes unmanned plane out of control or the thing of air crash happens occasionally, and causes the loss being not necessarily to.
Utility model content
Technical problem to be solved in the utility model is to overcome existing defect, provides a kind of unmanned plane wing and wing tip
Winglet connection structure, its technical solution is as follows：
A kind of structure that unmanned plane wing is connected with winglet, including wing end face, winglet end face, anticreep connection
Mechanism；It is characterized in that：The anticreep bindiny mechanism is pasted onto at edge in face of wingtip 45%, and being connected through a screw thread will be anti-
Anti-loosing screw in de- bindiny mechanism is fixed at winglet end face 45%.
Preferably：The anticreep bindiny mechanism is pasted onto by using AB glue at edge in face of wingtip 45%.
Preferably：Exterior skin is done in the wing end face by compound carbon fibre material, when winglet end face spreads carbon fiber
Pre-buried a diameter of 12mm, thickness are 6061 Al alloy blocks of 3mm.
Preferably：6061 Al alloy block is pasted onto apart from 45% winglet end face of leading edge with epoxide-resin glue with full
Sufficient bonding strength and requirement.
Preferably：Anticreep bindiny mechanism includes threaded rod, soket head cap screw, front apron, anti-loosing screw, U-shaped sliding block, anticreep
Pedestal, spring；U-shaped sliding block acts on preventing the transverse direction of winglet sliding by the elastic force of spring in anticreep pedestal inner orbit
It is de-；The threaded rod, soket head cap screw are arranged on front apron；The front apron is connected with anticreep pedestal by soket head cap screw
It connects.
Advantageous effect：Light weight is small easy to install, and the length of the stretching end face of anti-loosing screw is adjustable, and threaded rod is being pacified
Prominent aerofoil surface is exposed small after assembling, and reduces wing drag.Even if the U-shaped sliding block of spring failure is due to gravity
Effect also have certain self-locking function.
Description of the drawings
Fig. 1 is the utility model general assembly 3 d effect graph.
Fig. 2 is the utility model component identification figure one.
Fig. 3 is the utility model component identification figure two.
Fig. 4 is the total dimensions chart of the utility model.
Fig. 5 is the U-shaped sliding block of the utility model and threaded rod figure.
Fig. 6 is the utility model anticreep pedestal figure.
Wherein：1-winglet end face, 2-wing end faces, 3-winglet carbon fiber pipes, 4-wing carbon fiber pipes,
5-Φ, 2.5 long L1The threaded rod of (being determined according to specific wing thickness), 6-soket head cap screw M2x6,7-front aprons, 8-anticreep spiral shells
It follows closely (soket head cap screw M3x20), 9-U-shaped sliding blocks, 10-anticreep pedestals, 11-springs, the Al alloy block of 12-Φ 12x3.
Specific implementation mode
Shown in attached drawing 1-6.
A kind of structure that unmanned plane wing is connected with winglet, including wing end face, winglet end face, anticreep connection
Mechanism；It is characterized in that：The anticreep bindiny mechanism is pasted onto at edge in face of wingtip 45%, and being connected through a screw thread will be anti-
Anti-loosing screw in de- bindiny mechanism is fixed at winglet end face 45%.
Anticreep bindiny mechanism component includes threaded rod, soket head cap screw, front apron, anti-loosing screw (soket head cap screw
M3x20), the Al alloy block of U-shaped sliding block, anticreep pedestal, spring, Φ 12x3mm, U-shaped sliding block rely on bullet in anticreep pedestal Nei Daoli
The elastic force of spring acts on to be slipped to lock the lateral of winglet.It is centrally disposed in the Al alloy block that winglet end face is laid with
M3 screw threads are simultaneously attacked in 2.7 holes a diameter of Φ；And wing end face can directly use AB glue or first by anticreep with anticreep pedestal (main body) component
Pedestal is sticked on laminate with AB glue and then laminate and anticreep pedestal is sticked to together in 45% wing endface position of leading edge.
In a diameter of Φ of 6061 Al alloy block centre drills apart from 45% endface of winglet leading edge, that is, Φ 12x3mm 2.7
M3 screw threads are simultaneously attacked to configure the anti-loosing screw in anticreep bindiny mechanism in hole；Anticreep pedestal is sticked on aviation laminate so using AB glue
Aviation laminate and anticreep pedestal are pasted onto together in 45% wing endface position of leading edge afterwards.After completing assembly installation,
Upper surface of the airfoil exposed small button need to be only lifted when use, after so that winglet end face is closed with wingtip face paste, unclamp small press
Button then locks wing and winglet by built-in spring automatic reset；The operating method that is connect with winglet of dismounting wing and
It is the same when installation installation step, it repeats no more.
When in use, winglet carbon fiber pipe 3 is inserted into wing carbon fiber pipe 4, makes winglet end face and wing
End face is bonded, only need to be by the 2.5 long L of Φ on front apron 71Threaded rod 5 upwards lift, make anti-loosing screw 8 from U-shaped sliding block 9
It is passed through in big hole, waits for that both ends of the surface are bonded, relieving of loosing one's grip, the threaded rod 5 is under the elastic force effect of spring, 2.5 long L of Φ1's
Threaded rod 5 resets at once, and at this moment U-shaped sliding block 9 has lockked anti-loosing screw 8, that is, completes docking for winglet and wing.
The advantages of anticreep bindiny mechanism is that light weight is small easy to install, and the length of the stretching end face of anti-loosing screw 8 can
It adjusts, 2.5 long L of Φ1Threaded rod 5 after assembling prominent aerofoil surface it is exposed small, reduce wing drag.I.e.
The U-shaped sliding block 9 of spring failure is set also to have certain self-locking function due to the effect of gravity.
Many details are elaborated in the above description in order to fully understand the utility model.But above description
Only it is the preferred embodiment of the utility model, the utility model can be much to come different from other manner described here
Implement, therefore the utility model is not limited by specific implementation disclosed above.Any those skilled in the art exist simultaneously
It does not depart under technical solutions of the utility model ambit, it is all new to this practicality using the methods and technical content of the disclosure above
Type technical solution makes many possible changes and modifications, or is revised as the equivalent embodiment of equivalent variations.It is every without departing from this
The content of utility model technical solution any is simply repaiied according to the technical essence of the utility model is made to the above embodiment
Change, equivalent variations and modification, in the range of still falling within technical solutions of the utility model protection.
Claims (5)
1. a kind of structure that unmanned plane wing is connected with winglet, including wing end face, winglet end face, anticreep connect machine
Structure；It is characterized in that：The anticreep bindiny mechanism is pasted onto at edge in face of wingtip 45%, and is connected through a screw thread anticreep
Anti-loosing screw in bindiny mechanism is fixed at winglet end face 45%.
2. the structure that a kind of unmanned plane wing according to claim 1 is connected with winglet, it is characterized in that：The anticreep
Bindiny mechanism includes threaded rod, soket head cap screw, front apron, anti-loosing screw, U-shaped sliding block, anticreep pedestal, spring；The U-shaped cunning
Block is arranged in anticreep pedestal inner orbit, and is acted on by the elastic force of spring to prevent the lateral of winglet from slipping；The spiral shell
Rasp bar, soket head cap screw are arranged on front apron；The front apron is connect with anticreep pedestal by soket head cap screw.
3. the structure that a kind of unmanned plane wing according to claim 1 is connected with winglet, it is characterized in that：The anticreep
Bindiny mechanism is pasted onto by using AB glue at edge in face of wingtip 45%.
4. the structure that a kind of unmanned plane wing according to claim 1 is connected with winglet, it is characterized in that：The wing
Exterior skin is done in end face by compound carbon fibre material, pre-buried a diameter of 12mm, thickness 3mm when winglet end face spreads carbon fiber
6061 Al alloy blocks.
5. the structure that a kind of unmanned plane wing according to claim 4 is connected with winglet, it is characterized in that：Described 6061
Al alloy block is pasted onto apart from 45% winglet end face of leading edge with epoxide-resin glue to meet bonding strength and requirement.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721812242.6U CN207658033U (en) | 2017-12-22 | 2017-12-22 | A kind of unmanned plane wing and winglet connection structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721812242.6U CN207658033U (en) | 2017-12-22 | 2017-12-22 | A kind of unmanned plane wing and winglet connection structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207658033U true CN207658033U (en) | 2018-07-27 |
Family
ID=62943077
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721812242.6U Active CN207658033U (en) | 2017-12-22 | 2017-12-22 | A kind of unmanned plane wing and winglet connection structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207658033U (en) |
-
2017
- 2017-12-22 CN CN201721812242.6U patent/CN207658033U/en active Active
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