CN207257957U - A kind of unmanned plane wing and fuselage quick assembling mechanism - Google Patents
A kind of unmanned plane wing and fuselage quick assembling mechanism Download PDFInfo
- Publication number
- CN207257957U CN207257957U CN201721021322.XU CN201721021322U CN207257957U CN 207257957 U CN207257957 U CN 207257957U CN 201721021322 U CN201721021322 U CN 201721021322U CN 207257957 U CN207257957 U CN 207257957U
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- China
- Prior art keywords
- carbon pipe
- fuselage
- distance
- wing
- coupler body
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Abstract
The utility model belongs to vehicle technology field, propose a kind of unmanned plane wing and fuselage quick assembling mechanism, including fuselage and the wing for being movably arranged on fuselage both sides, concave-board is both provided with two side skeleton of fuselage, main carbon pipe and secondary carbon pipe are provided between wing, two cards are both provided with main carbon pipe and secondary carbon pipe, card is between two concave-boards；The distance between two cards are the distance between two concave-boards on main carbon pipe, and the distance between two cards are the distance between two concave-boards on secondary carbon pipe；Concave-board is double hook shape carbon plate, including preceding coupler body and rear coupler body, and distance is main carbon pipe and secondary carbon pipe distance between preceding coupler body and rear coupler body.Through the above technical solutions, solve the problems, such as that prior art unmanned aerial vehicle body and wing assembling complexity, maintenance cost are high.
Description
Technical field
The utility model belongs to vehicle technology field, is related to a kind of unmanned plane wing and fuselage quick assembling mechanism.
Background technology
As technology develops, unmanned air vehicle technique is more and more obvious in the effect of aviation field particularly military field, for side
Just the carrying of unmanned plane transport, unmanned plane all consider dismantled and assembled in design.At present, wing installation is needed the major-minor in wing
Two carbon pipes, two carbon pipe nested encryptions at the same time and on fuselage, due between the carbon pipe of nesting there are frictional force, to be made to carbon pipe
Into abrasion；In addition, spiral shell is used in the longitudinally opposed position of wing and fuselage generally by being punched at the wing carbon pipe nested with fuselage
Nail nut is fixed, and makes installation process complicated, and after being dismounted for multiple times, the diameter in hole can become larger due to abrasion, need at this time to carbon
Hole on pipe carries out reaming and replaces thicker screw, reduces carbon pipe service life.
Utility model content
The utility model proposes a kind of unmanned plane wing and fuselage quick assembling mechanism, solve prior art unmanned aerial vehicle body and
The problem of wing assembling is complicated, maintenance cost is high.
What the technical solution of the utility model was realized in：
A kind of unmanned plane wing and fuselage quick assembling mechanism, including：
Including fuselage and the wing for being movably arranged on the fuselage both sides, groove is both provided with two side skeleton of the fuselage
Plate, main carbon pipe and secondary carbon pipe are provided between the wing, two cards are both provided with the main carbon pipe and the secondary carbon pipe,
The card is between two concave-boards.
Further, the distance between two described cards are the distance between two described concave-boards on the main carbon pipe,
The distance between two described cards are the distance between two described concave-boards on the pair carbon pipe.
Further, the concave-board is double hook shape carbon plate, including preceding coupler body and rear coupler body, the preceding coupler body and it is described after hook
Distance is the main carbon pipe and the secondary carbon pipe distance between body.
Further, the outside diameter of the main carbon pipe is more than the outside diameter of the secondary carbon pipe.
Further, the preceding coupler body inner arc diameter is identical with the main carbon pipe outside diameter, the rear coupler body inner arc
Diameter is identical with the secondary carbon pipe outside diameter.
Further, the card is circle.
Further, the rear hatchcover being connected with the wing is further included, the rear hatchcover is also connected with front hatch cover, the front deck
Lid front end is provided with fast-assembling buckle, and the front deck cover back-end both sides are provided with the short pin of installation, it is described after hatchcover front end be provided with
It is described that the corresponding pin hole of short pin is installed.
The use principle of the utility model and have the beneficial effect that：
1st, the main carbon pipe of wing and secondary carbon pipe being placed on concave-board, main carbon pipe sleeve is located at before concave-board in coupler body circular arc,
Secondary carbon pipe sleeve is located at after concave-board in coupler body circular arc, and card is stuck on the inside of preceding coupler body and rear coupler body, and is bonded with concave-board.
Such design makes main carbon pipe and secondary carbon pipe are fixed laterally, avoids fuselage and wing connecting staggered.Fuselage and wing connect
Connect two carbon pipes using perforation, and unconventional carbon pipe and carbon pipe nested encryptions, can be conveniently rapid without device to hole during installation
Installation wing, simplify assembling process, save the set-up time, while greatly save carbon pipe usage amount, also reduce aircraft knot
Structure weight；Wing is fixed without punching on carbon pipe, constantly plug positioning pin is reduced to the abrasion at carbon pipe punching, eliminates dimension
Protect cost.
2nd, connected, be conducive in unmanned plane during flying process with secondary carbon two carbon pipes of pipe by main carbon pipe between wing and fuselage
Middle wing more balances, while is conducive to strengthen the reliability connected between wing and fuselage；After the thickness of wing nose is more than
The thickness at end, therefore the outside diameter of main carbon pipe is more than the outside diameter of secondary carbon pipe, such design can meet the needs of reliability and
With cost-effective；The diameter of preceding coupler body inner arc is identical with the outside diameter of main carbon pipe, before being conducive between coupler body and main carbon pipe more
Fitting, while the diameter of rear coupler body inner arc is identical with the outside diameter of secondary carbon pipe, is conducive to more paste between rear coupler body and secondary carbon pipe
Close；Main carbon pipe and secondary carbon pipe cross section are circle, and card design is circle, can meet the needs to wing limit function,
Be conducive to strengthen integrally-built harmony and aesthetics at the same time.
3rd, front deck cover back-end both sides are provided with the short pin of installation, and rear hatchcover front end is provided with pin hole corresponding with installing short pin,
Front hatch cover front end is provided with fast-assembling buckle, will need to only be installed when installing front hatch cover after short pin is inserted into the corresponding pin hole of hatchcover, so
It is buckled afterwards with fast-assembling and is connected front hatch cover with fuselage, it is such to design the installation for facilitating front hatch cover, but also machine can be limited
To displacement before the wing.
Brief description of the drawings
The utility model is described in further detail with reference to the accompanying drawings and detailed description.
Fig. 1 is the utility model assembling structure schematic diagram；
Fig. 2 assembles design sketch for the utility model；
Fig. 3 is wing and front hatch cover assembling schematic diagram in the utility model；
In figure：1- concave-boards, coupler body before 11-, coupler body after 12-, 2- wings, 3- fuselages, the main carbon pipes of 4-, 5- pair carbon pipes, 6-
Hatchcover afterwards, 61- pin holes, 7- front hatch covers, 71- install short pin, 8- cards.
Embodiment
Below in conjunction with the utility model embodiment, the technical scheme in the embodiment of the utility model is carried out clear, complete
Site preparation describes, it is clear that the described embodiments are only a part of the embodiments of the utility model, instead of all the embodiments.
Based on the embodiment in the utility model, what those of ordinary skill in the art were obtained without creative efforts
Every other embodiment, shall fall within the protection scope of the present invention.
As shown in Figure 1-Figure 3, the utility model proposes a kind of unmanned plane wing and fuselage quick assembling mechanism, including：
Including fuselage 3 and the wing 2 for being movably arranged on 3 both sides of fuselage, concave-board 1 is both provided with 3 liang of side skeletons of fuselage,
Main carbon pipe 4 and secondary carbon pipe 5 are provided between wing 2, is both provided with two cards 8 on main carbon pipe 4 and secondary carbon pipe 5, card 8 is located at
Between two concave-boards 1.
The main carbon pipe 4 of wing 2 and secondary carbon pipe 5 are placed on concave-board 1, main carbon pipe 4 is set in coupler body 11 before concave-board 1
In circular arc, secondary carbon pipe 5 is set in after concave-board 1 in 12 circular arc of coupler body, and card 8 is stuck in preceding coupler body 11 and rear coupler body 12 respectively
Side, and be bonded with concave-board 1.Such design makes main carbon pipe 4 and secondary carbon pipe 5 are fixed laterally, avoids fuselage 3 and wing
2 connecting staggereds.Fuselage 3 and wing 2 are connected using the two carbon pipes penetrated through, and unconventional carbon pipe and carbon pipe nested encryptions, peace
Without device to hole during dress, wing 2 conveniently can be rapidly installed, assembling process is simplified, save the set-up time, while save significantly
Carbon pipe usage amount is saved, also reduces aero-structure weight；Wing 2 is fixed without punching on carbon pipe, reduces constantly plug positioning pin
To the abrasion at carbon pipe punching, maintenance cost is eliminated.
Further, the distance between two cards 8 are the distance between two concave-boards 1 on main carbon pipe 4, on secondary carbon pipe 5
The distance between two cards 8 are the distance between two concave-boards 1.
Further, concave-board 1 is double hook shape carbon plate, including preceding coupler body 11 and rear coupler body 12, preceding coupler body 11 and rear coupler body 12
Between distance be main carbon pipe 4 and secondary 5 distance of carbon pipe.
Further, the outside diameter of main carbon pipe 4 is more than the outside diameter of secondary carbon pipe 5.
Further, preceding 11 inner arc diameter of coupler body is identical with main 4 outside diameter of carbon pipe, rear 12 inner arc diameter of coupler body and pair
5 outside diameter of carbon pipe is identical.
Further, card 8 is circle.
Connected, be conducive in unmanned plane during flying mistake with secondary carbon 5 two carbon pipes of pipe by main carbon pipe 4 between wing 2 and fuselage 3
Wing 2 more balances in journey, while is conducive to strengthen the reliability connected between wing 2 and fuselage 3；The thickness of 2 front end of wing
More than the thickness of rear end, therefore the outside diameter of main carbon pipe 4 is more than the outside diameter of secondary carbon pipe 5, and such design can meet reliability
Demand, and can be cost-effective；The diameter of preceding 11 inner arc of coupler body is identical with the outside diameter of main carbon pipe 4, coupler body 11 before being conducive to
More it is bonded between main carbon pipe 4, while the diameter of 12 inner arc of rear coupler body is identical with the outside diameter of secondary carbon pipe 5, is conducive to rear hook
More it is bonded between body 12 and secondary carbon pipe 5；Main carbon pipe 4 and secondary 5 cross section of carbon pipe are circle, and card 8 is designed as circle, Ji Nengman
The sufficient needs to 2 limit function of wing, while be conducive to strengthen integrally-built harmony and aesthetics.
Further, the rear hatchcover 6 being connected with wing 2 is further included, rear hatchcover 6 is also connected with front hatch cover 7,7 front end of front hatch cover
Fast-assembling buckle is provided with, 7 rear end both sides of front hatch cover are provided with the short pin 71 of installation, and rear 6 front end of hatchcover is provided with installing short pin 71
Corresponding pin hole 61.
7 rear end both sides of front hatch cover are provided with the short pin 71 of installation, and rear 6 front end of hatchcover is provided with corresponding with installing short pin 71
Pin hole 61,7 front end of front hatch cover are provided with fast-assembling buckle, and need to will only install hatchcover 6 after short pin 71 is inserted into when installing front hatch cover 7 corresponds to
Pin hole 61 in, be then buckled with fast-assembling and be connected front hatch cover 7 with fuselage 3, such design facilitates the installation of front hatch cover 7,
But also it can limit before wing 2 to displacement.
The above is only the preferred embodiments of the present utility model only, is not intended to limit the utility model, all in this practicality
Within new spirit and principle, any modification, equivalent replacement, improvement and so on, should be included in the guarantor of the utility model
Within the scope of shield.
Claims (7)
1. a kind of unmanned plane wing and fuselage quick assembling mechanism, it is characterised in that：Including fuselage (3) and it is movably arranged on the fuselage
(3) wing (2) of both sides, is both provided with concave-board (1) on (3) two side skeleton of fuselage, is provided between the wing (2)
Two cards (8), the card are both provided with main carbon pipe (4) and secondary carbon pipe (5), the main carbon pipe (4) and the secondary carbon pipe (5)
Piece (8) is between two concave-boards (1).
2. a kind of unmanned plane wing according to claim 1 and fuselage quick assembling mechanism, it is characterised in that：The main carbon pipe
(4) the distance between upper two described cards (8) are the distance between two described concave-boards (1), two on the pair carbon pipe (5)
The distance between a described card (8) is the distance between two described concave-boards (1).
3. a kind of unmanned plane wing according to claim 1 and fuselage quick assembling mechanism, it is characterised in that：The concave-board
(1) it is double hook shape carbon plate, including preceding coupler body (11) and rear coupler body (12), between the preceding coupler body (11) and the rear coupler body (12)
Distance is the main carbon pipe (4) and described secondary carbon pipe (5) distance.
4. a kind of unmanned plane wing according to claim 1 and fuselage quick assembling mechanism, it is characterised in that：The main carbon pipe
(4) outside diameter is more than the outside diameter of the secondary carbon pipe (5).
5. a kind of unmanned plane wing according to claim 3 and fuselage quick assembling mechanism, it is characterised in that：The preceding coupler body
(11) inner arc diameter is identical with main carbon pipe (4) outside diameter, rear coupler body (12) the inner arc diameter and the secondary carbon
It is identical to manage (5) outside diameter.
6. a kind of unmanned plane wing according to claim 1 and fuselage quick assembling mechanism, it is characterised in that：The card (8)
For circle.
7. a kind of unmanned plane wing according to claim 1 and fuselage quick assembling mechanism, it is characterised in that：Further include with it is described
The rear hatchcover (6) of wing (2) connection, the rear hatchcover (6) are also connected with front hatch cover (7), and front hatch cover (7) front end is provided with
Fast-assembling is buckled, and front hatch cover (7) the rear end both sides are provided with the short pin (71) of installation, and described rear hatchcover (6) front end is provided with and institute
State the corresponding pin hole (61) of the short pin (71) of installation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721021322.XU CN207257957U (en) | 2017-08-15 | 2017-08-15 | A kind of unmanned plane wing and fuselage quick assembling mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721021322.XU CN207257957U (en) | 2017-08-15 | 2017-08-15 | A kind of unmanned plane wing and fuselage quick assembling mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207257957U true CN207257957U (en) | 2018-04-20 |
Family
ID=61925012
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721021322.XU Expired - Fee Related CN207257957U (en) | 2017-08-15 | 2017-08-15 | A kind of unmanned plane wing and fuselage quick assembling mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207257957U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
-
2017
- 2017-08-15 CN CN201721021322.XU patent/CN207257957U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109927878A (en) * | 2019-04-25 | 2019-06-25 | 西安航空学院 | Diamond wing mounting structure and aircraft with the mounting structure |
| CN109927878B (en) * | 2019-04-25 | 2024-02-02 | 西安航空学院 | Diamond wing mounting structure and aircraft with same |
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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: 20180420 Termination date: 20190815 |