CN205203359U - Device for connecting wing and fuselage can loosen automatically and take off - Google Patents
Device for connecting wing and fuselage can loosen automatically and take off Download PDFInfo
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- CN205203359U CN205203359U CN201520921790.7U CN201520921790U CN205203359U CN 205203359 U CN205203359 U CN 205203359U CN 201520921790 U CN201520921790 U CN 201520921790U CN 205203359 U CN205203359 U CN 205203359U
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- horizontal surface
- wing
- fuselage
- tie bolt
- hanging point
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Abstract
The utility model relates to an unmanned air vehicle technique field provides a device for connecting wing and fuselage can loosen automatically and take off, include: around hang the point and deformable around connecting bolt, when unmanned aerial vehicle normal flight, through the flexible bolt with the wing fix hang the point around the fuselage on, when unmanned aerial vehicle's wing or fuselage met the barrier check and go forward, the flexible bolt was because the deformation of self breaks away from corresponding string point respectively for wing and fuselage slide and drop, thereby have realized the protection to wing and fuselage, accomplish the undamaged recovery of fuselage and wing.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly a kind of wing and the fuselage connecting device that can automatically get loose.
Background technology
At present, domestic unmanned plane wing and fuselage are all adopt attachment substantially, and this connection mode is applicable to launching or rolling start, hit net or the sliding unmanned plane running landing.And for hand-thrown take off mode, wipe land landing unmanned plane, if wing and fuselage still adopt attachment, then landing or when running into obstacle, collision can cause wing and fuselage and inner structure thereof to sustain damage.
Based on this, prior art needs to be improved really.
Utility model content
The technical matters that the utility model need solve is to provide a kind of device that fuselage and wing are got loose, unmanned plane is wiped when landing or encounter obstacle, fuselage and wing can be thrown off, and realize the harmless recovery of fuselage wing.
In order to solve the problem, the utility model provides the connecting device that a kind of wing and fuselage can get loose automatically, and its technical scheme adopted is as follows:
Described device comprises: front hanging point, rear hanging point, front tie bolt and rear tie bolt;
Described front hanging point comprises the first negative camber, extends the first horizontal surface and the second horizontal surface in a lateral direction at described first negative camber;
Described second horizontal surface lower than the first horizontal surface, and and distance between the first horizontal surface be greater than the height of nut in front tie bolt;
The other end of described second horizontal surface, direction perpendicular to the second horizontal surface are connected with bearing surface, and the other end of described bearing surface is extended with the 3rd horizontal surface along on the direction of the first horizontal surface;
Described first horizontal surface and the 3rd horizontal surface form chute, and the width of described chute equals the diameter of screw in front tie bolt;
Described second horizontal surface offers through hole in vertical direction, and the diameter of described through hole is greater than the external diameter of nut in front tie bolt;
Described rear hanging point comprises the second negative camber, extends the 4th horizontal surface in a lateral direction at described second negative camber, and be provided with semicircle groove at the midway location of described 4th horizontal surface, the diameter of described semicircle groove equals the diameter of screw in rear tie bolt;
The horizontal surface width being positioned at semicircle groove front end in described 4th horizontal surface is less than the horizontal surface width being positioned at semicircle groove rear end;
Described first negative camber and the second negative camber to be fixed on fuselage through countersunk-heat bolt respectively and to fit completely with fuselage curved surface;
Described front tie bolt and rear tie bolt are all positioned at immediately below wing, and when wing is connected with fuselage, front tie bolt is positioned at chute, and rear tie bolt is positioned at semicircle groove; Described front tie bolt and rear tie bolt are deformable bolt.
Preferably, described front tie bolt and rear tie bolt are nylon bolt.
Preferably, described front hanging point and rear hanging point all adopt D printing nylon material to make.
Preferably, the front end of described chute is fillet, and the front end of described 4th horizontal surface is fillet.
Preferably, the junction of described bearing surface and the second horizontal surface, the 3rd horizontal surface is fillet.
Preferably, the lower surface and the first negative camber of described second horizontal surface are fixed with reinforcement; Reinforcement is fixed with between the second negative camber and the 4th horizontal surface.
Preferably, the length of described first horizontal surface is less than the length of the second horizontal surface;
Accordingly, described bearing surface is trapezium structure, and it goes to the bottom identical with the length of the second horizontal surface, and upper base is identical with the length of the first horizontal surface.
Preferably, described front hanging point extends the first horizontal surface along the upper limb of the first negative camber; Described rear hanging point extends the 4th horizontal surface along the upper limb of the second negative camber.
The beneficial effects of the utility model are:
A kind of wing that the utility model provides and the connecting device that fuselage can get loose automatically; when unmanned plane normal flight; by deformable bolt, wing is fixed on the hanging point of fuselage; when the wing of unmanned plane or fuselage run into obstacle halt suddenly time; deformable bolt departs from corresponding hanging point respectively due to the deformation of self; wing and sliding machine body are come off, thus achieves the protection to wing and fuselage, complete the harmless recovery of fuselage and wing.
Accompanying drawing explanation
Fig. 1, Fig. 2 are the front hanging point integral structure schematic diagram of the utility model one embodiment;
Fig. 3 is the front hanging point lateral plan of the utility model one embodiment;
Fig. 4 is the front hanging point upward view of the utility model one embodiment;
Fig. 5, Fig. 6 are the rear hanging point integral structure schematic diagram of the utility model one embodiment;
Fig. 7 is the front and back tie bolt structural representation of the utility model one embodiment;
Fig. 8 is the Wing-Body Configurations connection procedure schematic diagram of the utility model one embodiment;
Fig. 9 is the structural representation after the Wing-Body Configurations of the utility model one embodiment connects.
Detailed description of the invention
Below in conjunction with drawings and Examples, detailed description of the invention of the present utility model is described in further detail.
As shown in Figure 8,9, the utility model provides the connecting device that a kind of wing and fuselage can get loose automatically, and described device comprises: front hanging point 1, rear hanging point 2, front tie bolt 3 and rear tie bolt 4;
As shown in Figure 1 and Figure 2, described front hanging point 1 comprises the first negative camber 11, extends the first horizontal surface 12 and the second horizontal surface 13 in a lateral direction at described first negative camber 11;
Described second horizontal surface 13 lower than the first horizontal surface 12, and and distance between the first horizontal surface 12 be greater than the height of nut in front tie bolt 3;
The other end of described second horizontal surface 13, direction perpendicular to the second horizontal surface 13 are connected with bearing surface 14, and the other end of described bearing surface 14 is extended with the 3rd horizontal surface 15 along on the direction of the first horizontal surface 12;
As shown in Figure 3, described first horizontal surface 12 and the 3rd horizontal surface 15 form chute 16, and the width of described chute 16 equals the diameter of screw in front tie bolt 3;
As shown in Figure 4, described second horizontal surface 13 offers through hole 17 in vertical direction, and the diameter of described through hole 17 is greater than the external diameter of nut in front tie bolt 3;
As shown in Figure 5,6, described rear hanging point 2 comprises the second negative camber 21, the 4th horizontal surface 22 is extended in a lateral direction at described second negative camber 21, be provided with semicircle groove 23 at the midway location of described 4th horizontal surface 22, the diameter of described semicircle groove 23 equals the diameter of screw in rear tie bolt 4;
The horizontal surface width being positioned at semicircle groove 23 front end in described 4th horizontal surface 22 is less than the horizontal surface width being positioned at semicircle groove 23 rear end;
Described first negative camber 11 and the second negative camber 12 to be fixed on fuselage through countersunk-heat bolt respectively and to fit completely with fuselage curved surface;
As shown in Figure 8, described front tie bolt 3 and rear tie bolt 4 are all positioned at immediately below wing, and when wing is connected with fuselage, front tie bolt 3 is positioned at chute 16, and rear tie bolt 4 is positioned at semicircle groove 23, as shown in Figure 9; Described front tie bolt 3 and rear tie bolt 4 are deformable bolt.
Preferably, the front end of described chute 16 is fillet, and the front end of described 4th horizontal surface 22 is fillet, to guide front tie bolt 3 and rear tie bolt 4 slips into.
In use, first the screw of tie bolt 3 and rear tie bolt 4 before the below of left and right wing is all fixed with, and make front tie bolt 3 and rear tie bolt 4 far away as far as possible, again one group of front hanging point 1 and rear hanging point 2 are fixed on the side of fuselage through countersunk-heat bolt, another front hanging point 1 of group and rear hanging point 2 are fixed on the opposite side of fuselage through countersunk-heat bolt; The position of front hanging point 1 and rear hanging point 2 will adapt with the position of front tie bolt 3 and rear tie bolt 4;
As shown in Figure 8, wing is put into fuselage and has aerofoil profile front end, toward pusher wing until after on wing two tie bolt 4 snap on the semicircle groove 23 of hanging point 2 after on fuselage, now, two front tie bolts 3 will put under in corresponding chute 16, as shown in Figure 9, and tie bolt 4 after locking, lock front tie bolt 3 through through hole 17, wing and fuselage connection complete.
After unmanned plane during flying state relies on, the semicircle groove 23 of hanging point 2 limits the front and back position of wing, rely on the 4th horizontal surface 22 of the first horizontal surface 12 of front hanging point 1, the 3rd horizontal surface 15 and rear hanging point 2 to limit unmanned plane upwards to throw off, fuselage restriction wing to upper/lower positions, so wing is very firmly safe and reliable in state of flight.
Unmanned plane when landing with wiping, and fuselage and wing have two kinds of disengaging modes:
1) halt suddenly if fuselage runs into obstacle, go forward tie bolt 3 and rear tie bolt 4 of wing can depart from front hanging point 1 and rear hanging point 2 respectively due to the elastic deformation of self, and wing forward slip is come off, and ensures fuselage and wing is harmless departs from;
2) halt suddenly if wing runs into obstacle, go forward tie bolt 3 and rear tie bolt 4 of wing can depart from front hanging point 1 and rear hanging point 2 respectively due to the elastic deformation of self, wing is slided backward and comes off, and ensures fuselage and wing is harmless departs from.
In the utility model, described front tie bolt 3 and rear tie bolt 4 can be PC bolt, nylon bolt etc.; Be preferably nylon bolt, compared to other material bolts, nylon bolt can adopt existing on the market, need not customize, thus reduce preparation cost.
Preferably, described front hanging point 1 and rear hanging point 2 all adopt 3D to print nylon material and make, and nylon material has deformable feature, to ensure that bolt can get loose from hanging point, and adopt 3D printout, can reduce costs further.
In order to prevent stress from concentrating, the junction of described bearing surface 14 and the second horizontal surface 13, the 3rd horizontal surface 15 is fillet, thus service life of hanging point 1 before extending.
Preferably, the lower surface and the first negative camber 11 of described second horizontal surface 13 are fixed with reinforcement; Reinforcement is fixed with between the second negative camber 21 and the 4th horizontal surface 22.
Because unmanned plane requires that weight is light as far as possible, therefore, under the prerequisite meeting structural strength, the weight of hanging point before and after reducing as much as possible, as: as described in arranging, the length of the first horizontal surface 12 is less than the length of the second horizontal surface 13; Accordingly, described bearing surface 14 is trapezium structure, and it goes to the bottom identical with the length of the second horizontal surface 13, and upper base is identical with the length of the first horizontal surface 12.
And described front hanging point 1 extends the first horizontal surface 12 along the upper limb of the first negative camber 11; Described rear hanging point 2 extends the 4th horizontal surface 22 along the upper limb of the second negative camber 21.
A kind of wing that the utility model provides and the connecting device that fuselage can get loose automatically; when unmanned plane normal flight; by deformable bolt, wing is fixed on the hanging point of fuselage; when the wing of unmanned plane or fuselage run into obstacle halt suddenly time; deformable bolt departs from corresponding hanging point respectively due to the deformation of self; wing and sliding machine body are come off, thus achieves the protection to wing and fuselage, complete the harmless recovery of fuselage and wing.
Above embodiment is only for illustration of the utility model; and be not limitation of the utility model; the those of ordinary skill of relevant technical field; when not departing from spirit and scope of the present utility model; can also make a variety of changes and modification; therefore all equivalent technical schemes also belong to category of the present utility model, and scope of patent protection of the present utility model should be defined by the claims.
Claims (8)
1. wing and the fuselage connecting device that can automatically get loose, it is characterized in that, described device comprises: front hanging point (1), rear hanging point (2), front tie bolt (3) and rear tie bolt (4);
Described front hanging point (1) comprises the first negative camber (11), extends the first horizontal surface (12) and the second horizontal surface (13) in a lateral direction described first negative camber (11);
Described second horizontal surface (13) lower than the first horizontal surface (12), and and distance between the first horizontal surface (12) be greater than the height of nut in front tie bolt (3);
The other end of described second horizontal surface (13), direction perpendicular to the second horizontal surface (13) are connected with bearing surface (14), and the other end of described bearing surface (14) is along the direction of the first horizontal surface (12) being extended with the 3rd horizontal surface (15);
Described first horizontal surface (12) and the 3rd horizontal surface (15) form chute (16), and the width of described chute (16) equals the diameter of screw in front tie bolt (3);
Described second horizontal surface (13) offers through hole (17) in vertical direction, and the diameter of described through hole (17) is greater than the external diameter of nut in front tie bolt (3);
Described rear hanging point (2) comprises the second negative camber (21), the 4th horizontal surface (22) is extended in a lateral direction described second negative camber (21), be provided with semicircle groove (23) at the midway location of described 4th horizontal surface (22), the diameter of described semicircle groove (23) equals the diameter of screw in rear tie bolt (4);
The horizontal surface width being positioned at semicircle groove (23) front end in described 4th horizontal surface (22) is less than the horizontal surface width being positioned at semicircle groove (23) rear end;
Described first negative camber (11) and the second negative camber to be fixed on fuselage through countersunk-heat bolt respectively and to fit completely with fuselage curved surface;
Described front tie bolt (3) and rear tie bolt (4) are all positioned at immediately below wing, and when wing is connected with fuselage, front tie bolt (3) is positioned at chute (16), and rear tie bolt (4) is positioned at semicircle groove (23); Described front tie bolt (3) and rear tie bolt (4) are deformable bolt.
2. wing as claimed in claim 1 and the fuselage connecting device that can automatically get loose, it is characterized in that, described front tie bolt (3) and rear tie bolt (4) are nylon bolt.
3. wing as claimed in claim 2 and the fuselage connecting device that can automatically get loose, it is characterized in that, described front hanging point (1) and rear hanging point (2) all adopt 3D printing nylon material to make.
4. wing as claimed in claim 1 and the fuselage connecting device that can automatically get loose, it is characterized in that, the front end of described chute (16) is fillet, and the front end of described 4th horizontal surface (22) is fillet.
5. wing as claimed in claim 1 and the fuselage connecting device that can automatically get loose, it is characterized in that, described bearing surface (14) is fillet with the junction of the second horizontal surface (13), the 3rd horizontal surface (15).
6. wing as claimed in claim 1 and the fuselage connecting device that can automatically get loose, is characterized in that, the lower surface and the first negative camber (11) of described second horizontal surface (13) are fixed with reinforcement; Reinforcement is fixed with between the second negative camber (21) and the 4th horizontal surface (22).
7. wing as claimed in claim 1 and the fuselage connecting device that can automatically get loose, it is characterized in that, the length of described first horizontal surface (12) is less than the length of the second horizontal surface (13);
Accordingly, described bearing surface (14) is trapezium structure, and it goes to the bottom identical with the length of the second horizontal surface (13), and upper base is identical with the length of the first horizontal surface (12).
8. the connecting device that the wing as described in any one of claim 1-7 and fuselage can get loose automatically, is characterized in that, described front hanging point (1) extends the first horizontal surface (12) along the upper limb of the first negative camber (11);
Described rear hanging point (2) extends the 4th horizontal surface (22) along the upper limb of the second negative camber (21).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520921790.7U CN205203359U (en) | 2015-11-13 | 2015-11-13 | Device for connecting wing and fuselage can loosen automatically and take off |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520921790.7U CN205203359U (en) | 2015-11-13 | 2015-11-13 | Device for connecting wing and fuselage can loosen automatically and take off |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205203359U true CN205203359U (en) | 2016-05-04 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520921790.7U Active CN205203359U (en) | 2015-11-13 | 2015-11-13 | Device for connecting wing and fuselage can loosen automatically and take off |
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| Country | Link |
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| CN (1) | CN205203359U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741834A (en) * | 2016-11-30 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Hanging point attachment means are carried at a kind of thin wing |
| CN107963201A (en) * | 2017-11-24 | 2018-04-27 | 北京卫星制造厂 | A kind of winglet attachment device of fast demountable |
| CN109398751A (en) * | 2016-12-06 | 2019-03-01 | 昆山鲲鹏无人机科技有限公司 | The detection method whether the tilting wing unmanned plane wing with a kind of aerodynamic arrangement and inclining rotary mechanism loosens |
-
2015
- 2015-11-13 CN CN201520921790.7U patent/CN205203359U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741834A (en) * | 2016-11-30 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Hanging point attachment means are carried at a kind of thin wing |
| CN106741834B (en) * | 2016-11-30 | 2018-12-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Hanging point attachment device is carried at a kind of thin wing |
| CN109398751A (en) * | 2016-12-06 | 2019-03-01 | 昆山鲲鹏无人机科技有限公司 | The detection method whether the tilting wing unmanned plane wing with a kind of aerodynamic arrangement and inclining rotary mechanism loosens |
| CN109398751B (en) * | 2016-12-06 | 2023-07-04 | 昆山鲲鹏无人机科技有限公司 | Method for detecting whether unmanned aerial vehicle wing with tilting mechanism loosens or not |
| CN107963201A (en) * | 2017-11-24 | 2018-04-27 | 北京卫星制造厂 | A kind of winglet attachment device of fast demountable |
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| GR01 | Patent grant |