CN213335811U - Flexible folding wing at tail of pipeline launching projectile body - Google Patents
Flexible folding wing at tail of pipeline launching projectile body Download PDFInfo
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- CN213335811U CN213335811U CN202021488778.9U CN202021488778U CN213335811U CN 213335811 U CN213335811 U CN 213335811U CN 202021488778 U CN202021488778 U CN 202021488778U CN 213335811 U CN213335811 U CN 213335811U
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- base block
- projectile body
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- tail
- flexible
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Abstract
The utility model relates to a pipeline launch projectile body technical field just discloses a flexible folding wing of pipeline launch projectile body afterbody, including the projectile body, a plurality of bar grooves have been seted up on the projectile body surface, and are a plurality of bar groove department all is equipped with first base block and second base block, first base block and second base block are located bar groove both sides respectively, first base block and second base block all with projectile body fixed connection, be equipped with fin mechanism between second base block and the first base block, be provided with the screw hole on the first base block, threaded hole is provided with stop gear. This flexible folding wing of pipeline launching projectile body afterbody has realized the folding and the expansion of flexible wing through the torsional spring, has solved the problem that occupies too much installation space, launching tube way space and projectile body space that fixed wing and roll up the arc wing and exist, has bigger wing expansion area simultaneously, can carry on spacingly to the fin bracing piece through limit structure, has guaranteed flight in-process airfoil stability, has better pneumatic performance.
Description
Technical Field
The utility model relates to a pipeline launch projectile body technical field specifically is a flexible folding wing of pipeline launch projectile body afterbody.
Background
At present, the tail wings of the pipeline launching type missile are divided into a fixed wing and a curling wing, the fixed wing needs to be provided with a longer tail wing rod, the distance between a tail connecting rod of the missile body and a wing surface needs to be longer to ensure the aerodynamic performance of the missile body such as flight stability and the like, and a larger installation space needs to be occupied, so that the length of a gun barrel is increased, and the aerodynamic performance is poorer; and roll up arc folding wing and need great installation space, can occupy great projectile body space, and can lead to the projectile body rotatory among the flight process, and a lot of projectile body rotations are unfavorable for stable flight.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model provides a pipeline launch projectile afterbody flexible folding wing possesses sparingly space, possess bigger wing expansion area simultaneously, possess advantages such as good pneumatic performance, solved the stationary vane and rolled up the problem of the defect that two kinds of wing types of arc wing exist.
(II) technical scheme
In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a flexible folding wing of pipeline launch projectile body afterbody, includes the projectile body, a plurality of bar grooves have been seted up on the projectile body surface, and is a plurality of bar groove department all is equipped with first base block and second base block, first base block and second base block are located bar groove both sides respectively, first base block and second base block all with projectile body fixed connection, be equipped with fin mechanism between second base block and the first base block, be provided with the screw hole on the first base block, threaded hole is provided with stop gear, second base block is close to first base block one side and sets up flutedly.
Preferably, fin mechanism includes the fin bracing piece, fin bracing piece one end is located between first base block and the second base block, fin bracing piece bottom edge fixedly connected with flexile fin, the pivot of two symmetric distributions of fin bracing piece one end fixedly connected with, first base block and second base block are run through respectively in two pivots, two pivots respectively with first base block and second base block swing joint, the fin bracing piece is close to first base block one side and has seted up the spacing groove, the fin bracing piece is close to second base block one side and is equipped with fixed cover and torsional spring, fixed cover and fin bracing piece fixed connection, the torsional spring is located inside the recess.
Preferably, the limiting mechanism comprises a bolt, the bolt is in threaded connection with a threaded hole, one end of the bolt, which is located inside the threaded hole, is provided with a hole, a spring is arranged inside the hole, one end of the spring is fixedly connected with the inner wall of the hole, and the other end of the spring is fixedly connected with a limiting pin.
Preferably, the torsion spring is sleeved with the rotating shaft, one end of the torsion spring is connected with the fixed sleeve in an inserting mode, and the other end of the torsion spring is fixedly connected with the inner wall of the groove.
Preferably, the flexible tail wing is triangular, and one side edge of the flexible tail wing is fixedly connected with the bottom wall of the strip-shaped groove.
Compared with the prior art, the utility model provides a flexible folding wing of pipeline transmission projectile afterbody possesses following beneficial effect:
this flexible folding wing of pipeline launching projectile body afterbody has realized the folding and the expansion of flexible wing through the torsional spring, has solved the problem that occupies too much installation space, launching tube way space and projectile body space that fixed wing and roll up the arc wing and exist, possess bigger wing expansion area simultaneously. Can carry on spacingly to the fin bracing piece through limit structure, guarantee flight in-process airfoil stability, have better aerodynamic performance.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is an enlarged view of the portion A of FIG. 1 according to the present invention;
FIG. 3 is a schematic structural view of the tail wing mechanism of the present invention;
fig. 4 is an enlarged view of a portion B of fig. 3 according to the present invention.
Wherein: 1. a body of elastomer; 2. a strip-shaped groove; 3. a first base block; 4. a second base block; 5. a groove; 6. a tail wing support bar; 7. a flexible tail; 8. a rotating shaft; 9. a limiting groove; 10. fixing a sleeve; 11. a torsion spring; 12. a bolt; 13. a spring; 14. and a limiting pin.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Please refer to fig. 1-4, a flexible folding wing at tail of pipeline launching projectile body, including projectile body 1, a plurality of bar grooves 2 have been seted up on surface of projectile body 1, in practical application, a plurality of bar grooves 2 annular array distribute on surface of projectile body 1, the specific quantity of bar grooves 2 sets up to four at least, a plurality of bar grooves 2 department all is equipped with first base block 3 and second base block 4, first base block 3 and second base block 4 all set up at bar groove 2 near 1 head one end of projectile body, first base block 3 and second base block 4 are located bar groove 2 both sides respectively, first base block 3 and second base block 4 all with projectile body 1 fixed connection, be equipped with fin mechanism between second base block 4 and the first base block 3, be provided with the screw hole on the first base block 3, be provided with stop gear in the screw hole, second base block 4 is seted up flutedly on one side near first base block 3.
The tail wing mechanism comprises a tail wing support rod 6, one end of the tail wing support rod 6 is positioned between a first base block 3 and a second base block 4, the bottom edge of the tail wing support rod 6 is fixedly connected with a flexible tail wing 7, the flexible tail wing 7 is triangular, one side edge of the flexible tail wing 7 is fixedly connected with the bottom wall of a strip-shaped groove 2, the flexible tail wing 7 can be accommodated in the strip-shaped groove 2, so that the installation space is saved, one end of the tail wing support rod 6 is fixedly connected with two rotating shafts 8 which are symmetrically distributed, the two rotating shafts 8 respectively penetrate through the first base block 3 and the second base block 4, the two rotating shafts 8 are respectively movably connected with the first base block 3 and the second base block 4, the tail wing support rod 6 can rotate around the rotating shafts 8 by arranging the rotating shafts 8, one side of the tail wing support rod 6, which is close to the first base block 3, is provided with a, fixed cover 10 and 6 fixed connection of fin bracing piece, fixed cover 10 sets up to the tubulose, and torsional spring 11 is located inside recess 5, and torsional spring 11 cup joints with pivot 8, and 11 one ends of torsional spring are pegged graft with fixed cover 10, and the 11 other ends of torsional spring and 5 inner wall fixed connection of recess are favorable to driving fin bracing piece 6 and revolute 8 rotations through the elasticity of torsional spring 11.
Stop gear includes bolt 12, bolt 12 and screw hole threaded connection, the trompil has been seted up to bolt 12 one end that is located screw hole inside, the inside spring 13 that is equipped with of trompil, spring 13 one end and trompil inner wall fixed connection, spring 13 other end fixedly connected with spacer pin 14, under the flexible fin 7 state of accomodating, the fin bracing piece 6 is pressed close to the projectile body 1 surface, spacer pin 14 is located inside the trompil this moment, spring 13 is in compression state, when fin bracing piece 6 rotates under the torsional spring 11 effect, can make spacing groove 9 remove to spacer pin 14 department, spacer pin 14 can insert the spacing inslot 9 under the spring 13 effect.
When using, folding fin bracing piece 6 earlier, folding flexible fin 7 in bar groove 2 on projectile body 1, after putting into launching tube with projectile body 1, because launching tube's restriction, flexible fin 7 can not expand. After the projectile body 1 leaves the launching pipeline after being launched, the tail wing support rod 6 rotates under the action of the torsion spring 11, the flexible tail wing 7 is unfolded, after the tail wing support rod 6 rotates, the limit groove 9 on the tail wing support rod 6 moves to the limit pin 14, and the limit pin 14 is inserted into the limit groove 9 under the elastic force of the spring 13, so that the tail wing support rod 6 is fixed, and the flexible tail wing 7 is completely unfolded and stabilized.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (5)
1. The utility model provides a flexible folding wing of pipeline launch projectile body afterbody, includes projectile body (1), its characterized in that: a plurality of bar grooves (2) have been seted up on projectile body (1) surface, and are a plurality of bar groove (2) department all is equipped with first base block (3) and second base block (4), first base block (3) and second base block (4) are located bar groove (2) both sides respectively, first base block (3) and second base block (4) all with projectile body (1) fixed connection, be equipped with fin mechanism between second base block (4) and first base block (3), be provided with the screw hole on first base block (3), threaded hole is provided with stop gear, second base block (4) are close to first base block (3) one side and are seted up fluted (5).
2. The flexible folding wing for the tail of the pipeline launching projectile body as claimed in claim 1, wherein: the tail wing mechanism comprises a tail wing support rod (6), one end of the tail wing support rod (6) is positioned between the first base block (3) and the second base block (4), the bottom edge of the empennage support rod (6) is fixedly connected with a flexible empennage (7), one end of the empennage support rod (6) is fixedly connected with two rotating shafts (8) which are symmetrically distributed, the two rotating shafts (8) respectively penetrate through the first base block (3) and the second base block (4), the two rotating shafts (8) are respectively movably connected with the first base block (3) and the second base block (4), one side of the empennage support rod (6) close to the first base block (3) is provided with a limit groove (9), one side of the empennage support rod (6) close to the second base block (4) is provided with a fixed sleeve (10) and a torsion spring (11), fixed cover (10) and fin bracing piece (6) fixed connection, torsional spring (11) are located inside recess (5).
3. The flexible folding wing for the tail of the pipeline launching projectile body as claimed in claim 1, wherein: stop gear includes bolt (12), bolt (12) and screw hole threaded connection, bolt (12) are located the inside one end of screw hole and have seted up the trompil, trompil inside is equipped with spring (13), spring (13) one end and trompil inner wall fixed connection, spring (13) other end fixedly connected with spacer pin (14).
4. The flexible folding wing for the tail of the pipeline launching projectile body as claimed in claim 2, wherein: torsional spring (11) cup joints with pivot (8), torsional spring (11) one end is pegged graft with fixed cover (10), torsional spring (11) other end and recess (5) inner wall fixed connection.
5. The flexible folding wing for the tail of the pipeline launching projectile body as claimed in claim 2, wherein: the flexible tail wing (7) is triangular, and one side edge of the flexible tail wing (7) is fixedly connected with the bottom wall of the strip-shaped groove (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021488778.9U CN213335811U (en) | 2020-07-25 | 2020-07-25 | Flexible folding wing at tail of pipeline launching projectile body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021488778.9U CN213335811U (en) | 2020-07-25 | 2020-07-25 | Flexible folding wing at tail of pipeline launching projectile body |
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| Publication Number | Publication Date |
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| CN213335811U true CN213335811U (en) | 2021-06-01 |
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| CN202021488778.9U Active CN213335811U (en) | 2020-07-25 | 2020-07-25 | Flexible folding wing at tail of pipeline launching projectile body |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113371193A (en) * | 2021-06-02 | 2021-09-10 | 南京航空航天大学 | Imitative bird tail exhibition structure based on paper folding material |
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2020
- 2020-07-25 CN CN202021488778.9U patent/CN213335811U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113371193A (en) * | 2021-06-02 | 2021-09-10 | 南京航空航天大学 | Imitative bird tail exhibition structure based on paper folding material |
| CN113371193B (en) * | 2021-06-02 | 2022-04-22 | 南京航空航天大学 | Imitative bird tail exhibition structure based on paper folding material |
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Effective date of registration: 20230817 Address after: 2201-49, 22nd Floor, Building 1, Green Valley Information Industry Park, No. 368 Chengbei Street, Liandu District, Lishui City, Zhejiang Province, 323020 Patentee after: Zhejiang Xiangding Aerospace Technology Co.,Ltd. Address before: 621000 133 Mian Xingdong Road, Mianyang hi tech Zone, Sichuan Patentee before: Sichuan Yunyou Jiutian Technology Co.,Ltd. |