CN109612347B - Quick release structure for missile wing - Google Patents
Quick release structure for missile wing Download PDFInfo
- Publication number
- CN109612347B CN109612347B CN201811413428.3A CN201811413428A CN109612347B CN 109612347 B CN109612347 B CN 109612347B CN 201811413428 A CN201811413428 A CN 201811413428A CN 109612347 B CN109612347 B CN 109612347B
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- China
- Prior art keywords
- missile wing
- lug
- missile
- auxiliary
- main
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
Abstract
The invention relates to a quick release structure of a missile wing, which comprises a self-made bolt and nut (6), a main lug plate (3), an auxiliary lug plate (5) and a locking screw (4); a main lug (3) and an auxiliary lug (5) are arranged on the missile cabin body (2), and a U-shaped positioning groove is formed in the front end of the auxiliary lug (5); the missile wing (1) is provided with a main lug piece matching surface (9) and an auxiliary lug piece matching surface (7); auxiliary lug piece fitting surface (7) is provided with a positioning hole (8), a self-made screw nut (6) can be inserted into the U-shaped positioning groove, and a main lug piece (3) is provided with a threaded hole for being matched with a locking screw (4). The invention realizes the quick release function of the missile wing, realizes the reliable connection of the missile wing through one locking screw, greatly shortens the assembly and disassembly time of the missile wing, has simple structure and meets the interchangeability requirement of the missile wing.
Description
Technical Field
The invention belongs to the field of missile structure design, relates to a missile wing connecting structure, and particularly relates to a missile wing quick-release type connecting structure.
Background
In order to facilitate storage and transportation of the missile, the missile wing needs to be designed into a dismounting structure. Generally, the connection structure between the missile wing and the cabin body is a lug type joint, a multi-tenon type joint, a disc type joint and the like, which are reliable in connection but inconvenient to disassemble and assemble, and the connection is either required to use more screws or complex in connection relation, so that the requirement of quick disassembly cannot be met.
Disclosure of Invention
The purpose of the invention is as follows:
the invention aims to provide a missile wing quick-release structure aiming at the prior art situation, and aims to realize the functions of quickly disassembling and assembling missile wing surfaces.
The technical scheme adopted by the invention is as follows:
the utility model provides a missile wing rapid disassembly structure which characterized in that: the self-made bolt and nut assembly comprises a self-made bolt and nut 6, a main lug 3, an auxiliary lug 5 and a locking screw 4;
wherein, a main lug 3 and an auxiliary lug 5 are arranged on the missile cabin body 2, and the front end of the auxiliary lug 5 is provided with a U-shaped positioning groove;
a main lug piece matching surface 9 and an auxiliary lug piece matching surface 7 are arranged on the missile wing 1 at positions corresponding to the main lug piece 3 and the auxiliary lug piece 5;
the auxiliary lug piece matching surface 7 is provided with a positioning hole 8, the self-made bolt nuts 6 are oppositely screwed on two sides of the auxiliary lug piece matching surface 7 before the missile wing 1 is installed, and when the missile wing 1 is installed, the self-made bolt nuts 6 are inserted into the U-shaped positioning grooves, so that the position precision of the missile wing 1 in the course direction is ensured, and the movement of the missile wing 1 in the reverse course direction and the wingspan direction is limited;
the main lug plate 3 is provided with a threaded hole for matching with the locking screw 4, and the matching surface 9 of the main lug plate of the missile wing 1 is provided with a kidney-shaped groove 10, so that the interchangeability of installation of the missile wing is ensured.
It is characterized in that the main lug 3 is positioned in front of the auxiliary lug 5.
The locking device is characterized in that the threaded hole in the main lug plate 3 and the kidney-shaped groove 10 on the matching surface 9 of the main lug plate are inclined downwards and reversely at certain angles respectively, so that after the locking screw 4 is screwed down, the axis of the locking screw 4 is inclined downwards and reversely at certain angles respectively, acting force in the downward direction and acting force in the acting direction are generated on the missile wing 1, and the movement of the missile wing 1 in the wingspan direction and the acting direction are limited
It is characterized in that the locking screw 4 is loose-proof through the elastic pad.
The invention has the beneficial effects that:
the invention realizes the quick release function of the missile wing, realizes the reliable connection of the missile wing through one locking screw, greatly shortens the assembly and disassembly time of the missile wing, has simple structure and meets the interchangeability requirement of the missile wing.
Drawings
FIG. 1 is a view of the structure of a quick release missile wing;
FIG. 2 is a partial enlarged view of a portion B of the quick release missile;
FIG. 3 is an enlarged view of a portion A of the quick release missile wing;
FIG. 4 shows a structure diagram of a self-made bolt and nut;
FIG. 5 is a view of a missile wing structure;
FIG. 6 is an enlarged view of a portion of the missile wing B;
fig. 7 is a partially enlarged view of the portion of the missile wing a.
Detailed Description
The invention is described in further detail below with reference to the drawings.
As shown in fig. 1-2, the quick release structure of the missile wing of the invention is characterized in that: the self-made bolt and nut assembly comprises a self-made bolt and nut 6, a main lug 3, an auxiliary lug 5 and a locking screw 4;
the missile cabin body 2 is provided with a main lug 3 and an auxiliary lug 5, the main lug 3 is positioned in front of the auxiliary lug 5, and the front end of the auxiliary lug 5 is provided with a U-shaped positioning groove;
a main lug piece matching surface 9 and an auxiliary lug piece matching surface 7 are arranged on the missile wing 1 at positions corresponding to the main lug piece 3 and the auxiliary lug piece 5; the auxiliary lug piece matching surface 7 is provided with a positioning hole 8, the self-made bolt nuts 6 are oppositely screwed on two sides of the auxiliary lug piece matching surface 7 before the missile wing 1 is installed, and when the missile wing 1 is installed, the self-made bolt nuts 6 are inserted into the U-shaped positioning grooves, so that the position precision of the missile wing 1 in the course direction is ensured, and the movement of the missile wing 1 in the reverse course direction and the wingspan direction is limited; the main lug 3 is provided with a threaded hole for matching with the locking screw 4, a waist-shaped groove 10 is formed in the main lug matching surface 9 of the missile wing 1, the interchangeability of installation of the missile wing is guaranteed, the threaded hole and the waist-shaped groove 10 are respectively inclined at a certain angle towards the downward direction and the reverse direction, after the locking screw 4 is screwed down, the axis of the locking screw 4 is respectively inclined at a certain angle towards the downward direction and the reverse direction, acting force towards the downward direction and the direction is generated on the missile wing 1, and the movement of the missile wing 1 in the wingspan direction and the direction is limited.
During assembly, the self-made bolt and nut 6 is twisted on two sides of the auxiliary lug piece matching surface 7, the missile wing 1 is pushed to enable the main lug piece matching surface and the auxiliary lug piece matching surface to be attached to the main auxiliary lug piece, the self-made bolt and nut 6 is aligned to the U-shaped positioning groove and inserted into the U-shaped positioning groove and fixed, and finally the locking screw 4 is screwed into the main lug piece 3 to enable the missile wing 1 to be compressed. When the elastic wing 1 is disassembled, the locking screw 4 is taken down, and the elastic wing 1 is pushed forwards and upwards along the chord plane of the elastic wing 1, so that the elastic wing 1 can be disassembled.
Claims (2)
1. The utility model provides a missile wing rapid disassembly structure which characterized in that: comprises a self-made bolt and nut (6), a main lug (3), an auxiliary lug (5) and a locking screw (4);
wherein, a main lug (3) and an auxiliary lug (5) are arranged on the missile cabin body (2), and the front end of the auxiliary lug (5) is provided with a U-shaped positioning groove;
the missile wing (1) is provided with a main lug piece matching surface (9) and an auxiliary lug piece matching surface (7) at the positions corresponding to the main lug piece (3) and the auxiliary lug piece (5);
the positioning hole (8) is formed in the auxiliary lug piece matching surface (7), the self-made bolt and nut (6) is oppositely screwed on two sides of the auxiliary lug piece matching surface (7) before the missile wing (1) is installed, and when the missile wing (1) is installed, the self-made bolt and nut (6) is inserted into the U-shaped positioning groove, so that the position precision of the missile wing (1) in the course direction is ensured, and the movement of the missile wing (1) in the reverse course direction and the wingspan direction is limited;
the main lug plate (3) is provided with a threaded hole for matching with the locking screw (4), and a waist-shaped groove (10) is formed in the main lug plate matching surface (9) of the missile wing (1) to ensure the interchangeability of installation of the missile wing;
the main lug (3) is positioned in front of the auxiliary lug (5);
the threaded hole in the main lug plate (3) and the kidney-shaped groove (10) in the main lug plate matching surface (9) are inclined downwards and reversely at certain angles respectively, so that after the locking screw (4) is screwed down, the axis of the locking screw (4) is inclined downwards and reversely at certain angles respectively, acting force in the downward direction and acting force in the acting direction are generated on the missile wing (1), and the movement of the wingspan direction and the acting direction of the missile wing (1) is limited.
2. The quick release structure of a missile wing as claimed in claim 1 wherein the locking screw (4) is locked by the elastic washer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811413428.3A CN109612347B (en) | 2018-11-23 | 2018-11-23 | Quick release structure for missile wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811413428.3A CN109612347B (en) | 2018-11-23 | 2018-11-23 | Quick release structure for missile wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109612347A CN109612347A (en) | 2019-04-12 |
| CN109612347B true CN109612347B (en) | 2021-05-18 |
Family
ID=66005030
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811413428.3A Active CN109612347B (en) | 2018-11-23 | 2018-11-23 | Quick release structure for missile wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109612347B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113899252A (en) * | 2021-10-21 | 2022-01-07 | 上海机电工程研究所 | Connecting device for missile wing and missile body and missile |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3219158A (en) * | 1964-03-30 | 1965-11-23 | Ralph E Carter | Quick attach panel fastener |
| US3228335A (en) * | 1964-05-25 | 1966-01-11 | Robert S Thompson | Dovetail locking device |
| US3276377A (en) * | 1964-11-03 | 1966-10-04 | Jack B Bell | Fin locking device |
| US20080078859A1 (en) * | 2006-06-23 | 2008-04-03 | Turner Mark A | Folding control surface assembly and vehicle incorporating same |
| CN202228488U (en) * | 2011-09-26 | 2012-05-23 | 江西洪都航空工业集团有限责任公司 | Connecting structure capable of being disassembled and assembled |
| CN205403618U (en) * | 2016-02-24 | 2016-07-27 | 江苏优培德复合材料有限公司 | Short carbon fiber guided missile all -wing aircraft of cutting |
| CN107953297A (en) * | 2017-11-08 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing fast assembly and disassembly mechanism |
-
2018
- 2018-11-23 CN CN201811413428.3A patent/CN109612347B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3219158A (en) * | 1964-03-30 | 1965-11-23 | Ralph E Carter | Quick attach panel fastener |
| US3228335A (en) * | 1964-05-25 | 1966-01-11 | Robert S Thompson | Dovetail locking device |
| US3276377A (en) * | 1964-11-03 | 1966-10-04 | Jack B Bell | Fin locking device |
| US20080078859A1 (en) * | 2006-06-23 | 2008-04-03 | Turner Mark A | Folding control surface assembly and vehicle incorporating same |
| CN202228488U (en) * | 2011-09-26 | 2012-05-23 | 江西洪都航空工业集团有限责任公司 | Connecting structure capable of being disassembled and assembled |
| CN205403618U (en) * | 2016-02-24 | 2016-07-27 | 江苏优培德复合材料有限公司 | Short carbon fiber guided missile all -wing aircraft of cutting |
| CN107953297A (en) * | 2017-11-08 | 2018-04-24 | 江西洪都航空工业集团有限责任公司 | A kind of missile wing fast assembly and disassembly mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109612347A (en) | 2019-04-12 |
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