Missile wing quick disassembling structure

A technology of wings and main lugs, which is applied in the direction of projectiles, offensive equipment, weapon types, etc., can solve the problems of complex connection relationship, inability to meet quick disassembly, inconvenient disassembly and assembly, and meet the requirements of interchangeability and simple structure , The effect of reducing the time of assembly and disassembly

Active Publication Date: 2019-04-12
JIANGXI HONGDU AVIATION IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Usually, the connection structures between the wings and the cabin include lug joints, multi-mortise joints, disc joints, etc. The above structures are reliable in connection, but inconvenient to disassemble and assemble. The connection may require more screws. Or the connection relationship is complicated, which cannot meet the requirements of quick disassembly

Method used

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  • Missile wing quick disassembling structure
  • Missile wing quick disassembling structure
  • Missile wing quick disassembling structure

Examples

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Embodiment Construction

[0023] The present invention will be further described in detail below in conjunction with the accompanying drawings.

[0024] Such as figure 1 -2, the wing quick release structure of the present invention is characterized in that it includes self-made bolts and nuts 6, main lugs 3, auxiliary lugs 5 and locking screws 4;

[0025] Wherein, the main ear piece 3 and the auxiliary ear piece 5 are arranged on the missile cabin body 2, the main ear piece 3 is located at the front part of the auxiliary ear piece 5, and a U-shaped positioning groove is opened at the front end of the auxiliary ear piece 5;

[0026] The matching surface 9 of the main lug and the matching surface 7 of the auxiliary ear are set on the position corresponding to the main lug 3 and the auxiliary lug 5 on the wing 1; the matching surface 7 of the auxiliary lug has a positioning hole 8, and before the wing 1 is installed, Tighten the self-made bolts and nuts 6 on both sides of the auxiliary lug mating surface...

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Abstract

The invention relates to a missile wing quick disassembling structure, which comprises self-made bolt nuts (6), a main lug sheet (3), an auxiliary lug sheet (5) and a locking screw (4). The main lug sheet (3) and the auxiliary lug sheet (5) are arranged on a missile bay (2), and a U-shaped positioning groove is formed in the front end of the auxiliary lug sheet (5); a missile wing (1) is providedwith a main lug sheet matching face (9) and an auxiliary lug sheet matching face (7); and the auxiliary lug sheet matching face (7) is provided with a positioning hole (8), the self-made screw nuts (6) can be inserted into the U-shaped positioning groove, and the main lug sheet (3) is provided with a threaded hole for being matched with the locking screw (4). According to the missile wing quick disassembling structure, the missile wing quick disassembling function is achieved, the missile wing is reliably connected through the locking screw, the time of assembling and disassembling of the missile wing is greatly reduced, the structure is simple, and the missile wing meets the interchangeability requirement.

Description

technical field [0001] The invention belongs to the field of missile structure design, and relates to a missile-wing connection structure, in particular to a missile-wing quick-detachable connection structure. Background technique [0002] In order to facilitate the storage and transportation of missiles, it is necessary to design the missile wings as a disassembled structure. Usually, the connection structures between the wings and the cabin include lug joints, multi-mortise joints, disc joints, etc. The above structures are reliable in connection, but inconvenient to disassemble and assemble. The connection may require more screws. Or the connection relationship is complicated, which cannot meet the requirements of quick disassembly. Contents of the invention [0003] Purpose of the present invention: [0004] The purpose of the present invention is to design and provide a missile wing quick disassembly structure aiming at the above-mentioned prior art situation, and t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B10/02
CPCF42B10/02
Inventor 陈雷吴华晴邹敏怀马俊飞付俊兴瞿绍奇邬亨贵陈逸云欧阳金栋姚盼盼
Owner JIANGXI HONGDU AVIATION IND GRP
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