Special-shape missile bay section connecting structure for sectional fairing deploying

A technology for connecting structures and missile compartments, applied to self-propelled bombs, weapon types, projectiles, etc., can solve the problems of inconsistent joints, poor workmanship, and inability to prevent loosening of threads, and achieve easy manufacturing process and good load-bearing performance Effect

Inactive Publication Date: 2015-04-29
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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  • Abstract
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  • Claims
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AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a special-shaped missile cabin connection structure suitable for split-flap throwing covers, to solve the problems that the screw threads cannot be prevented from loosening and the butt joints are inconsistent when the special-shaped missile cabins are connected, and to overcome the gap at the butt joints , the problem of poor workmanship

Method used

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  • Special-shape missile bay section connecting structure for sectional fairing deploying

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Embodiment Construction

[0014] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0015] As shown in Figure 1, a special-shaped missile cabin section connection structure suitable for split-flap throwing covers includes a guide cabin metal shell 1, a warhead cabin metal shell 5, and a cabin body adapter ring 7, wherein, There is a threaded structure on the inner wall of the right side edge of the metal shell 1 of the pilot cabin that covers the heat-proof layer 2 of the pilot cabin, and the left side of the thread structure end of the metal shell 1 of the pilot cabin is a raised structure, forming a stop at the end of the thread. The push surface, and two anti-loosening holes are opened on the raised structure; the cabin body adapter ring 7 is a stepped cylindrical structure, and the diameter of the left side of the cylinder wall is small, and it is raised with the metal shell 1 of the guide cabin. The structure ma...

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Abstract

The invention relates to the technical field of special-shape aircraft bay connecting section, and particularly discloses a special-shape missile bay section connecting structure for sectional fairing deploying. The special-shape missile bay section connecting structure comprises a guide bay metal shell, a warhead bay metal shell and a bay body adapter ring, wherein the bay body adapter ring is of a step-shaped cylinder structure, and is fixedly connected with the guide bay metal shell through a thread structure, the left cylinder wall of the bay body adapter ring and the guide bay metal shell are fixedly connected through an anti-loosening pin, the warhead bay metal shell is matched with the end surface of the guide bay metal shell, the inner wall of the warhead bay metal shell is matched with the right cylinder wall of the bay body adapter ring, and the warhead bay metal shell and the bay body adapter ring are fixedly connected through a connecting pin. The special-shape missile bay section connecting structure has the advantages that the problems of failure of loosening prevention of bay section large threads and the nonuniform butting surface of the special-shape bay body are solved; compared with the flap type quick connecting, the bearing property of the butting surface is good, the gap of the butting surface is avoided, and the implementation of manufacturing technology is easy.

Description

technical field [0001] The invention belongs to the technical field of cabin section connection of special-shaped aircraft, and in particular relates to a cabin section connection structure of special-shaped missiles suitable for split-flap ejection. Background technique [0002] In order to meet the precise strike requirements for small-scale targets in missile emergency operations and the precise strike requirements for multiple types of targets in different battlefield environments, a gliding missile with a symmetrical profile uses a high-precision composite guidance system of inertial + GPS + infrared imaging. In the gliding section, the GPS signal is used to correct the inertial group error. After entering the attack section, when the infrared seeker is turned on, it turns to the infrared terminal guidance mode. When the seeker is working at a predetermined height, it is necessary to throw off the heat shield of the seeker to expose the optical head cover at its front e...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/36
Inventor 常园园杨浩韩旭周克华王捷冰商学谦占续军朱秉诚
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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