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Detachable multivalve cabin section abutting heat protection structure

A flap-type, heat-proof technology, used in projectiles, self-propelled bombs, offensive equipment, etc., can solve the problems of low efficiency, inconvenient assembly and disassembly, etc., achieve low operation efficiency, meet the requirements of rapid disassembly and assembly, good isolation heat effect

Active Publication Date: 2019-04-09
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This solution is very inconvenient during assembly and disassembly, and requires careful handling of each screw and a certain curing time, which is very inefficient

Method used

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  • Detachable multivalve cabin section abutting heat protection structure
  • Detachable multivalve cabin section abutting heat protection structure
  • Detachable multivalve cabin section abutting heat protection structure

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Embodiment Construction

[0026] The present invention will be described in detail below in conjunction with the accompanying drawings and examples.

[0027] The multi-lobed heat-proof ring structure at the joint between the hypersonic aircraft cabins is divided into two categories according to the different docking sections, the actuator section and the non-actuator section. The aerodynamic shape of the actuator section is more complicated, so many The shape of the petal-type heat-proof ring structure should also be transitionally designed with its curved surface. However, no matter whether the structure of the multi-lobed heat-proof ring is complex or not, its structure is composed of a multi-lobed heat-proof ring 1, a docking frame 2, a countersunk screw 3, and a silicone rubber 4. The structural composition and installation diagram are as follows figure 1 shown.

[0028] The docking frame 2 between cabin sections is radially connected by countersunk screws, and the connecting thread is processed o...

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Abstract

The invention relates to a detachable multivalve type cabin section abutting heat protection structure. Abutting frames of two cabin sections to be abutted are radially connected, an outer ring at theradial connecting part is provided with a multivalve type heat protection ring, and the multivalve type heat protection ring is in clearance fit with the outer heat protection structures of the two abutted cabin sections. With regard to the abutting structure between cabin sections with repeated disassembly and assembly requirements, the multivalve heat protection ring which is convenient to disassemble and assemble is adopted to prevent heat at the abutting part, that is, the abutting of the cabin sections still adopts a countersunk screw radial abutting mode, but the multivalve heat protection ring is only mounted in a screw joint mode after being abutted; and the multivalve heat protection ring covers all abutting screws and the abutting part to play a heat protection role, can be repeatedly disassembled and assembled, is simple and convenient to operate, and meets the requirement of rapid maintenance response.

Description

technical field [0001] The invention belongs to the field of heat-proof structure design. The invention is a local heat-proof structure suitable for the joints of hypersonic aircraft cabins. The detachable multi-lobed cabin joint heat-proof structure realizes the operation work of quickly installing and disassembling cabins, and simplifies traditional tactical weapon cabins. The heat-proof structure treatment of the docking between the sections can not only realize the heat-proof function, but also meet the rapid maintenance response time required by the troops. The multi-lobed cabin section joint heat-proof structure can be applied to the heat-proof design of various hypersonic aircraft cabin section joint structures. Background technique [0002] According to the structural layout and assembly requirements of a hypersonic vehicle, the overall structure is generally decomposed into multiple cabins butt joints, and each cabin has its own unique heat-resistant materials and ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F42B15/00F42B15/34
CPCF42B15/00F42B15/34
Inventor 金玲宋磊刘爱莲张程陈星星周剑波许俊伟聂青张晶王聪伟卞亚东关强余天一赵鹏飞程运江王毅王丽华刘铎陈学生陈克毕海东黄燕珺孟兆威孔繁良王强
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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