A detachable multi-lobed cabin section butt joint heat protection structure

A flap-type, heat-proof technology, used in offensive equipment, projectiles, self-propelled bombs, etc., can solve the problems of inconvenient assembly and disassembly, low efficiency, etc., to improve rapid response capabilities, low operating efficiency, and meet the needs of rapid disassembly. the effect of

Active Publication Date: 2021-06-11
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • 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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  • A detachable multi-lobed cabin section butt joint heat protection structure
  • A detachable multi-lobed cabin section butt joint heat protection structure
  • A detachable multi-lobed cabin section butt joint heat protection structure

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Embodiment Construction

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

[0027] The multi-lobe heat-proof ring structure at the docking section of the hypersonic aircraft 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 complex, so there are many The shape of the flap-type heat protection ring structure should also be designed with a transitional design along with its curved surface. However, the multi-lobed heat shielding ring is composed of multi-lobed heat shielding ring 1, docking frame 2, countersunk head screws 3, and silicone rubber 4, regardless of whether the structure is complex or not. Its structural composition and installation diagram are as follows figure 1 shown.

[0028] The docking frames 2 between the cabins are radially connected by countersunk screws, and the docking frame is m...

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Abstract

A detachable multi-lobed cabin section butt heat-proof structure, the docking frames of the two cabin sections to be docked are radially connected, and the outer ring at the radial connection is equipped with a multi-petal heat-proof ring. The heat ring is in clearance fit with the outer heat-proof structure of the above-mentioned butt joint two compartments. The present invention aims at the docking structure between the cabin sections that require repeated disassembly and assembly, and proposes that the docking place adopts a multi-lobed heat-proof ring that is easy to disassemble to prevent heat at the docking part—that is, the cabin section docking still uses countersunk head screws in the radial direction The docking form is just to install the multi-lobed heat-proof ring by screwing after the docking. The multi-lobed heat-proof ring covers all the docking screws and the docking parts to protect the heat, and can be disassembled and operated repeatedly. It is simple and meets the requirements 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 butt joint between the cabin sections of a hypersonic aircraft. The detachable multi-lobe cabin-section butt heat-proof structure realizes the operation of rapid installation and disassembly of the cabin sections, and simplifies the traditional tactical weapon cabin. The heat-proof structure treatment of the docking between the segments can not only realize the function of heat-proof and heat-proof, but also meet the fast maintenance response time required by the troops. The multi-lobe cabin-section docking heat-proof structure can be applied to the heat-proof design of various hypersonic aircraft cabin-section docking structures. Background technique [0002] According to the structural layout and assembly requirements of hypersonic aircraft, the overall structure is generally decomposed into multiple cabins butt joints, a...

Claims

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Application Information

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Patent Type & Authority Patents(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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