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A kind of disassembly method of large size and small thickness high temperature resistant structure

A disassembly method and small thickness technology, applied in the field of aircraft thermal protection structure assembly, can solve the problems of large size, small thickness, difficult installation and disassembly methods, etc., to avoid scratches and damage, improve disassembly efficiency, and ensure disassembly The effect of stability

Active Publication Date: 2019-08-06
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The structure with TPS cover has the characteristics of special-shaped curved surface, large size, and small thickness. The conventional installation and disassembly methods are difficult to meet. It is urgent to propose a high-temperature-resistant structure disassembly method for real-time protection of TPS under complex profiles. In view of this, it is necessary to design a A disassembly and assembly method of a large-size, small-thickness, high-temperature-resistant structure, which realizes repeated disassembly and assembly of the structure with a TPS cover

Method used

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Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0037] In order to make the purpose, content, and advantages of the present invention clearer, the specific implementation manners of the present invention will be further described in detail below in conjunction with examples.

[0038] The embodiment of the present invention is described by taking the rear equipment hatch cover of an aircraft as an example.

[0039] The rear equipment hatch cover disassembly method provided by the embodiment of the present invention includes the following steps:

[0040] Step 1. Through the three-dimensional model of the rear equipment hatch and its assembly process, extract the connection interface that can be disassembled and used on the hatch; the rear equipment hatch is equipped with TPS material;

[0041] Step 2. Design the tooling for disassembling and assembling the cover, including designing the guide device and operating tooling, specifically:

[0042] Step 21. At the front and rear center of the rear equipment compartment, there is...

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PUM

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Abstract

The invention relates to a large-size small-thickness and high-temperature-resistant structure disassembling and assembling method, and relates to the technical field of aircraft thermal protection structure assembling. According to the large-size small-thickness and high-temperature-resistant structure disassembling and assembling method, by putting forward a design method and a using method of disassembling of a tooling, large-size small-thickness and high-temperature-resistant structure disassembling and assembling are achieved. Through the large-size small-thickness and high-temperature-resistant structure disassembling and assembling method, the disassembly stability of an aircraft cover can be ensured; scratch and damage to TPS on the cover are avoided; and disassembling and assembling efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of assembly of aircraft thermal protection structures, in particular to a method for disassembling and assembling a large-sized and small-thick high-temperature-resistant structure. Background technique [0002] In recent years, with the continuous improvement of aircraft flight parameters such as altitude, range, and Mach number, flight loads such as force, heat, noise, and vibration have become increasingly severe. trend, the ensuing problem is the large-area use of high-temperature-resistant thermal protection materials (referred to as thermal protection components), and thermal protection components have problems such as low density, poor impact resistance, and no pressure resistance. Real-time protection is required during the process. [0003] In order to meet the thermal protection requirements of the projectile, an aircraft bonded TPS on the surface of the entire aircraft (including the flap). TPS i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/10B23P19/00G06T15/00
CPCB23P19/00B23P2700/01B64F5/10G06T15/005
Inventor 陈紫轩杨春宇王晶李军武珂
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP