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An assembly method for an aircraft to assemble an omni-axial thermal protection component

An assembly method and thermal protection technology, which is applied in aircraft assembly, aircraft component testing, etc., can solve the problem that aircraft thermal protection components cannot be assembled accurately, and achieve the effect of ensuring accurate assembly method, strong operability, and precise position

Active Publication Date: 2020-07-28
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide an assembly method for an aircraft to assemble omni-axial thermal protection components, so as to solve the problem that the aircraft thermal protection components cannot be assembled accurately

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  • An assembly method for an aircraft to assemble an omni-axial thermal protection component
  • An assembly method for an aircraft to assemble an omni-axial thermal protection component
  • An assembly method for an aircraft to assemble an omni-axial thermal protection component

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Embodiment Construction

[0016] 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.

[0017] With the background of a three-axis precise assembly method for a thermal protection structure of an aircraft, the present invention provides an assembly method for assembling an omni-axial thermal protection component of an aircraft, which specifically includes the following steps:

[0018] S1. According to the installation requirements proposed by the design, the thermal protection components are installed on the lower surface of the No. 2 cabin, and the assembly sequence of the thermal protection components is confirmed. The installation sequence is as attached figure 1 As shown, the order of disassembly is just opposite to the order of installation;

[0019] S2. Determine the overturning tooling of the aircraft in all axial directions, the overturning tooling 5 can clamp the ...

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Abstract

The invention discloses a method for assembling axial thermal protection components on an aircraft. The method comprises the following steps that a face cabin body profile face is swept before the thermal protection components are mounted, the assembling order and relationship of the thermal protection components are determined, the aircraft is assembled on an overturning tool, a limiting block isdesigned according to the theoretical gap between the two adjacent thermal protection components, and the thermal protection components are mounted sequentially according to the assembling order. Themethod for assembling the axial thermal protection components on the aircraft realizes the accurate positioning and bonding links of the thermal protection components, achieving of the precise assembling method of a thermal protection structure is ensured, precision of the protection position is achieved, validating is conducted through a process scheme, and the operability is high.

Description

technical field [0001] The invention belongs to the field of thermal protection system assembly, and in particular relates to an assembly method for an aircraft to assemble omni-axial thermal protection components. Background technique [0002] In recent years, with the continuous improvement of flight parameters such as missile flight altitude, range, and Mach number, flight loads such as force, heat, noise, and vibration have become increasingly severe. The shape of the missile body is complex, the volume is large, and the weight is light. 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, and at the same time, its assembly parameters (gap and step difference, etc.) need to be strictly controlled in...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/10B64F5/60
CPCB64F5/10B64F5/60
Inventor 陈紫轩杨春宇郑健王晶刘岭
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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