Thermal insulation structure repairing method

A technology of radial size and position, applied in the field of thermal protection structure maintenance, can solve the problems of reducing the maintenance cycle and cost of hypersonic aircraft, and achieve the effect of shortening the maintenance cycle, good high temperature resistance and heat insulation performance, and avoiding secondary damage

Inactive Publication Date: 2019-07-02
BEIJING AEROSPACE TECH INST
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Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, provide a method for repairing the heat insulation structure, solve the problem of r

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  • Thermal insulation structure repairing method
  • Thermal insulation structure repairing method

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[0027] The present invention will be described in detail below with reference to specific examples and drawings.

[0028] A method for repairing thermal insulation structure: processing the damaged part of the thermal insulation structure, and processing the irregular damaged part into a regular-shaped repair hole, and the processing method is low-speed processing, and the radial size of the repair hole is larger than the damaged part The radial size of the repair block is larger than 5mm; the repair block with similar shape to the repair hole is processed, and n glue grooves are set in the longitudinal direction of the repair block; the side and bottom surface of the repair block, and each surface of the repair hole are evenly coated with high-temperature adhesive Place the repair block in the repair hole to ensure that the high temperature resistant adhesive can fill the gap between the repair block and the repair hole; after curing the high temperature resistant adhesive, polis...

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Abstract

The invention provides a thermal insulation structure repairing method. The method includes the steps that a damaged part of a thermal insulation structure is treated, and the non-regular damaged partis treated into a repairing hole in a regular shape; a repairing block with the shape similar to that of the repairing hole is machined, and n glue guiding grooves are formed in the repairing block in the longitudinal direction; the side surfaces and the bottom surface of the repairing block and all surfaces of the repairing hole are uniformly coated with a high-temperature-resistant adhesive; the repairing block is placed in the repairing hole, and it is guaranteed that a gap between the repairing block and the repairing hole can be filled with the high-temperature-resistant adhesive; and curing treatment is carried out on the high-temperature-resistant adhesive, and treatment is finished, the surfaces of the repairing block and the surface of an original thermal insulation structure aretreated by using a high-temperature-resistant adhesive, so that the treated surfaces of the repairing block are in smooth transition with the treated surface of the thermal insulation structure. According to the method, the repair problem after an outer surface heat protection structure of a hypersonic aircraft is damaged is solved, and the maintenance period and cost of the hypersonic aircraft are effectively reduced.

Description

technical field [0001] The invention relates to a method for repairing a heat insulation structure, which belongs to the technical field of heat protection structure maintenance. Background technique [0002] At present, foreign hypersonic vehicles generally adopt lightweight ceramic matrix composite materials with integrated anti-heat insulation function for thermal protection structure design. While this type of material has excellent erosion resistance, temperature resistance, heat insulation and other properties, it also has low strength. , high brittleness, and easy bump damage during ground operation. In view of the damage to the ceramic-based heat-insulation structure on the outer surface of hypersonic vehicles, the current common practice is to replace the damaged ceramic-based heat-insulation structure. For example, the US space shuttle uses silica ceramic tiles as its heat protection structure. According to the plan, the number of damaged insulation tiles after ea...

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Application Information

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IPC IPC(8): B28D1/00B64G1/58
CPCB28D1/00B64G1/58
Inventor 曹杰熊强宋月娥李晶全栋梁王洋张帆马寅魏陈晓娜韩乐
Owner BEIJING AEROSPACE TECH INST
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