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Repair method of multi-layer composite thermal protection component

A repair method and composite technology, which is applied in the field of repair of multi-layer composite thermal protection components after partial damage, can solve problems such as difficulty, collapse, and performance degradation, and achieve strong operability, saving production cycle and materials cost effect

Inactive Publication Date: 2018-01-09
BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The multi-layer composite thermal protection component is connected to the load-bearing structure through high-temperature-resistant adhesives. During subsequent assembly and transportation, impact by external force may cause the upper panel to crack or even collapse as a whole, and its performance will drop sharply.
It is very difficult to adopt the overall component replacement scheme, which is limited by factors such as the preparation cycle, price, and replacement process

Method used

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  • Repair method of multi-layer composite thermal protection component
  • Repair method of multi-layer composite thermal protection component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0019] For 1) the damaged area is not larger than 20mm×20mm and there is no damage to the fiber suture,

[0020] (1) Select the appropriate drill bit according to the damage area, and the drill bit should be smaller than the diameter of the damage area (1±0.5) mm. Adjust the drilling depth of the drill bit, remove the fiber-reinforced ceramic panel and the collapsed airgel insulation material on the upper surface of the damaged area, and form a circular hole with a depth of not less than 3mm.

[0021] (2) Grind the heat insulation tile until the external dimensions match the hole: the diameter of the heat insulation tile is smaller than the hole (0.5±0.2)mm, and the length is greater than the hole depth (0.5±0.1)mm.

[0022] (3) Grooves with a depth of (0.5±0.1) mm and a width of (1±0.5) mm are processed on the side of the heat insulation tile, and the groove spacing is (5±1) mm.

[0023] (4) The bottom surface and side of the heat insulation tile are bonded with glue. If the...

Embodiment 2

[0026] For 2) the damaged area is larger than 20mm×20mm or the fiber suture is damaged

[0027] (1) Determine the local replacement area according to the damage area, and the replacement area is generally a regular rectangle.

[0028] (2) Cut the ceramic panel on the upper surface with a grinding wheel saw. The distance between the cutting area of ​​the grinding wheel saw and the theoretical edge is not less than 10mm, and use a saw blade to saw the ceramic panel on the upper surface within 10mm. Cut the lower surface ceramic panel along the airgel with a foot knife. The thermal protection component is separated from the load-bearing structure (metal cabin) by a glue line.

[0029] (3) Clean up the residual adhesive layer on the surface of the bearing structure.

[0030] (4) Cut the multi-layer composite thermal protection material, and match the trimmed edge to the size of the cleaned area: the thickness of the multi-layer composite thermal protection material after cutting...

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Abstract

The invention belongs to the technical field of thermal protection, and particularly relates to a repair method of a locally-damaged multi-layer composite thermal protection component. When the damaged area is not larger than 20mm*20mm and fiber suture lines are not damaged, the locally-damaged part is cleaned, and then the cleaned partially-damaged part is sealed with a thermal insulating tile; the bottom surface with adhesives, and the side surfaces with adhesives, of the thermal insulating tile, are glued; in order to protect the connection strength of the thermal insulating tile, grooves are designed in the side surfaces of the tile as adhesive storage grooves, so that the glue joint area can be increased; and the final aerodynamic configuration is obtained by polishing the upper surface of the thermal insulating tile. When the damaged area is larger than 20mm*20mm or the fiber suture lines are damaged, the locally-damaged part is cleaned, and then the multi-layer composite thermalprotection component is glued; the bottom surface, with adhesives, of the multi-layer composite thermal protection component is glued with a load-bearing structure; the gap between the multi-layer composite thermal protection component and the surrounding thermal protection component is sealed through a flexible thermal insulation material; and the adhesive layer thickness is adjusted according to the step difference between butt joint gaps of a repair part and the original gluing part, the adhesive layer thickness is controlled within 0.2mm - 0.8mm, and the final aerodynamic configuration isguaranteed.

Description

technical field [0001] The invention belongs to the technical field of heat protection, and in particular relates to a method for repairing partially damaged multilayer composite heat protection components. Background technique [0002] When a hypersonic vehicle (Mach number ≥ 5) flies in the atmosphere, the air temperature rises sharply due to the influence of "aerodynamic heating", and the heat energy is quickly transferred to the surface of the vehicle. In order to ensure that the structural temperature is controlled within the allowable range, the outer surface of the vehicle Generally, anti-heat insulation materials are laid, which have anti-scouring, anti-oxidation and ablation resistance and high-efficiency heat insulation properties. [0003] According to preliminary evaluation and ground tests, a multi-layer composite heat protection material has become one of the outer heat protection materials for hypersonic aircraft due to its many advantages in weight, heat insu...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/40
Inventor 赵欣游晶王旭冉
Owner BEIJING XINGHANG MECHANICAL ELECTRICAL EQUIP
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