A defect repair method based on integrally formed heat-resistant materials for returnable spacecraft

A technology for a returnable spaceship and a heat-proof material, which is applied in the field of repairing the defects of the integrally formed heat-proof material for the returnable spaceship, can solve the problems of a long preparation period, uneven local density and complicated process of the integrally formed heat-proof material of the returnable spaceship , to achieve the effect of ensuring flatness, ensuring bonding strength, and ensuring bonding strength

Active Publication Date: 2021-09-03
BEIJING SATELLITE MFG FACTORY
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Problems solved by technology

[0003] The preparation cycle of integrally formed heat-resistant materials for returnable spacecraft is long and the process is complicated. During the preparation process, defects such as local uneven density and poor glue may occur. It is necessary to propose a defect repair method for integrally formed heat-resistant materials for returnable spacecraft. , it can still be repaired after local defects occur, meeting the end-use performance

Method used

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  • A defect repair method based on integrally formed heat-resistant materials for returnable spacecraft
  • A defect repair method based on integrally formed heat-resistant materials for returnable spacecraft

Examples

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Embodiment

[0050] Carry out X-ray and visual flaw detection for an integrally formed heat-resistant material in the aerospace field. After the defect is found, the defect position is marked according to the detection. The maximum defect size range is 60mm*60mm, and the depth is 4mm.

[0051] Machining: Use mechanical processing methods to remove all heat-resistant materials at the defect position according to the marked defect position. The removal size is 110mm*110mm and the depth is 6mm.

[0052] Machining of repairing and filling blocks: select the blank that is consistent with the raw material of the integrally formed heat-resistant material to prepare mechanically processed repairing and filling blocks. According to the size of the removal position, the repair and filling blocks are processed into squares, and the shape and removal position require (+0.5~+1) mm glue joint gap, after the repair block is glued, there must be no 2mm step difference between the height direction of the he...

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Abstract

A method for repairing defects based on integrally formed heat-resistant materials for returnable spacecraft, (1) performing flaw detection on integrally formed heat-resistant materials for returnable spacecraft, and confirming the size and depth of defects on the integrally formed heat-resistant materials for returnable spacecraft; (2) Use the method of mechanical processing to remove all the heat-resistant materials at the defect position; (3) Use phenolic resin to paint, cure and polish the defect removal position; (4) Prepare the repair block and repair the block The size is processed according to the size of the defect removal position; (5) Use an adhesive to glue the repair filler block in the defect removal position to complete the defect repair of the integrally formed heat-resistant material of the returnable spacecraft.

Description

technical field [0001] The invention relates to a process method for repairing defects of integrally formed heat-resistant materials of a reversible spacecraft. The invention belongs to the field of the thermal protection system of the returnable spaceship of the second cosmic speed. Background technique [0002] During the reentry flight, the returnable spacecraft needs to experience high heat flow erosion. The outer surface of the returnable spacecraft must have a reliable and erosion-resistant thermal protection system to ensure the protection of the equipment and personnel inside the spacecraft. With the continuous development of deep space exploration technology, in view of the heat flow environment of the second space flight speed, it is required that the ablation layer on the surface of the thermal protection system cannot crack or fall off, and the structural stability and integrity of the surface are required to be high. hot material. [0003] The preparation cycl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C73/26B29C73/10
CPCB29C73/10B29C73/26B29C2073/262B29C2073/264
Inventor 宫顼关鑫张明赖小明尉世厚杨雷张璇张鹏飞刘佳杨海涛张玉生黎昱张鑫陶涛殷雷马彬
Owner BEIJING SATELLITE MFG FACTORY
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