High-heat-resistance sealed cabin pipeline cabin penetration flange and machining method

Abstract

The invention belongs to the field of spacecraft assembly structure design and particularly relates to a pipeline cabin penetration flange of a spacecraft sealed cabin body. The high-heat-resistance sealed cabin pipeline cabin penetration flange comprises a cup-shaped flange base, a guide pipe and a supporting gasket. The cup-shaped flange base comprises a cup body and a flange base body. One end of the guide pipe penetrates through the cup bottom of the cup body in the cup-shaped flange base and is fixed through welding, and the other end of the guide pipe penetrates through a central through hole of the flange base body. A gap between the other end of the guide pipe and the central through hole of the flange base body is filled through the supporting gasket. Ventilation holes are circumferentially and uniformly distributed in the supporting gasket. The cup-shaped flange base of the pipeline cabin penetration flange has the characteristic of high heat resistance and adopts the towering cup body type design, the path where heat of a spacecraft cabin body structure is transmitted to the guide pipe can be prolonged, and the transmission efficacy of the heat is effectively relieved.

Description

technical field [0001] The invention belongs to the field of spacecraft general assembly structure design, and in particular relates to a pipeline penetrating flange of a sealed cabin body of a spacecraft. Background technique [0002] Penetrating flanges are the main form to realize the internal and external pipeline connection of the spacecraft's sealed cabin. For spacecraft with complex piping systems, there can be as many as dozens of pipeline penetrating flanges. The sealing performance of the penetrating flange plays a vital role in the pressure maintenance and leakage of the medium in the sealed cabin. For a self-sealing spacecraft without the function of air supply and pressure maintenance, the leakage of the gas medium in the sealed cabin will directly affect the pressure of the cabin. The pressure and thermal control environment in the cabin will cause the failure of the test load carried in the cabin; for the spacecraft with air supply and pressure maintenance, th...

AI Technical Summary

Problems solved by technology

The sealing connection between the pipeline piercing flange and the structure of the sealed cabin adopts the form of metal surface connection and embedded O-ring sealing ring. Therefore, in order to improve the thermal resistance characteristics of the piercing flange, a non-metallic The thermal insulation pad cannot meet the sealing connection between the penetration flange and the cabin body; if the heat insulation penetration flange of non-metallic material is used, it cannot meet the support strength of the penetration pipeline and the flange can not meet the requirements. tightness

[0004] At present, in the general assembly design of spacecraft, the design of the penetrating flange structure of the pipeline in the airtight cabin adopts the form of a common flange surface and a certain length of pipeline screwed or welded sections protruding from both sides. It can meet the strength support of the pipeline through the cabin, and can also realize the tightness of the connection between the flange surface and the cabin structure, but the temperature of the cabin can be directly transmitted to the pipeline through the flange plane with almost no delay. Flanges do not have high thermal resistance characteristics

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