FIELD: space technology.
SUBSTANCE: invention relates to space technology, represents a body of a payload module (PM) of a spacecraft and can be used to create a modular type SC for various purposes. The case of the PM spacecraft is installed on the central part of the spacecraft. The case consists of a horizontal base panel, which has attachment points with the central part of the spacecraft, two vertical support panels, which have attachment points with the central part of the spacecraft and the base panel, and two instrument panels, having attachment points with the base and base panels. On the base panel, a conical or cylindrical load-bearing structure is rigidly fixed, which is covered by a horizontal base panel of the second tier with a central hole. Rigidity panels are installed along the load-bearing structure, rigidly connecting it to the base panel of the second tier.
EFFECT: providing thermal decoupling of honeycomb panels made of materials with different CTE, due to the absence of attachment points between the base panel of the second tier with the instrument panels of the spacecraft PN body.
2 cl, 3 dwg
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Authors
Dates
2022-10-04—Published
2022-06-08—Filed