FIELD: astronautics.
SUBSTANCE: invention relates to the technology of assembling spacecraft (SC), mainly telecommunication satellites. Method is applicable to a spacecraft consisting of a payload module (PM) and a service system module (SSM) manufactured separately and combined by electrical, mechanical and hydraulic interfaces at the final stage of the spacecraft manufacturing. Part of the PM structure covers the central part of the SSM structure. PM assembling is performed on a removable processing rig equivalent in size to the covered part of the SSM and mated to the covering part of the PM structure. Axes of the rig coordinates coincide with the axes of the SC coordinates. Sequentially mounted are the basic (one or more), support and instrument panels. On the panels of the assembled PM structure, fixed are devices, equipment, interfaces and other elements.
EFFECT: technical result is the improvement of quality and reduction of the labour intensity of assembly operations due to their optimization and unification, as well as increasing the accuracy of the positioning of the PM elements.
4 cl, 13 dwg
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Authors
Dates
2018-06-19—Published
2017-02-28—Filed