FIELD: astronautics.
SUBSTANCE: invention relates to spacecraft (SC). Manufacturing of the payload module (PLM) of the spacecraft of the block-modular design consists in assembling the PLM on the process equipment separately from the service system module (SSM). Assembly of the PLM power frame, consisting of honeycomb panels and fastening structural elements, is produced on a demountable technological tool. After the manufacture of the power frame is completed, a technological corset is mounted on the outside of it, providing the specified parameters of positioning and rigidity of the power frame, after that the dismountable processing tool is removed, and further installation of instruments and equipment on the power frame, rigging with PLM, its transportation and installation on the SSM is carried out in the technological corset, removed after the final assembly of the spacecraft.
EFFECT: technical result of the invention is to provide predetermined positioning parameters and rigidity of the PLM due to increasing the accuracy of positioning of landing surfaces and sizes of the PLM when performing rigging, internal machining and mounting on the SSM in a technological corset.
1 cl, 5 dwg
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Authors
Dates
2018-06-29—Published
2017-02-28—Filed