FIELD: astronautics.
SUBSTANCE: invention relates to space engineering, particularly, to spacecraft optoelectronic devices. Method of assembling optoelectronic devices of spacecraft consists in the fact that optoelectronic devices are installed on a spacer-stable frame isolated from the useful load. Frame is pivoted via hinge joints from the spacecraft body. Optoelectronic devices are placed at a distance from each other in the volume limited by the size of the fairing. Optoelectronic devices are grouped together and mounted on independent brackets on the frame assembly elements. Frame is made of a set of carbon-fibre rods of round cross-section and connected through direct interface of connection directly with carbon-fibre power tube of spacecraft body. Nodal elements are assembled from thin-walled titanium fittings with hinges. Compensation of temperature deformations along three axes relative to one rigidly fixed point is provided with the help of node elements. Each independent bracket is adjusted to set accurate positioning of optoelectronic devices.
EFFECT: enabling stability of position under action of dynamic loads.
1 cl, 3 dwg
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Authors
Dates
2020-09-21—Published
2019-10-03—Filed