FIELD: solar batteries.
SUBSTANCE: invention relates to the assembly of solar battery (hereinafter – SB) panels of a spacecraft. The method consists in the fact that the side panels of the SB are fixed to the central panel of the SB on both sides by means of hinged nodes. In this case, the central panel is fixed on the technological device, and the side panels are de-weighted relatively to the central panel, allowing them to rotate freely around the axes of the hinge nodes. By this rotation, the panel package is transferred to the configuration necessary for further manufacturing of the SB.
EFFECT: increased manufacturability of the assembly of large-area SB.
1 cl, 2 dwg
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