FIELD: transport.
SUBSTANCE: invention relates to protective device of spacecraft used to protect opto-electronic hardware against heat and light effects. Proposed flap comprises panel and fasteners. Said panel represents two closed rigidly interconnected tubular carcasses. Inner space of said carcasses has two layers of screen-vacuum heat-insulation packages (SVHI) with mesh tensioned there between and fastened to tubular carcasses. SVHI packages are fastened together and to mesh at separate points. Tubular carcass and SVHI packages are coated with facing fabric with optical coefficients. Cover flap is 8.4 times easier than known design.
EFFECT: production of required design.
4 dwg
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