FIELD: cosmonautics.
SUBSTANCE: invention relates to the field of space equipment and can be used for separating power structures of spacecrafts. The separation system for power structures of spacecrafts comprises power units installed along the circumference of the separated structures. The power units are tightened with a bandage secured by two diametrically located pyro units. The pyro units are located diametrically opposite from each other without rigid attachment to the structure. Between the power units, protection is installed on the separated part of the structure, in the form of a closed-loop lattice casing, secured whereon with threads and an adhesive material, e.g., with polyamide threads and tapes with an adhesive layer, is a polymer material.
EFFECT: reliability is increased.
3 cl, 4 dwg
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