FIELD: aviation.
SUBSTANCE: invention relates to the manufacturing and ground testing of a spacecraft (SC), primarily telecommunications satellites. Spacecraft power system contains a solar panel (1) connected to a load (3) via connectors (1-3, 1-2), and a stabilized voltage converter (2), as well as a battery (5) connected to a stabiliser (2). In course of manufacturing of the spacecraft, the connectors (1-2) and (1-3) are undocked (the solar panel is replacing its simulator (9)), and a ground charge-discharge complex (10) is connected to the battery (5). The battery (5) is connected to the common bus by common terminal (grounded on the body (8) of the SC) through the connectors (5-2), and through the connectors (5-1) and the contacts (2-1) - with the stabiliser (2) by B-positive. When assembling the spacecraft and between its electrical tests, the connectors (5-2) are undocked, and technological cables-inserts (5-3) with resistance of (1÷10) kOm are inserted into their break. Connectors "A", "B" in the circuit from the battery (5) to the common power bus are selected with sockets on the battery (5) side. Connectors "C" and "D" are not regulated by the "plug-socket" position.
EFFECT: provided fail-free spacecraft manufacturing process.
2 cl, 1 dwg
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Authors
Dates
2018-06-15—Published
2016-07-01—Filed