| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aerospace engineering and may be used at spacecraft for adjustment and calibration of ground and space complexes. Spacecraft comprises body with instrumentation panel, solar cells, reference reflectors, engine compartment, multi-charge launchers for storage and extraction of reference reflectors. Launcher comprises cylindrical container with sets of reference reflectors confined by thrusts, reflector feed rope mechanism, reflector separation speed transducer, launch carriage with electric drive of reflector grip and feed, spring pushers and displacement mechanism. Launch carriage is arranged outside aforesaid container.EFFECT: improved configuration, increased number of reflectors, decreased structural mass consumption per one reflector.3 dwg |
