FIELD: space engineering; communication space vehicles. SUBSTANCE: space vehicle includes instrument and equipment compartment 1 having rectangular spatial form with equipment panels 2 located on its side faces. Orientation mechanism 3 located in central portion of each side face of truss is connected with on-board photoconverter panel 4. Rigidly secured on front face of truss is antenna platform 5 on which mast 6 with antenna 7 is mounted; antenna has S range. Brackets 8 are mounted on lateral surfaces of antenna platform along longitudinal axis of space vehicle. Rear end of each bracket 8 holds reflector 10 of Ku range antenna mounted through opening and locking mechanism; front end of bracket 8 carries antenna feed unit 11. On-board photoconverter panels 4 are located beyond zone of reflector aperture of antennae 10. During injection, space vehicle is located under aerodynamic nose fairing 13. EFFECT: large number of reflector-type antennas of Ku range at limited diameter of aerodynamic nose fairing; increased capacity of satellite communication systems. 2 cl, 2 dwg
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Authors
Dates
1997-11-27—Published
1995-12-19—Filed