This paper presents preliminary design of a multimission spacecraft bus for meteorological and communications payloads. The meteorological payload uses sun-synchronous circular orbit and the communications payload uses Molniya type orbit to provide communications for areas not covered by geosynchronous communications satellites. The launch vehicles are Pegasus for the meteorological payload and Taurus for the communications payload. The spacecraft bus uses three-axis stabilization consisting of a three reaction wheel system. The electric power system consists of single-axis tracking silicon solar array and Ni2 H2 batteries. The propulsion subsystem consists of six hydrazine thrusters and one propellant tank.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Design of multi-mission spacecraft bus


    Contributors:

    Publication date :

    1992-02-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Design of multi-mission spacecraft bus

    AGRAWAL, BRIJ | AIAA | 1992


    Spacecraft mission design

    Brown, Charles D. | SLUB | 1992


    Spacecraft mission design

    Brown, Charles D. | SLUB | 1998


    Spacecraft mission design

    Brown, Charles D. | TIBKAT | 1998


    Spacecraft mission design

    Brown, Charles D. | SLUB | 1996