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Design of multi-mission spacecraft busThis 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.
Document ID
19920050562
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Agrawal, Brij N.
(U.S. Naval Postgraduate School Monterey, CA, United States)
Date Acquired
August 15, 2013
Publication Date
February 1, 1992
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 92-0980
Accession Number
92A33186
Distribution Limits
Public
Copyright
Other

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