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Multi-purpose satellite busThe Multi-Purpose Satellite bus (MPS) can be used for a number of payloads which may require different orbits, pointing accuracy, and electrical power consumption. Specifically, it was designed to accommodate the Advanced Very High Resolution Radiometer and an EHF communication payload, both of which have a three-year life. The estimated beginning-of-life weight of the MPS bus is 150 kg. It can be launched by either the Pegasus ALV or the Taurus SSLV. Configuration requirements for the different missions are discussed.
Document ID
19920063841
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Sakoda, Daniel
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Agrawal, Brij N.
(U.S. Naval Postgraduate School Monterey, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Meeting Information
Meeting: Annual AIAA/Utah State University Conference on Small Satellites
Location: Logan, UT
Country: United States
Start Date: August 26, 1991
End Date: August 29, 1991
Accession Number
92A46465
Distribution Limits
Public
Copyright
Other

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