Multi-Purpose Satellite Bus
| dc.contributor.author | Sakoda, Daniel | |
| dc.contributor.author | Agrawal, Brij | |
| dc.date | 08/01/91 | |
| dc.date.accessioned | 2013-11-13T01:03:31Z | |
| dc.date.available | 2013-11-13T01:03:31Z | |
| dc.date.issued | 1991-08 | |
| dc.identifier.uri | https://hdl.handle.net/10945/37313 | |
| dc.description | Publication: AIAA/USU Conference on Small Satellites | en_US |
| dc.description | Technical Session III: Military Applications | en_US |
| dc.description.abstract | This paper presents design considerations of a Multi-Purpose Satellite bus (MPS). The project was sponsored by the NASA Universities Space Research Association (USRA) Advanced Design Program. A multi-purpose satellite bus was selected as the study topic from a Statement-of-Work generated by the Defense Advanced Research Projects Agency. The estimated beginning-of-life weight of the MPS bus is 150 kg. A detailed analysis with two dissimilar payloads (a meteorological payload and a communication payload), both having a three year life, demonstrates the flexibility of the bus. The MPS bus was designed to mate with the Pegasus Air Launched Vehicle and the Taurus Standard Small Launch Vehicle. The satellite bus design is presented with emphasis on configuration requirements due to the dissimilar mission demands. | en_US |
| dc.description.sponsorship | This project was sponsored by the NASA/Universities Space Research Association (USRA)Advanced Design Program. | en_US |
| dc.rights | This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States. | en_US |
| dc.title | Multi-Purpose Satellite Bus | en_US |
