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dc.contributor.authorAgrawal, B.N.
dc.contributor.otherDepartment of Aeronautics and Astronautics
dc.date.accessioned2019-09-11T19:46:08Z
dc.date.available2019-09-11T19:46:08Z
dc.date.issued1992-02
dc.identifier.urihttp://hdl.handle.net/10945/63208
dc.description1992 Aerospace Design Conference February 3-6, 1992 /Itvine, CAen_US
dc.descriptionThe work presented in this paper was performed under spacecraft design project course at the Naval Postgraduate School.
dc.description.abstractThis paper presents preliminary design of a multi-mission 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 threeaxis stabilization consisting of 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.en_US
dc.description.sponsorshipNASA/Universities Space Research Association Advanced Design Programen_US
dc.description.sponsorshipNaval Postgraduate School (NPS)en_US
dc.description.sponsorshipNaval Research Laboratory (NRL)en_US
dc.description.sponsorshipJet Propulsion Laboratory (JPL)en_US
dc.description.sponsorshipDefense Advanced Research Project Agency (DARPA)en_US
dc.description.sponsorshipMIT Lincoln Laboratoryen_US
dc.format.extent11 p.en_US
dc.publisherAIAAen_US
dc.rightsThis 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.titleDesign of Multipurpose Spacecraft BUSen_US
dc.typeConference Paperen_US
dc.contributor.corporateNaval Postgraduate School (U.S.)en_US


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