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Design of the Thermal Control System for the Space Technology 5 MicrosatelliteThe New Millennium Program's (NMP) Space Technology 5 (ST-5) Project, currently in Phase B of the design process, is slated to launch three 20-kg class spin stabilized microsatellites in late 2003. The proposed orbit is highly elliptical and could result in an earth shadow eclipse of almost 2 hours. Although ST-5's maximum eclipse is only 2 hours, future missions could involve eclipses as long as 8 hours. As spacecraft size, mass, and available resources decrease and eclipse duration increases, thermal engineers will be challenged to design simple but robust thermal control systems that meet temperature requirements for all phases of the mission. This paper presents the results of a study of three design concepts and preliminary analysis of the design selected for ST-5.
Document ID
20020002376
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Douglas, Donya
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Michalek, Ted
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Swanson, Ted
(NASA Goddard Space Flight Center Greenbelt, MD United States)
Brodeur, Stephen
Date Acquired
August 20, 2013
Publication Date
January 1, 2001
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
SAE-01ICES-7
Meeting Information
Meeting: 31st International Conference on Environmental Systems (ICES)
Location: Orlando, FL
Country: United States
Start Date: July 9, 2001
End Date: July 12, 2001
Sponsors: Society of Automotive Engineers, Inc.
Distribution Limits
Public
Copyright
Other

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