Translator Disclaimer
31 May 2006 University Nanosat System thermal design, analysis, and testing
Author Affiliations +
Thermal design for space systems is an iterative process that balances the temperature requirements for all mission phases with the available resources. Secondary payloads often have to be designed for a wide range of conditions available on various launch platforms, without the benefit of additional resources such as power or thermal shielding. This paper will discuss the thermal design, analysis, and thermal vacuum testing of a small satellite payload that was initially intended for launch from the US Space Shuttle and eventually launched on the EELV Heavy demonstration in December 2004.
© (2006) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Charlotte Gerhart "University Nanosat System thermal design, analysis, and testing", Proc. SPIE 6221, Modeling, Simulation, and Verification of Space-based Systems III, 62210A (31 May 2006);


Small satellite thermal design, test, and analysis
Proceedings of SPIE (May 31 2006)
CHIPS microsatellite optical system: lessons learned
Proceedings of SPIE (September 03 2008)
Passive cryocooler for microsatellite payload
Proceedings of SPIE (November 18 1998)
EELV Secondary Payload Adapter (ESPA)
Proceedings of SPIE (November 07 2000)

Back to Top