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Journal cover: Aircraft Engineering and Aerospace Technology

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Online from: 1929

Subject Area: Mechanical & Materials Engineering

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Design and development of thermal test model of a micro-satellite for thermal balance test


Document Information:
Title:Design and development of thermal test model of a micro-satellite for thermal balance test
Author(s):Gilbert Justin Jose Nesamani, (Centre for Research in Satellite Technologies (CREST), Nanyang Technological University, Singapore), Sunil Chandrakant Joshi, (Centre for Research in Satellite Technologies (CREST), Nanyang Technological University, Singapore), Zhanli Jin, (Centre for Research in Satellite Technologies (CREST), Nanyang Technological University, Singapore), Poh Keong Chan, (Centre for Research in Satellite Technologies (CREST), Nanyang Technological University, Singapore), Soon Cheng Lee, (Centre for Research in Satellite Technologies (CREST), Nanyang Technological University, Singapore)
Citation:Gilbert Justin Jose Nesamani, Sunil Chandrakant Joshi, Zhanli Jin, Poh Keong Chan, Soon Cheng Lee, (2008) "Design and development of thermal test model of a micro-satellite for thermal balance test", Aircraft Engineering and Aerospace Technology, Vol. 80 Iss: 1, pp.51 - 58
Keywords:Artificial satellites, Control, Thermal measurement
Article type:Research paper
DOI:10.1108/00022660810842010 (Permanent URL)
Publisher:Emerald Group Publishing Limited
Abstract:

Purpose – This paper seeks to provide an insight into the design and development of the thermal test model (TTM) of X-Sat, a 120?kg class micro-satellite, being developed at the Centre. This model was specifically constructed for carrying out a thermal balance test (TBT) in a 4?m diameter vertical thermal vacuum chamber.

Design/methodology/approach – The construction of the thermal model followed a structural mock-up model which was modified thermally to suit the purpose. Specific and careful consideration was given to the geometry and, more importantly, thermal characteristics such as thermal mass, surface properties, etc. to mimic the actual satellite configuration as closely as possible. Test plans were devised to qualify the fabricated components to meet the out-gassing and other thermal requirements for the model. Design and qualification of supporting frame and linkages for TBT are also covered.

Findings – It is possible to simulate the thermal characteristics of a micro-satellite in orbit under a different mission scenario through proper scaling and using alternative material options while developing TTM.

Originality/value – The paper discusses in detail the simplified cost-effective approach of constructing TTM and also outlines the various issues to be considered for a TBT. It provides valuable information needed for micro-satellite designers.



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