TY  - JOUR
AB  - 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.
VL  - 80
IS  - 1
SN  - 0002-2667
DO  - 10.1108/00022660810842010
UR  - https://doi.org/10.1108/00022660810842010
AU  - Justin Jose Nesamani Gilbert
AU  - Chandrakant Joshi Sunil
AU  - Jin Zhanli
AU  - Keong Chan Poh
AU  - Cheng Lee Soon
PY  - 2008
Y1  - 2008/01/01
TI  - Design and development of thermal test model of a micro‐satellite for thermal balance test
T2  - Aircraft Engineering and Aerospace Technology
PB  - Emerald Group Publishing Limited
SP  - 51
EP  - 58
Y2  - 2024/04/23
ER  -