Recent efforts in space exploration have focused on budget solutions for
monitoring Earth’s climate and astrophysics. Implementing such a satellite requires thermal
design in order to maintain the scientific instruments and bus components within their ideal operating
temperatures. This paper outlines the thermal system’s engineering design and thermal analysis for a High
Usability Host Spacecraft. Preliminary thermal engineering results suggest that the High Usability Host
Spacecraft concept proposed herein is viable for low-cost scientific instrumentation satellite based missions.
Keywords: NX space systems thermal, satellite, spacecraft, systems engineering, thermal control.
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