Optimal spacecraft hardware placement to minimize required power input for hibernation survival

Spacecraft hardware placement is an important factor in the structural and thermal performance of a spacecraft. This is especially true for a solar powered lunar roving vehicle with a passive thermal control system. Lunar roving vehicles are subjected to a 354 hour day and night cycle with extreme high and low temperature environments. A systematic approach to hardware placement considering thermal performance would allow engineers to fully explore the design space early in the spacecraft design process. Genetic algorithm optimization is used to determine optimum component placement that minimizes required hibernation power during the lunar night. This optimization strategy enables significant mass reduction of onboard batteries while retaining system performance. The optimization strategy is capable of considering conductive and radiative heat transfer to produce a hardware layout strategy that survives both the worst case hot and worst case cold conditions required for the lunar roving vehicle. A case study was presented that demonstrates a 56% reduction in hibernation power in a 19 component system while ensuring all 19 components have a small form factor, a balanced center of gravity, and operate within their allowable temperature ranges.