Abstract
The research focuses on the thermal interface design of the HAKUTO Rover Flight Model (FM) and its evaluation using the final thermal vacuum experiment. Initially, an analytical thermal model was developed, dividing the rover into six distinct radiating surfaces. The surface temperature of the rover was then determined based on its orientation relative to the solar radiative flux, as well as other thermal factors such as lunar radiation, solar albedo, and conduction from the lunar regolith. By considering the impact of these heat sources, suitable mounting locations for the avionics and the angle of the solar panels were determined to optimize the rover's thermal performance and power generation while ensuring the rover's mass remained under 4 kg. After the preliminary thermal analysis, numerical computational simulations were conducted to further elaborate on the thermal response of the final HAKUTO Rover FM design, which was then verified through a thermal balance test in a vacuum environment.
Abstract (translated)
URL
https://arxiv.org/abs/2610.28127
