Analysis of CubeSat thermal performance using various PV panel configurations

Abstract

Managing the temperature of a nanosatellite is crucial to ensure the proper functioning of the payload and the platform during a mission. A thermal engineer faces the challenge of keeping both within acceptable temperature margins, which can be affected by various factors such as solar radiation, heat generated by on board equipments, and the spacecraft's orientation. To address this challenge, a simplified thermal model is typically created and examined. This model takes into account the spacecraft's geometry, material properties, and environmental factors to determine the temperature of critical components. This paper presents the results of simulations conducted on a 3D CubeSat orbiting at an altitude of 600Km. The simulations explore various PV panel combinations to determine the best compromise between thermal control and allowable power. This involves finding the optimal PV panel configuration that provides the necessary thermal control while still allowing the spacecraft to operate within its power constraints.