Numerical Investigation of the Launch Vibration and Orbital Thermal Behaviour of a CubeSat

Abstract

CubeSat missions are subjected to the induced vibrations of the rocket during launch, and then they are exposed to an extreme thermal environment while in orbit around Earth. These conditions have the potential to damage the components of the satellite and cause a failure for the mission. Thus, numerical models are used to identify and resolve structural and thermal problems in a CubeSat design to increase the chance of mission success. The accuracy of a model is dependent on the correct application of boundary conditions and simulation parameters, as well as its level of geometric detail. A vibration and a thermal numerical model of the Western Skylark CubeSat were therefore developed with a high level of detail to accurately simulate its response to the expected environmental conditions. It was found that the increase in the resolution of the model better captured the behaviour of the Western Skylark in reaction to its environmental conditions, indicating that similar techniques should be employed by future CubeSat projects. The results showed that there were high stress concentrations in the threaded rods of the structure due to the random vibration loading. Further, two of its sensors, the Fine Sun Sensor and the CubeMag Deployable, achieved temperatures that were either below their operational or survival limits. Solutions to these concerns are provided.