Determining Aerothermodynamic Effects on Very-Low-Earth-Orbit Satellites Using Direct Simulation Monte Carlo Method

Abstract

Very low Earth orbits (VLEOs) have an altitude of 100–450 km and have become a popular topic in space technology owing to their high application potential. However, spacecraft experience stronger aerothermodynamic effects at VLEOs. In this study, we used a parallel direct simulation Monte Carlo (DSMC) code called PDSC++ and compared it with a traditional DSMC code. The results are in good agreement with the benchmarks. We also simulated the aerothermodynamic factors of a CubeSat, including the operating attitude, orbit altitude, size configuration, and solar panel deployment. The simulations indicate that CubeSats experience minimum drag at an angle of attack of 45°. The orbit altitude strongly affects the particle flow around and stress on a CubeSat. Moreover, a large CubeSat with solar panels experiences high drag and stress. These results can be used as a guide for further research on the service length and other configurational factors of CubeSats.