Aerodynamic force and moment computations for very low Earth orbit satellites using a TPMC model

Abstract

The recent upswing in satellite operations of very low Earth orbit has triggered the necessity to evaluate aerodynamic forces and moments, which can significantly affect satellite orbit. The present paper evaluates the aerodynamic forces and pitching moment on a satellite design using the test particle Monte Carlo method, accounting for the contribution of solar panel shape and placement relative to the position of the center-of-gravity of the satellite. Simulation results show that solar panel placement has significant effects on the moments caused by the solar panel aerodynamic forces. From the computations, an optimal satellite configuration that has both reduced drag and enhanced longitudinal static stability can be identified for a given volume and solar panel area. A sensitivity study was performed to understand the contribution of varying thermospheric conditions and satellite pitch on computed drag forces. This analysis highlights the importance of including a variable drag model in an orbit propagator to account for changes of operation altitude, attitude, and solar activity.