Method for calculating force and moment of aerodynamic drag of a satellite with complex shape

The paper proposes and implements a method for calculating the main forces and moments caused by the interaction of the atmosphere and the surface of a low Earth orbit satellite. Both values depend significantly on the orientation of the spacecraft relative to the incoming flow. In this paper, the entire calculation process is divided into a preliminary computationally expensive first stage and a second stage, which is used to calculate the right-hand sides of the equations of motion. The interaction is assumed to be diffuse-specular, and the incoming flow is free-molecular.