Analysis of Atmospheric Drag Acceleration and Engineering Realization of Space Target

Space target orbit determination module is an important component of space target surveillance radar system. The development of this module requires very complex aerospace dynamics knowledge, which brings great difficulties to non-orbit mechanics researchers engaged in radar system design. The core of orbit determination is the calculation of perturbation acceleration, which is the basis of high precision numerical orbit calculation. To this end, this paper takes the atmospheric drag perturbation which can not be ignored in the precise orbit determination of LEO satellite as an example, introduces its mathematical principle, gives the program design idea and function interface implementation, and makes a simulation comparison with STK. The experimental results verify the effectiveness of the interface function, and show that the function interface designed in this paper can assist researchers in radar system design.