Simulation and Emulation of Orbit Parameters of Spacecraft Based on Satellite Passive Detection

The medium-low orbit satellite is used as observation satellite to make parameters estimation and error analysis of the spacecraft orbit. Based on the variable mass particle dynamics, the simplified motion equation of observation satellite was numerically solved by the Runge-Kutta method, and the position of the observation satellite at any time was calculated more accurately. Based on the variable mass particle dynamics, the orbit estimation equation of the spacecraft was given, and the position and the velocity data of the spacecraft at any time were numerically solved by the Runge-Kutta method, and then the fitting curves of these data were obtained. The residual analysis was made to test the output from the model, which indicated that this model is acceptable and valid.