Error analysis for hill's guidance in rendezvousing a target on elliptical orbit

In the phase of rendezvousing a target on elliptical orbit, the accuracy of Hill's guidance is concerned with several error factors. The error factors considered here are mainly navigation error and actuation error. Basic analytic formulas of error models are derived. Compared with the situation of rendezvousing a target on circular orbit, we analyzed the terminal position error by the navigation error influence of initial true anomaly. Then an improved method of Hill's guidance is designed. The improved algorithm can obviously enhance the terminal position accuracy. The simulation results by Monte-Carlo method show that logically changing initial true anomaly can decrease the terminal position error by the navigation error, and the improved method can further enhance the guidance accuracy.