Abstract: An autonomous orbit control method using Bplane parameters as targeting parameters is proposed during the phase of approaching the deep space celestial body. First, the navigation system determines the current position and velocity of the spacecraft, which are mapped onto the Bplane to get the deviation from the desired encounter condition by integrating the dynamic model, and then the velocity increment for the orbital correction is derived using linear guidance formula and the error ellipse is utilized to describe the Bplane error. Finally, Monte Carlo simulation results show that the method is capable of guiding the Mars probe to a successful encounter.

Key words: autonomous orbit control, Bplane, error ellipse, deepspace exploration