Abstract:

To deal with the rendezvous problem between the small satellite and the co-orbital target, a guidance strategy was developed to make the satellite meet the target in a desired time. A quadratic equation about the relative motion between the two satellites and the transfer time was derived using the homogeneous central gravity field model. An analytic solution to the equation can provide the optimal thrust time and thrust direction of the fuel-fixed, open-time intercept. An improved guidance algorithm was proposed by replacing the analytic method during the free-flight phase with the Lambert guidance algorithm. Simulations were conducted and their results were tested by STK software to be correct and effective.

Key words: control and navigation technology of aerocraft, small satellite, co-orbital transfer, analytic guidance method, Lambert algorithm