Transition trajectory guidance for a conceptual space-based missile

The transition trajectory guidance technology for a conceptual space-based missile is studied in this paper. Firstly the conception of using a missile striking from space is described. For the extraatmospheric flight phase, the time-fixed orbital transfer theory is utilized to determine braking position and braking velocity. And then a finite thrust guidance approach with gravity anomaly compensation by virtual reentry position prediction is presented to eliminate planning error. Finally, the performance of the proposed guidance approach is verified and analyzed by computer simulation.