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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...
A direct method is discussed for multistage launch vehicle ascent trajectory optimization. First the optimal control problem is modeled with the performance index as maximum terminal mass. A modified Gauss Pseudospectral method is used to design a rapid optimal algorithm for multistage launch vehicle ascent trajectory. The nonlinear terminal state constraints are converted into linear terminal state...
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