A trajectory design methodology is developed for autolanding phase of RLV (Reusable Launch Vehicle) based on iterative correction algorithm in this paper. According to the inherent traits in phase of unpowered landing of RLV, geometric structure of trajectory and dynamic characteristics of the aircraft are studied in detail. And mathematical descriptions of the trajectory as well as the selection principle and calculation formula of feature parameters are given. Compared with the traditional design methods of trajectory, this methodology is simple and rapid. The simulation results also demonstrate the feasibility, effectiveness, and superiority of the algorithm.
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