摘要
作为低成本飞行的气动力辅助变轨是当前和未来的空间和星际探测任务的一个重要策略。基于最优变轨的精度、稳定性和鲁棒性的要求 ,促进了大气飞行的制导发展。尽管最优变轨要遵循性能指标、控制余度或性能和控制余度的组合指标要求来进行 ,但是实际上可把变轨弧段分成两部分 ,再入后可采用平衡滑行 ,以获得最佳性能要求 ;逸出前的弧段则采用升力降的轨道 ,可增大逸出后近地点的高度 ,而使在希望到达的远地点的速度冲量最小。按照这种升力调制控制原则 ,讨论了 3种制导方法 :即预测校正法、显式制导法和能量控制器法 。
Aeroassisted orbital transfer (AOT) as a low cost maneuver flight is an important strategy of current and future space and interplanetary missions. The atmosphereic guidance concepts of these flights are developed in view of the precision, stability and robustness requirements of AOT trajectories, which exhibit many of the desirable characteristics by the optimization. Although the optimal AOT can be generated by extremizing a fucntional measuring performance, control margin, or a combination of them, yet in practice the trajectory can be separated into two phases, an equilibrium glide phase for the first part of the AOT is used to obtain the best performance after entry atmosphere and a lift-down configuration for the final part of the exit phase is used to help maximize the perigee altitude and then to minimize characteristic velocity. According to this flight modulation control, the three guidance algorithms discussed in this paper include a predictor/corrector, a explicit guidance and a energy controller, and they can all effectively control the optimal AOT.
出处
《导弹与航天运载技术》
北大核心
2003年第6期25-31,共7页
Missiles and Space Vehicles
基金
国家自然科学基金资助
项目编号为 195 82 0 05
