Transition Trajectory Guidance for A Conceptual Space-based Missile

摘要：

　　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.

关键词： Transition Trajectory Guidance Space-based Missile Finite Thrust Guidance Virtual Reentry Position

作者: Zhengdong Hu Xuemei Tang Wenli Yan

作者单位: Science and Technology on Complex Land Systems Simulation Laboratory,Beijing 100012

会议类型: 国际会议

会议名称: 第26届中国控制与决策会议(2014 CCDC)

会议地点: 长沙

会议语种:英文

页码: 3426-3429

在线出版日期: 2014-05-31（万方平台首次上网日期，不代表论文的发表时间）