摘要
以第二代升力式再入飞行器为应用背景,对飞行器再入飞行后的末端能量管理方法进行了深入的研究和分析.在参考航天飞机末端能量管理方法的基础上,分析了TAEM段轨迹参数,优化设计了TAEM段地面轨迹和高度剖面,并进行了纵向和侧向制导律设计.仿真结果表明本文设计的TAEM飞行轨迹满足飞行约束条件,制导方法具有较高的精度和适应性,能满足第二代升力式再入飞行器末端能量管理要求.
According to the application of the 2nd generation lifting reentry vehicle, a further research and analysis was performed for the TAEM. Based on the space shuttleg trajectory and guidance of TAEM, several parameters of TAEM trajectory are analyzed, and the ground trajectory and altitude profiles of TAEM are de- signed by optimization. Also, the longitudinal and lateral guidance laws are given in order to make simulation verification for the reference trajectory. Simulation results satisfy all of the trajectory constraints, and the guid- ance algorithm has been proved effective and accurate. The guidance method validates that the guidance is fea- sibility and validity for TAEM of the 2nd generation lifting reentry vehicle.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2012年第9期20-24,共5页
Journal of Harbin Institute of Technology
关键词
末端能量管理
再入飞行器
轨迹优化
terminal area energy management
reentry vehicle
trajectory optimization
