摘要
研究了异面低地轨道（ＬＥＯ－ＬＥＯ）变轨过程中，气动辅助轨道转移飞行器（简称ＡＯＴＶ）在大气内飞行的最优闭环导引律的一种设计方法．对气动辅助轨道转移飞行器大气内飞行的动力学模型进行合理的简化和近似，将ＡＯＴＶ燃料最省的指标转化为大气出口速度极大条件的性能指标，然后应用最优控制理论，经数学推导得到了控制变量与飞行器状态的解析关系，即ＡＯＴＶ近最优导引律．数学仿真验证了所设计的导引律是正确可行的．
Presents the investigation of an approximate optimal guidance law for the aeroassisted plane change problem (LEO - LEO), which transforms the performance of the least fuel costs into that of maximizing the exit velocity after approximating and simplifying the dynamical equations of AOTV, and establishes the AOTV approximate optimal guidance between control variables and the spacecraft state variables, and concludes from numerical simulation results that the designed guidance is accurate and effective.
出处
《哈尔滨工业大学学报》
EI
CAS
CSCD
北大核心
2001年第2期183-185,共3页
Journal of Harbin Institute of Technology
基金
高等学校博士点专项科研基金(97021324)
