摘要
在燃料一定的情况下,研究连续推力作用下卫星轨道的相对可达区域非常重要。通过对动力学模型的分析,将相对可达区域的计算转化为对最优控制问题的求解,通过对优化模型的分析,最终将最优控制问题的求解转化为对线性微分方程组的求解。给出了卫星轨道相对可达区域的确定方法,对不同燃料和时间限制情况下卫星的相对可达区域进行了计算、仿真和分析,并给出了相应的变化规律。
This paper studies the relative reachable domain of satellite trajectory generated after continuous-thrust applied. With analysis of the dynamic model, the calculation of relative reachable domain was transformed as the solution of the optimal control problem and through the analysis on the optimization model, the solution of the optimal control problem was transformed into the solution of linear differential equations. A method of determining the relative reachable domain was proposed in the paper. Based on different fuel limits and different time limits,calculation and simulation for relative reachable domain were presented. And various regularities of relative reachable domain under respective limits were analyzed.
出处
《飞行力学》
CSCD
北大核心
2011年第1期63-65,88,共4页
Flight Dynamics
关键词
卫星轨道
连续推力
最优控制
相对可达区域
satellite trajectory
continuous-thrust
optimum control
relative reachable domain
