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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。
Under certain fuel conditions, it is very important to study the relative accessibility of satellite orbits under continuous thrust. Through the analysis of the dynamic model, the calculation of relative reachable area is transformed into solving the optimal control problem. By analyzing the optimization model, the solution of the optimal control problem is finally transformed into the solution of linear differential equations. The method of determining the relative reachable area of satellite orbit is given. The relative reachable area of satellites with different fuel and time constraints is calculated, simulated and analyzed, and the corresponding variation rules are given.