基于发射约束的双曲线轨道运载能力计算方法研究

Research on Calculation of Carrying Capacity in Hyperbolic Orbit Missions based on Launch Constrains

为了解决深空探测任务规划中运载火箭发射轨道快速计算问题,基于双曲线轨道出发点与运载火箭发射弹道匹配存在约束的现状,研究了基于双曲线速度赤纬和发射能量计算火箭运载能力的匹配方法。提出了一种考虑射向和航落区约束下的无量纲运载能力折算关系,能够模拟实际发射可实现的最大运载能力,并可将其代入发射轨道全局优化。利用这一方法,分别对指定窗口发射任务进行了计算和分析,得到了各窗口中满足出发条件的轨道可行域范围和火箭能够实现的最大无量纲运载能力。结论表明,此方法能够有效用于双曲线轨道发射任务运载能力计算,可为任务规划提供充分的参考和帮助。

In order to solve the problem of fast-calculation of launch trajectory in deep space exploration mission planning,based on the fact that hyperbolic trajectory and launch trajectory are constrained,the matching method for calculating rocket carrying capacity based on hyperbolic velocity and declination and launch energy is studied.A conversion relationship of dimensionless carrying capacity considering launch azimuth and downrange is proposed,which can simulate the maximum carrying capacity achieved in actual launch and be substituted into global optimization.By this means,designated launch windows are calculated and analyzed.Feasible range of orbits in each window that satisfies departure conditions and the maximum dimensionless carrying capacity that rocket can achieve are obtained.Results show that the method proposed can be effectively used in carrying capacity calculation of hyperbolic orbit missions.It can provide sufficient reference and help for mission planning.