Vehicle-and-trajectory optimization of nuclear electric spacecraft for lunar missions
Vehicle-and-trajectory optimization of nuclear electric spacecraft for lunar missions
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DOI：
10.2514/3.26584
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发表时间：
1995
影响因子：
1.6
通讯作者：
C. Kluever;B. Pierson
中科院分区：
文献类型：
--
作者：
C. Kluever;B. Pierson
针对地月系统受限三体动力学控制的小推力核动力推进航天器，提出了一种新的运载器-轨道组合优化问题。该问题涉及计算最佳航天器尺寸参数和轨道设计变量，这些参数和变量导致从圆形低地球轨道到圆形低月球轨道的固定行程时间平面转移的最大有效载荷。特别地，计算了最佳比冲和输入功率。详细的飞行器和轨迹优化方法是有效的，在解决一个复杂的相互作用的问题，是重要的航天器和使命设计师。几个数值解得到了广泛的旅行时间。
A new combined vehicle-and-trajectory optimization problem is solved for a low-thrust nuclear-electricpropulsion spacecraft whose motion is governed by restricted three-body-problem dynamics for the Earth-moon system. The problem involves computing the optimal spacecraft sizing parameters and trajectory design variables that result in the maximum payload for a fixed-trip-time, planar transfer from circular low Earth orbit to circular low-lunar orbit. In particular, the optimal specific impulse and input power are computed. The detailed vehicleand-trajectory optimization approach is effective in solving a complex interactive problem that is important to both spacecraft and mission designers. Several numerical solutions are obtained for a wide range of trip times.