Optimization of low-thrust interplanetary trajectories using collocation and nonlinear programming
Optimization of low-thrust interplanetary trajectories using collocation and nonlinear programming
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DOI：
10.2514/3.21429
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发表时间：
1995
影响因子：
2.6
通讯作者：
Sean Tang;B. Conway
中科院分区：
文献类型：
--
作者：
Sean Tang;B. Conway
本文将配点法与非线性规划相结合，用于确定最短时间、小推力的行星际转移轨道。由于飞行器发动机连续工作，最小时间轨迹也是推进剂最小化。数值解方法要求转移分为三个阶段：逃离出发行星、日心飞行和到达目的地行星。在每个阶段中使用两体引力模型，并将从行星中心坐标到日心坐标的转换，反之亦然，作为一组对问题变量的非线性约束。不需要对最优控制时间历程进行先验假设。以0.0001 g的极低推力加速度的地球-火星转移为例。
The method of collocation with nonlinear programming is applied to the determination of minimum-time, low-thrust interplanetary transfer trajectories. Since the vehicle motor operates continuously, the minimum-time trajectories are also propellant minimizing. The numerical solution method requires that the transfer be divided into three phases: escape from the departure planet, heliocentric flight, and arrival at the destination planet. Two-body gravitational models are used in each phase and the transformation from planetocentric coordinates to heliocentric coordinates and vice-versa is incorporated as a set of nonlinear constraints on the problem variables. No a priori assumptions on the optimal control time history are required. An Earth-to-Mars transfer with a very low thrust acceleration of 0.0001 g is used as an example.