The Use of Solutions to Problems of Spacecraft Trajectory Optimization in Impulse Formulation when Solving the Problems of Optimal Control of Trajectories of a Spacecraft with Limited Thrust Engine: I

I. S. Grigoriev; K. G. Grigoriev

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The Use of Solutions to Problems of Spacecraft Trajectory Optimization in Impulse Formulation when Solving the Problems of Optimal Control of Trajectories of a Spacecraft with Limited Thrust Engine: I

机译：有限推力发动机航天器最优控制问题在冲量公式化中对航天器轨迹优化问题的求解：

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In this first part of our paper, it is suggested to use solutions to boundary value problems in the optimization problems (in impulse formulation) for spacecraft trajectories in order to obtain the initial approximation, when boundary value problems of the maximum principle are solved numerically by the shooting method. The technique suggested is applied to the problems of optimal control over motion of the center of mass of a spacecraft controlled by the thrust vector of jet engine with limited thrust in an arbitrary gravitational field in a vacuum. The method is based on a modified (in comparison to the classic scheme) shooting method computation together with the method of continuation along a parameter (maximum reactive acceleration, initial thrust-to-weight ratio, or any other parameter equivalent to them). This technique allows one to obtain the initial approximation with a high precision, and it is applicable to a wide range of optimal control problems solved using the maximum principle, if the impulse formulation makes sense for these problems.

机译：在本文的第一部分中，建议通过数值求解最大原理的边界值问题时，在航天器轨道的优化问题（以脉冲形式表示）中使用边界值问题的解，以获得初始近似值。射击方法。提出的技术被应用于在真空中任意重力场中由有限推力的喷气发动机推力矢量控制的航天器质心运动的最佳控制问题。该方法基于修改后的（与经典方案相比）射击方法计算以及沿着参数（最大反作用加速度，初始推力重量比或与其等效的任何其他参数）的连续方法。这种技术可以使人获得高精度的初始近似值，并且如果脉冲公式对这些问题有意义，则它适用于使用最大原理解决的各种最优控制问题。

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《Cosmic research》 |2007年第4期|339-347|共9页
作者
I. S. Grigoriev; K. G. Grigoriev;
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Faculty of Mechanics and Mathematics, Lomonosov Moscow State University, Vorob'evy gory, Moscow, 119899 Russia;

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正文语种 eng
中图分类航天（宇宙航行）;
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1. The Use of Solutions to Problems of Spacecraft Trajectory Optimization in Impulse Formulation when Solving the Problems of Optimal Control of Trajectories of a Spacecraft with Limited Thrust Engine: II [J] . I. S. Grigoriev, K. G. Grigoriev Cosmic research . 2007,第6期

机译：有限推力发动机航天器最优控制问题在冲量公式化中对航天器轨迹优化问题的求解：II
2. Construction of Optimum Controls and Trajectories of Motion of the Center of Masses of a Spacecraft Equipped with the Solar Sail and Low-Thrust Engine, Using Quaternions and Kustaanheimo-Stiefel Variables [J] . Ya. G. Sapunkov, Yu. N. Chelnokov Cosmic research . 2014,第6期

机译：使用四元数和Kustaanheimo-Stiefel变量构造配备太阳帆和低推力发动机的航天器质心的最佳控制和运动轨迹
3. Computation of Interplanetary Trajectories of Spacecrafts with Nuclear Rocket Engines of High-Limited Thrust [J] . A.M. Kharitonov Journal of automation and information sciences . 2009,第6期

机译：高推力核火箭发动机航天器行星际轨迹的计算
4. Thrust-limited optimal three-dimensional spacecraft trajectories [C] . Seid Hossein Pourtakdoust, Mir Abbas Jalali AIAA guidance, navigation and control conference . 1995

机译：推力有限的最佳三维航天器轨迹
5. Minimum fuel trajectories for low-thrust power-limited spacecraft. [D] . Golan, Oded M. 1990

机译：低推力功率限制的航天器的最小燃料轨迹。
6. An Automated Solution of the Low-Thrust Interplanetary Trajectory Problem [O] . Jacob A. Englander, Bruce A. Conway -1

机译：低推力行星际轨道问题的自动化解决方案
7. Spacecraft Trajectory Optimization Suite (STOpS): Optimization of Multiple Gravity Assist Spacecraft Trajectories Using Modern Optimization Techniques [O] . Timothy J. Fitzgerald -1

机译：航天器轨迹优化套件（停止）：使用现代优化技术优化多重重力辅助航天器轨迹
8. The Utilization of an Impulsive Solution in Solving Optimum Trajectory Problems with Bounded Thrust Magnitude [R] . Jezewski, D. J. 1967

机译：利用脉冲解法求解有界推力大小的最优轨迹问题

The Use of Solutions to Problems of Spacecraft Trajectory Optimization in Impulse Formulation when Solving the Problems of Optimal Control of Trajectories of a Spacecraft with Limited Thrust Engine: I

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