Ocampo Cesar
Department of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin, Austin, TX 78712, USA.
Ann N Y Acad Sci. 2004 May;1017:210-33. doi: 10.1196/annals.1311.013.
The modeling, design, and optimization of finite burn maneuvers for a generalized trajectory design and optimization system is presented. A generalized trajectory design and optimization system is a system that uses a single unified framework that facilitates the modeling and optimization of complex spacecraft trajectories that may operate in complex gravitational force fields, use multiple propulsion systems, and involve multiple spacecraft. The modeling and optimization issues associated with the use of controlled engine burn maneuvers of finite thrust magnitude and duration are presented in the context of designing and optimizing a wide class of finite thrust trajectories. Optimal control theory is used examine the optimization of these maneuvers in arbitrary force fields that are generally position, velocity, mass, and are time dependent. The associated numerical methods used to obtain these solutions involve either, the solution to a system of nonlinear equations, an explicit parameter optimization method, or a hybrid parameter optimization that combines certain aspects of both. The theoretical and numerical methods presented here have been implemented in copernicus, a prototype trajectory design and optimization system under development at the University of Texas at Austin.
本文介绍了用于广义轨迹设计与优化系统的有限冲量机动的建模、设计和优化。广义轨迹设计与优化系统是一种使用单一统一框架的系统，该框架有助于对可能在复杂引力场中运行、使用多种推进系统并涉及多个航天器的复杂航天器轨迹进行建模和优化。在设计和优化一大类有限推力轨迹的背景下，介绍了与使用有限推力大小和持续时间的可控发动机冲量机动相关的建模和优化问题。最优控制理论用于研究在通常与位置、速度、质量和时间相关的任意力场中这些机动的优化。用于获得这些解的相关数值方法包括求解非线性方程组、显式参数优化方法或结合两者某些方面的混合参数优化。这里介绍的理论和数值方法已在哥白尼系统中实现，哥白尼是德克萨斯大学奥斯汀分校正在开发的一个轨迹设计与优化系统原型。
