High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration

James R. Scott; Michael C. Martini

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High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration

机译：使用泰勒级数积分的航天器轨迹问题的高速解决方案

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InT HAS been known for some time that Taylor series (TS)nintegration is among the most efﬁcient and accurate numericalnmethods in solving differential equations. However, the full beneﬁtnof the method has yet to be realized in calculating spacecraftntrajectories, for two main reasons. First, most applications of Taylornseries to trajectory propagation have focused on relatively simplenproblems of orbital motion or on speciﬁc problems and have notnprovided general applicability. Second, applications that have beennmore general have required use of a preprocessor, which inevitablynimposes constraints on computational efﬁciency. The latter approachnincludes the work of Berryman et al. [1], who solved the planetarynn-body problem with relativistic effects. Their work speciﬁcallynnoted the computational inefﬁciencies arising from use of a prepro-ncessor and pointed out the potential beneﬁt of manually codingnderivative routines.

机译：InT一直以来都知道泰勒级数（TS）积分是求解微分方程式最有效，最准确的数值方法之一。然而，由于两个主要原因，该方法的全部优点尚未在计算航天器轨道中实现。首先，泰勒级数在轨道传播中的大多数应用都集中在相对较简单的轨道运动问题或特定问题上，而没有提供一般的适用性。其次，更普遍的应用程序需要使用预处理程序，这不可避免地对计算效率施加了约束。后一种方法包括Berryman等人的工作。 [1]，他以相对论效应解决了Planetarynn体问题。他们的工作专门指出了使用前置处理器会导致计算效率低下，并指出了手动编码衍生例程的潜在好处。

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《Journal of Spacecraft and Rockets》 |2010年第1期|p.199-202|共4页
作者
James R. Scott; Michael C. Martini;
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作者单位

NASA John H. Glenn Research Center at Lewis Field,Cleveland, Ohio 44135;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
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1. High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration [J] . James R. Scott, Michael C. Martini Journal of Spacecraft and Rockets . 2010,第1期

机译：使用泰勒级数积分的航天器轨迹问题的高速解决方案
2. Rapid Calculation of Spacecraft Trajectories Using Efficient Taylor Series Integration [J] . NASA Tech Briefs . 2011,第1期

机译：利用有效的泰勒级数积分快速计算航天器的轨迹
3. 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
4. High Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration [C] . J. Scott, M. Martini AIAA guidance, navigation and control conference and exhibit . 2008

机译：使用泰勒级数积分的航天器轨迹问题的高速解决方案
5. A new numerical optimization method based on taylor series for challenging trajectory optimization problems [D] . Martin, Christopher Scott 2011

机译：基于泰勒级数的求解轨迹优化问题的数值优化新方法。
6. Semi-Analytic Solution and Stability of a Space Truss Using a High-Order Taylor Series Method [O] . Sudeok Shon, Seungjae Lee, Junhong Ha, 2015

机译：高阶泰勒级数法的空间桁架半解析解和稳定性
7. High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration [O] . Scott James R., Martini Michael C. 2010

机译：使用泰勒级数积分的航天器轨迹问题的高速解决方案
8. High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration [R] . Scott, J. R., Martini, M. C. 2010

机译：利用泰勒级数积分高速解决航天器弹道问题

High-Speed Solution of Spacecraft Trajectory Problems Using Taylor Series Integration

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