Indirect Spacecraft Trajectory Optimization Using Modiﬁed Equinoctial Elements

Hongzhao Liu and Benson H. Tongue

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Indirect Spacecraft Trajectory Optimization Using Modiﬁed Equinoctial Elements

机译：修正等值元素的间接航天器弹道优化

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SEVERAL different types of orbital elements have been used overnthe years for spacecraft trajectory design. Four frequently usednorbital elements are Cartesian elements (CE), Keplerian elementsn(KE), equinoctial elements (EE), and modiﬁed equinoctial elementsn(MEE), the details of which are given in [1]. CE-based equations arensingularity free but are computationally difﬁcult to solve;KE and EEnequations can be solved efﬁciently but have singularities at anninclination or eccentricity of 0 (KE equations) or an eccentricity of 1n(EE equations).

机译：多年来，航天器轨迹设计中使用了几种不同类型的轨道元素。四个经常使用的轨道元素是笛卡尔元素（CE），开普勒元素n（KE），等量元素（EE）和修饰的等量元素n（MEE），其详细信息在[1]中给出。基于CE的方程没有奇异性，但在计算上难以解决； KE和EEnequations可以有效地求解，但在零偏角或偏心率为0（KE方程）或偏心率为1n（EE方程）时具有奇异性。

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《Journal of Guidance, Control, and Dynamics》 |2010年第2期|p.619-622|共4页
作者
Hongzhao Liu and Benson H. Tongue;
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University of California at Berkeley,Berkeley, California 94720-1740;

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1. Indirect Spacecraft Trajectory Optimization Using Modified Equinoctial Elements [J] . Hongzhao Liu, Benson H. Tongue Journal of guidance, control, and dynamics . 2010,第2期

机译：修正等值元素的间接航天器弹道优化
2. 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
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: I [J] . I. S. Grigoriev, K. G. Grigoriev Cosmic research . 2007,第4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：
4. MODELING PERTURBATIONS AND OPERATIONAL CONSIDERATIONS WHEN USING INDIRECT OPTIMIZATION WITH EQUINOTICAL ELEMENTS [C] . Andrew S. Feistel, Christopher L. RanieM AAS/AIAA space flight mechanics meeting . 2009

机译：当使用等值单元的间接优化时，对摄动和操作注意事项进行建模
5. Reducing spacecraft state uncertainty through indirect trajectory optimization. [D] . Zimmer, Scott Jason. 2005

机译：通过间接轨迹优化减少航天器状态不确定性。
6. Uncertainty-based Optimization Algorithms in Designing Fractionated Spacecraft [O] . Xin Ning, Jianping Yuan, Xiaokui Yue -1

机译：分馏航天器设计中基于不确定度的优化算法
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

Indirect Spacecraft Trajectory Optimization Using Modiﬁed Equinoctial Elements

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