Station-keeping strategies for halo orbits: A comparative study of target point approach and linear quadratic regulator in the Sun–Earth CRTBP

IF 1.6 4区 物理与天体物理 Q3 ASTRONOMY & ASTROPHYSICS
Jai Kumar, Manjiri Rane
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引用次数: 0

Abstract

Three-dimensional orbits near the interior Lagrange point (L1) of the Sun–Earth barycentre system are being considered for multiple missions. Trajectories at these Lagrange points are intrinsically unstable, necessitating spacecraft to utilize trajectory control to sustain proximity to their designated orbits. This research examines the station keeping of halo orbits around the Sun–Earth Lagrange point L1 within the circular-restricted three-body problem (CRTBP) utilizing two control strategies: target point approach (TPA) and linear quadratic regulator (LQR) methods. Halo orbits with out-of-plane amplitudes of 120,000, 150,000 and 250,000 km were generated using a differential correction method. Random initial errors in the state vector of the satellite were introduced to simulate realistic perturbations, and a genetic algorithm (GA) was applied to optimize maneuver intervals in the TPA. The TPA was tested with different numbers of future target points (2, 3, 4 and 5). Results from different simulations indicate that the TPA is more fuel-efficient for small perturbations, while the LQR approach is more effective for larger initial dispersions. Additionally, a transformation from the Sun–Earth barycentric frame to the Earth-centred J2000 inertial frame is established. These findings provide valuable insights for designing efficient station-keeping strategies that balance maneuver costs with mission longevity. This study offers a comprehensive strategy for maintaining spacecraft near the desired halo orbit trajectories.

日晕轨道保持策略:日地CRTBP中目标点逼近与线性二次型调节器的比较研究
太阳-地球质心系统内部拉格朗日点(L1)附近的三维轨道正被考虑用于多个任务。这些拉格朗日点上的轨迹本质上是不稳定的,这就要求航天器利用轨迹控制来维持其接近指定轨道的状态。本文研究了在圆约束三体问题(CRTBP)下,利用目标点法(TPA)和线性二次型调节器(LQR)两种控制策略对日地拉格朗日点L1的日晕轨道保持问题。光晕轨道的面外振幅分别为12万、15万和25万公里。引入卫星状态向量的随机初始误差来模拟实际扰动,并采用遗传算法优化TPA中的机动间隔。TPA以不同数量的未来目标点(2、3、4和5)进行测试。不同的模拟结果表明,TPA方法对于较小的扰动更省油,而LQR方法对于较大的初始分散更有效。此外,建立了从太阳-地球重心坐标系到以地球为中心的J2000惯性坐标系的转换。这些发现为设计平衡机动成本和任务寿命的有效空间站保持策略提供了有价值的见解。这项研究提供了一个全面的策略,以保持航天器接近所需的光晕轨道轨迹。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
Journal of Astrophysics and Astronomy
Journal of Astrophysics and Astronomy 地学天文-天文与天体物理
CiteScore
1.80
自引率
9.10%
发文量
84
审稿时长
>12 weeks
期刊介绍: The journal publishes original research papers on all aspects of astrophysics and astronomy, including instrumentation, laboratory astrophysics, and cosmology. Critical reviews of topical fields are also published. Articles submitted as letters will be considered.
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