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首页> 外文期刊>Transactions of the Japan society for aeronautical and space sciences >Study on Stationkeeping for Halo Orbits at EL_1: Dynamics Modeling and Controller Designing
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Study on Stationkeeping for Halo Orbits at EL_1: Dynamics Modeling and Controller Designing

机译：EL_1处晕轨道的定点研究：动力学建模和控制器设计

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This paper deals with the stationkeeping control for halo orbits at EL in the Sun-Earth/Moon system, and proposes an effective adaptive robust controller for the unknown spacecraft mass and perturbation boundaries. The controller has to deal with two divergence sources: one is the instability of the halo orbit, and the other is the perturbation imposed by the natural model onto the nominal model. The former source is displayed by the Floquet multiplier from the Poincare mapping. However, the latter is revealed by the difference of Hamiltonian functions between the nominal reference model, the circular restricted three-body problem (CR3BP) and the natural simulation model, the spatial bicircular model (SBCM). Firstly, the algorithm of backstepping control theory is employed to generate the initial controller in the nominal reference model of CR3BP. Some improvements are then implemented for the estimations of the unknown parameters as the perturbation boundaries and the spacecraft mass, which may cause the failure of the initial unimproved controller in stationkeeping. The controller proves to be effective in terms of adaptive robust estimation and asymptotic stability from Lyapunov's stability theory. Furthermore, further improvements of the triggers for the on/off schedule are proposed to remedy the weakness in the capability of estimating for excessively long (infinite) time required to converge. Finally, the controller developed in this paper is implemented in the natural simulation model of SBCM to evaluate its performance. In the numerical simulation, the mass and perturbation boundaries will converge only after approximately three iterations. The deviation of the estimating mass is 1 kg from its true mass, but 55 kg for the unimproved controller. The total velocity increment over five years is only 126 m/s, which is equivalent to the fuel consumption of 3.8 kg for the Hall thrust engine carried by SMART-1.
机译：本文讨论了太阳地球/月球系统中EL的晕圈的驻站控制，并针对未知的航天器质量和扰动边界提出了一种有效的自适应鲁棒控制器。控制器必须处理两个发散源：一个是光晕轨道的不稳定性，另一个是自然模型对标称模型施加的扰动。前一个源由Poincare映射中的Floquet乘法器显示。然而，后者是由名义参考模型，圆形受限三体问题（CR3BP）和自然模拟模型，空间双圆模型（SBCM）之间的汉密尔顿函数差异所揭示的。首先，采用反推控制理论的算法在CR3BP标称参考模型中生成初始控制器。然后对扰动边界和航天器质量进行未知参数估计的一些改进，这可能会导致初始未改进的控制器在站位维护中出现故障。根据Lyapunov的稳定性理论，该控制器在自适应鲁棒估计和渐近稳定性方面被证明是有效的。此外，提出了对开/关时间表的触发器的进一步改进，以弥补估计收敛所需的过长（无限）时间的能力的弱点。最后，本文开发的控制器在SBCM的自然仿真模型中实现，以评估其性能。在数值模拟中，质量和扰动边界将仅在大约三个迭代之后收敛。估计质量与其实际质量的偏差为1 kg，但对于未经改进的控制器，偏差为55 kg。五年中的总速度增量仅为126 m / s，相当于SMART-1携带的霍尔推力发动机的燃油消耗为3.8 kg。

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