Trajectory and Correction Maneuver During the Transfer from Earth to Halo Orbit

This article addresses the design of the trajectory transferring fi'om Earth to Halo orbit,and proposes a timing closed-loop strategy of correction maneuver during the trausfer in the frame of circular restricted three body problem (CR3BP).The relation between the Floquet multipliers and the magnitudes of Halo orbit is established,so that the suitable magnitude for the aerospace mission is chosen in previous researches,and six types of single-impulse transfer trajectories are attained from the geometry of the invariant manifolds.Based on one of the trajectories of indirect transfer which arc ignored in the most of literatures,the stochastic control theory for imperfect information of the discrete linear stochastic system is applied to design the trajectory correction maneuver.The statistical dispersion analysis is performed by Monte-Carlo simulation.

作 者： Xu Ming Xu Shijie   作者單位： School of Astronautics,Beifing University of Aeronautics and Astronautics,Beijing 100083,China  刊 名： 中國航空學(xué)報(bào)（英文版）  ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS  年，卷(期)： 2008 21(3)  分類號： V2  關(guān)鍵詞： libration point   Halo orbit   orbit design   trajectory correction maneuver   stochastic control theory   Monte-Carlo simulation  

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