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    Optimal Guidance for Lunar Module Soft Landing

    Access Status
    Fulltext not available
    Authors
    Zhou, Jingyang
    Teo, Kok Lay
    Zhou, D.
    Zhao, G.
    Date
    2010
    Type
    Journal Article
    
    Metadata
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    Citation
    Zhou, J.Y. and Teo, K.L. and Zhou, D. and Zhao, G.H. 2010. Optimal Guidance for Lunar Module Soft Landing. Nonlinear Dynamics and Systems Theory. 10 (2): pp. 189-201.
    Source Title
    Nonlinear Dynamics and systems theory
    ISSN
    15628353
    School
    Department of Mathematics and Statistics
    URI
    http://hdl.handle.net/20.500.11937/9905
    Collection
    • Curtin Research Publications
    Abstract

    In this paper, we consider an optimal control problem arising from the optimal guidance of a lunar module to achieving soft landing, where the description of the system dynamics is in a three-dimensional coordinate system. Our aim is to construct an optimal guidance law to realize the soft landing of the lunar module with the terminal attitude of the module to be within a small deviation from being vertical with respect to lunar surface, such that the fuel consumption and the terminal time are minimized. The optimal control problem is solved by applying the control parameterization technique and a time scaling transform. In this way, the optimal guidance law and the corresponding optimal descent trajectory are obtained. We then move on to consider an optimal trajectory tracking problem, where a desired trajectory is tracked such that the fuel consumption and the minimum time are minimized. This optimal tracking problem is solved using the same approach to the first optimal control problem. Numerical simulations demonstrate that the approach proposed is highly efficient.

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