A new impact angle control guidance law is introduced for a homing missile system equipped with a passive seeker against a stationary or slowly moving target. The proposed guidance law provides sufficient trajectory modulations, such as oscillatory trajectories, to enhance target observability from angle-only measurements. The derivation of the guidance command is based on the time-to-go polynomial guidance (TPG) law, which is one of the impact angle control laws. Closed-form solutions of the proposed law and their characteristics are investigated. The results inspired the proposed practical time-to-go calculation method and the maximum bounds of guidance gains, which are important for the practical implementation of the guidance law. Linear and nonlinear simulations with a target tracking filter are performed to investigate the performance of the proposed law.


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    Title :

    Time-to-go Polynomial Guidance with Trajectory Modulation for Observability Enhancement


    Contributors:
    Tae-Hun Kim (author) / Chang-Hun Lee (author) / Min-Jea Tahk (author)


    Publication date :

    2013-01-01


    Size :

    7036072 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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