A new guidance law with terminal angle constraint is presented for the midcourse guidance of anti-hypersonic missiles, thus to realize a near head-on scenario at the start of terminal phase. The proposed differentiator-based outputfeedback sliding mode guidance law is derived from supertwistbased differentiator and prescribed convergence law for secondorder sliding mode controller. Considering nonlinear dynamics of planar engagement, relative range and its derivative, line-of-sight angle and a guess of maximum target maneuverability is required for the implementation of new guidance law, information can always be available through data link from ground-based or air-based platforms. Fast convergence of line-of-sight angular rate as well as flight path angle can be expected. Simulation results validate the effectiveness of new guidance law against various target maneuvers and also illustrate the superiority when compared to conventional guidance laws.


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    Title :

    Differentiator-Based Output-Feedback SlidingMode Control for Angle Constrained Midcourse Guidance


    Contributors:
    Wan, Shizheng (author) / Chang, Xiaofei (author) / Yan, Jie (author)


    Publication date :

    2018-07-01


    Size :

    5206017 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English



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