A numerically efficient method is proposed to produce high-performance suboptimal trajectories for maximizing terminal speed in long-range air-to-air missile engagements. Pursuit guidance is augmented by a linear lead-angle bias function and combined with homing guidance such as proportional navigation and impact-angle-control guidance to quickly generate a suboptimal trajectory very close to the optimal trajectory while satisfying terminal constraints. Numerical results for various engagement scenarios are provided to demonstrate the usefulness of the proposed method for real-time optimal midcourse guidance.


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    Titel :

    Suboptimal Guidance Based on Pursuit and Impact Angle Control for Long-Range Air-to-Air Missiles


    Beteiligte:
    Tahk, Min-Jea (Autor:in) / Park, Jong-Chan (Autor:in) / Roh, Heekun (Autor:in) / Lee, Chang-Hun (Autor:in)


    Erscheinungsdatum :

    18.07.2023


    Format / Umfang :

    655276 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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