This chapter considers an engagement scenario consisting of a high value target (e.g., an aircraft), that on becoming aware that it is being attacked by a missile (attacker), fires a defending missile to engage and intercept this attacking missile and itself performs an evasive maneuver to escape the attacker. It explains some of the salient features of the three‐party differential game theory as they apply to the missile guidance problem. A 3‐D engagement kinematics model is developed and a solution to the guidance problem is obtained in terms of the matrix Riccati equation solution. The chapter also discusses ways in which additional inputs may be used in the guidance law to implement rule‐based artificial intelligence derived inputs to further enhance evasion and/or pursuit strategies by the parties.


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    Title :

    Three‐Party Differential Game Theory Applied to Missile Guidance Problem


    Contributors:


    Publication date :

    2017-04-25


    Size :

    23 pages




    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English







    Intelligent 3-Party Game Theoretic Approach to Missile Guidance

    Faruqi, F. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012