This chapter considers the case where the attacking missile may be required to perform both evasion and intercept maneuvers during the engagement. Three‐party evasion and intercept guidance are derived using differential game theory for 3‐D engagements using the 4‐DOF simulation model. Kinematics models are developed and a solution to the problem is obtained in terms of the Riccati differential equations, which admit a wide choice of performance index (PI) weightings. Preliminary simulation results are included in order to demonstrate the characteristics of intercept and evasion strategies of the parties. Simple (rule‐based) artificial intelligence‐based avoidance strategies are also implemented for enhancing evasion by the aircraft target and for intercept by the attacking missile. The chapter also discusses the results of the differential game‐based guidance simulation obtained via the MATLAB‐based simulation program.
Three‐Party Differential Game Missile Guidance Simulation Study
2017-04-25
38 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
Intelligent 3-Party Game Theoretic Approach to Missile Guidance
British Library Conference Proceedings | 2012
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