A Computing based Simulation Model for Missile Guidance in Planar Domain

This paper presents the design, development and implementation of a computing based simulation model for interceptor missile guidance for countering an anti-ship missile through a navigation law. It investigates the possibility of deriving, testing and implementing an efficient variation of the PN and RPN laws. A new guidance law [true combined proportional navigation (TCPN) guidance law] that combines the strengths of both the PN and RPN and has a superior capturability in a specified zone of interest is presented in this paper. The presented proportional navigation (PN) guidance law is modeled in a two dimensional planar engagement model and its performance is studied with respect to a varying navigation ratio (N) that is dependent on the ‘heading error (HE)’ and missile lead angle. The advantage of varying navigation ratio is: if N′ > 2, V c > 0, V m > 0, then the sign of navigation ratio is determined by cos (ε + HE) and for cos (ε + HE) ≥ 0 and N > 0, the formulation reduces to that of PN and for cos (ε + HE)