Finite-time H2 performance analysis considering target maneuvers and guidance loop dynamics

In this paper, the H 2 performance of the missile terminal guidance system that incorporates various target maneuvers is first studied over a finite horizon. A novel approach named finite-time generalized H 2 with initial conditions for a linear time-varying (LTV) system is adopted. Necessary and sufficient condition, which guarantees that the above mentioned performance measure is less than a prespecified value, is given in the form of Hermitian Riccati matrix differential equations (HRMDE). Finally, based on the new finite-time generalized H 2 metric, the interrelationship between various target maneuvers, guidance loop dynamics, and missile maximal acceleration is established. Also, the analysis and simulation results provide the feasible theoretical basis for the design of a missile terminal guidance system.