Abstract
In this paper, the H2 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 H2 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 H2 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.
Published Version
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