Abstract: The error characteristics of a state estimator are analyzed in the terminal guidance phase for highly maneuvering target interception. Firstly, the estimator’s model is expressed as a stochastic linear hybrid system with unknown maneuvering control input . When the mode jump event of the hybrid system is observable, mode decision results can be equivalent to the delayed true mode. Then the error dynamic equationand transfer function are derived when the mode decision delay exists. To achieve the guaranteed estimation performance, the upper boundary of mode decision delay and the lower boundary of mode sojourn time are derived. Finally, the results are corroborated through the typical interception of a fighter by an air-to-air missile. These results provide a theoretical basis for the estimator design of this class of hybrid systems.

Key words: state estimate, terminal guidance, maneuvering target interception, hybrid system, mode decision delay, mode mismatch