Abstract
This study addresses the design of cooperative guidance laws for interceptor missiles. A polyhedric bounded-error estimation of the target position is employed, based only on the assumption that the target acceleration and measurement noise remain within known bounds. This prediction of the maneuvering target trajectory is then incorporated into a model predictive control scheme to derive the missile guidance law. The cases of both single and multiple targets are investigated. Simulation results are presented to illustrate the proposed approach.
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