Abstract: A modified proportional navigation (PN) guidance law is designed for nose jet control exoatmospheric missiles, which guarantees zero miss distance even if there are uncertainties in the direction and magnitude of the target’s acceleration. Unlike traditional PN guidance laws, for the modified PN guidance law, a deviation elimination term is added and the PN gain is time-varying. Additionally, to deal with non-ideal interception scenarios, a transition guidance law is designed. After a finite time of implementing the transition guidance law, kinematic variables converge to be suitable for implementation of the modified PN guidance law. Simulation study are conducted to verify the feasibility of the proposed algorithm.

Key words: exoatmospheric missile, proportional navigation (PN) guidance law, nose jet control (NCJ)