Advanced guidance control system design for homing missiles with bearings-only measurements

A guidance control law for homing missiles with bearings-only measurements is presented. The law is chosen to be a proportional navigation one, but with an additional term in the control law to induce observability. The design preserves the simplicity of proportional navigation, and offers the ability to enhance the performance of a Kalman filter which is an integral part of the control. The closed form solutions of the differential equations describing the relative motion of missile-target systems under this guidance law are derived. Monte-Carlo simulations to study the system performance are performed.<
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