Abstract
In this paper, a new hybrid guidance law was presented based on the phased mixing of the proportional navigation (PN) and differential geometry (DG) guidance laws during the missile's flight stages to be able to deal with maneuvering targets, especially when obtaining noisy target and missile measurements. This hybrid guidance law was introduced through a guidance system that has a multi-sensor navigation system with different optimal skew redundant inertial measurement units' (SRIMU) configurations that increase the robustness of the guidance system. The robust guidance system is evaluated through the six degrees of freedom (DOF) simulation model.
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