Extension of Proportional Navigation by the Use of Optimal Filtering and Control Methods

摘要

A suboptimal guidance law for homing missiles, based on quadratic optimal stochastic control theory is investigated. On-line backward integration from final time to actual time is not required. A Kalman-Bucy filter which takes nonlinearity and target maneuvers into account is presented. The model is compared to the conventional and extended proportional navigation systems (simulated on a nonlinear quidance loop model). Positional error behavior improves by 45%.