Among the bank-to-turn (BTT) missile guidance methods, a prevalent method is to get the acceleration command and roll-angle command through a polar converting logic (PCL) from the acceleration commands generated by skid-to-turn (STT) missile guidance. In the design of a BTT missile guidance law using a PCL, the controllability of the system should be particularly considered in the terms of the stability of roll motion. In the paper, the problems found in the BTT missile guidance are examined by applying a typical guidance law, i.e. proportional navigation (PN) guidance law, to a simple missile model. Then a biased proportional navigation (BPN) guidance law, which has an additional bias for angular constraints compared with PN, is introduced and applied to BTT missile guidance. The results from Monte-Carlo simulations for a 6 DOF missile model under several sensor noises show that BPN has better guidance performances for BTT missiles than the typical guidance law, PN.
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