Missile guidance algorithm against high-g barrel roll maneuvers

Abstract

The features of high-# barrel rolls for an aircraft and the countermeasures for a proportional navigation guidance missile against this maneuver are studied. First, the features of the barrell roll maneuver, and the effects of the parameters on the miss distance are discussed. The simulation results show that a high-£ barrel roll maneuver generally produces a larger miss distance than a split-S (a sustained maximum g turn) and the miss distance does not critically depend on the maneuver initiation time, if the aircraft has a certain length of time-to-go and maneuvers with an appropriate roll rate. Second, the inference is made that the provision of a phase lead in the pitch-yaw plane in the missile guidance loop and adoption of the augmented proportional navigation guidance may be effective. It is also proven that a large phase shift (but less than ir/2) results in a smaller miss distance and that the combination of the phase lead and the augmented proportional navigation produces better results.