Attitude Head Pursuit Transition Guidance Law

Abstract

As an improved guidance method, the attitude head pursuit guidance (AHPG) law enables the attitude pursuit guidance (APG) law to be more suited to transition guidance of air-to-ground missiles. By adding a head angle into the attitude angle of APG, AHPG directs the missile axis onto the line of sight (LOS). The maximum range trajectory simulation shows that the elevator deflection angle reaches the saturated value of 10° at the outset and the impact angle is less than 60° when APG is used as transition guidance law. However, the elevator deflection angle on the whole trajectory is reduced to under 5° and the impact angle increased to over 60° when AHPG is used. The formulae to calculate head angles are derived for different target distributions. The simulation of multiple trajectories shows that with the help of the formulae based on AHPG law, the same performance could be achieved.