Optimal Guidance for Accelerating Missiles

A new guidance law is derived for missiles that undergo significant axial accelerations. The guidance law solution follows the use of a more complete dynamic engagement model as a constraint in the two-point boundary value guidance problem together with a coordinate system formulation that is less restrictive geometrically. Past guidance laws were found to yield sub-optimal trajectories when applied to missiles in certain high acceleration engagements; for example surface-to-air engagement with a crossing target. Simulation results are included.