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Formulation of the Optimal Trajectory for an Air-Breathing Medium Range Air-to-Air Missile.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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The Air Breathing Medium Range Air-to-Air Missile ABMRAAM represents developmental technology which incorporates both a rocket engine and a RAMJET engine. Such a missile uses proportional navigation guidance plus an additional trajectory loft command. This thesis examines the optimal trajectory, and hence the optimal lofting command, for an ABMRAAM. A numerical simulation of the missile is presented and the necessary conditions for the optimal trajectory are derived. From these conditions, the problem can be numerically solved for the optimal loft command.
APPROVED FOR PUBLIC RELEASE