SUB-OPTIMAL MISSILE GUIDANCE WITH PULSEMOTOR CONTROL LOGIC USING THE SINGULAR PERTURBATIONS METHOD

摘要

A planar non-linear missile guidance problem isrnstudied and a guidance method is proposed. Thernsolution includes finding the accelerationrncommands (guidance commands) andrncontrolling ignition timing for a dual pulsernrocket motor. A near optimal solution using thernsingular perturbations method for a switchedrnsystem is used. This solution method results in arnsimple to implement analytic solution to thernproblem. In order to solve this problem, a newrncondition in the minimum principle was derived.rnThe condition regards switched systems withrnsystem equations dependent on the switchingrntime. During the solution, a modified rocketrnequation to include drag was developed.