Non-linear state feedback control for near optimal intercept in three dimensions

The paper describes the development of an analysis tool to obtain missile performance data for optimal implementation of aerodynamic and thrust magnitude controllable missiles. The objective is to establish which motor type and aerodynamic configuration is best suited to any one of several Air Force missions. Optimal control solutions are derived to define the guidance and thrust magnitude control for air-launched tactical rockets. Constraints such as maximum lift coefficient, maximum load factor, and minimum and maximum velocity and thrust are enforced. The control solutions are non-linear and in a feedback form suitable for on-board implementation. Numerical results from a simulation study are presented which validate the operation of the control solutions.