Control Aspects of the Launch Phase of a Vertically-Launched Short-Range Surface-to-Air Missile

摘要

A two dimensional mathematical model of a thrust vector controlled, vertically-launched missile suitable for use in a computer simulation is described. The program is written in FORTRAN 4 to run on the DEC-20 digital computer. The results obtained from this model are used to discover the design features necessary in a control system to make such a missile assume a horizontal trajectory. An autopilot is designed using classical methods to control the pitch attitude of the missile. The use of bang-bang rather than proportional control in the pitch autopilot loop is also investigated. A means of estimating the flight path angle from the pitch attitude is derived to allow control of flight path angle. The velocity control autopilot incorporating this estimator is examined as to the accuracy of the estimator and the retardation experienced during turning. Improvements on the original design are made. Slew rate limitation, gain scheduling, and incidence limitation are introduced.