On Incomplete State Feedback Design of Missile Autopilot in Pitch Plane

摘要

A pole-placement method for designing a linear missile autopilot system for a class of tail-controlled cruciform missiles is presented in this article. A procedure for the choke of proper closed-loop pole locations has been proposed which assures desired transient performance. Developed pole-placement formulae are simple and can provide fast and stable acceleration in pitch plane. A forward path gain is introduced to ensure accurate tracking without any steady-state error for a step input. Also, some control over the missile body-rate, peak fin deflection and fin-rate can be achieved for specified stability margins. An incomplete state feedback controller has been designed to eliminate the need for an observer system. The design enables to achieve desired stability margins with different speed of responses and the capabilities of hardware resources might be utilised by a judicious choice of autopilot speed of response (GCF). A numerical example illustrates the effectiveness of the developed methodology.