A Method of Damping Missile Structural Bending Modes for Autopilot Design

摘要

The method presented introduces a reasonable amount of linear damping into the structural modes of oscillation by means of an auxiliary feedback loop. It is that this auxiliary loop can generally be made stable and that the damping in the structural modes can generally be increased. The scheme does not depend critically on the bending resonance frequencies nor on the mode shape amplitude, slope, or node location.