A METHOD OF DAMPING MISSILE STRUCTURAL BENDING MODES FOR AUTOPILOT DESIGN,

Abstract

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.

Document Details

Document Type
Technical Report
Publication Date
May 18, 1959
Accession Number
AD0609020

Entities

People

  • Kenneth L. Miller
  • Lawrence E. Freed

Organizations

  • TRW Inc.

Tags

DTIC Thesaurus Topics

  • Amplitude
  • Automatic Pilots
  • Feedback
  • Frequency
  • Motion
  • Oscillation
  • Resonance
  • Resonant Frequency

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.