An Analysis of the Effects of Transverse Vibration on the Attitude Motion of Free-Flight Rockets.

Abstract

The results of an analysis of the effects of transverse vibration of a spinning, flexible, free-flight rocket during its guidance phase on its attitude motion subsequent to end of guidance (EOG) are presented. Two models of a spinning, flexible, free-flight rocket are described. One is a simple two-body model. The other is a 'continuous' model. A physical explanation is given for the way transverse vibration during the guidance phase causes the appearance of a transverse angular rate at EOG. The two-body model is used to obtain a simple equation from which estimates of the transverse angular rate can be found. Typical results from the two models are presented and agreement between the results is shown.

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Document Details

Document Type
Technical Report
Publication Date
Dec 14, 1979
Accession Number
ADA080606

Entities

People

  • Grant A. Castleberry
  • John E. Cochran Jr.
  • Stephen D. Rew

Organizations

  • Auburn University

Tags

DTIC Thesaurus Topics

  • Angular Momentum
  • Clearances
  • Computational Science
  • Computers
  • Equations
  • Equations Of Motion
  • Exhaust Gases
  • Free Flight
  • Frequency
  • Mathematical Models
  • Molecular Dynamics
  • Moment Of Inertia
  • Momentum
  • Orientation (Direction)
  • Rocket Engines
  • Rocket Models
  • Thrust

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Molecular Photonics/Laser Physics
  • Robotics and Automation.