Gravity-Induced Angular Motion of a Spinning Missile

Abstract

The usual analysis of the steady state angular motion of a dynamically stable spinning missile assumes a quasi-steady state calculation of a gravity-induced trim angle. A condition for the validity of this quasi-steady state assumption is derived. When this condition is not satisfied, the gravity- induced angular motion must be described differently for three distinct portions of the trajectory: the upleg, near apogee, and the downleg. The accuracy of this description is checked by comparison with numerical integrations. Finally the influence of cubic static and Magnus moments on the motion is determined and a revised point mass trajectory model is constructed.

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Document Details

Document Type
Technical Report
Publication Date
Jul 01, 1971
Accession Number
AD0730641

Entities

People

  • Charles H. Murphy

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Aerodynamic Forces
  • Amplitude
  • Angular Motion
  • Cartesian Coordinates
  • Coefficients
  • Equations
  • Equations Of Motion
  • Flight
  • Flight Paths
  • Frequency
  • Numerical Integration
  • Orientation (Direction)
  • Projectiles
  • Steady State
  • Trajectories
  • Trim Angle

Fields of Study

  • Physics

Readers

  • Control Systems Engineering.