Effect of Horizontal and Vertical Side Forces and Moments on Stability of a Symmetric Missile in Ascending or Descending Flight

Abstract

Lloyd and Brown have shown that constant horizontal and vertical side forces and moments applied to a spinning projectile can result in dynamic instability. This instability arises from the nonlinear terms in the fixed-plane coordinate system spin that appear in the equations of motion. By quasilinearization, these nonlinear terms are shown to affect the frequencies slightly but the damping rates not at all. By the use of the fixed-plane system (rather than Lloyd and Brown's nonrolling system) simpler relations can be developed, the full effects of gravity, drag and roll damping obtained and the limitation to large gyroscopic stability factors removed. Very simple stability bounds are given for a slowly spinning or nonspinning finned missile such as Copperhead.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1979
Accession Number
ADA072808

Entities

People

  • Charles H. Murphy

Organizations

  • Ballistic Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautical Engineering
  • Aeronautics
  • Complex Variables
  • Conductive Polymers
  • Coordinate Systems
  • Differential Equations
  • Engineering
  • Equations
  • Equations Of Motion
  • Flight
  • Frequency
  • Jet Propulsion
  • Military Research
  • Molecular Dynamics
  • Physics Laboratories
  • Projectiles
  • Steady State

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Control Systems Engineering.