Stability of Spinning ICBM (Intercontinental Ballistic Missile) in First Stage Boost Phase.

Abstract

A computer program is developed to model a spinning intercontinental Ballistic Missile (IICBM) during the first stage boost phase. The equations of motion are derived and presented and a full rotation matrix is used to show the relationship between a launch-centered, nonrotating earth inertial reference frame and the missile body reference frame. The moments of inertia and aerodynamic forces are derived and presented. A feedback controller is derived which proved to be a necessary additiion to the system in order to reduce the angle of attack. The angle of attack of the missile produced adverse effects on the burnout vector without the feedback controller but the effects are reduced considerably with the controller included. Problem areas include possibly excessive nozzle gimbal rates caused by the feedback controller and the need to change the initial kick angle if the missile is spinning in order to achieve the same burnout conditions as a nonspinning missile. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1985
Accession Number
ADA164019

Entities

People

  • Robert W. Bandstra

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Air Force
  • Angular Momentum
  • Ascent Trajectories
  • Ballistic Missiles
  • Boost Phase
  • Computer Programs
  • Computer Simulations
  • Computers
  • Control Systems
  • Differential Equations
  • Engineering
  • Equations
  • Equations Of Motion
  • Intercontinental Ballistic Missiles
  • Moment Of Inertia
  • War Colleges

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Inertial Navigation Systems.
  • Rocket Propulsion.