Accession Number:

ADA164019

Title:

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

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1985-12-01

Pagination or Media Count:

111.0

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

Subject Categories:

  • Surface-Launched Guided Missiles

Distribution Statement:

APPROVED FOR PUBLIC RELEASE