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.
- Publication:
-
Final Report
- Pub Date:
- December 1979
- Bibcode:
- 1979aubu.reptQ....C
- Keywords:
-
- Attitude Stability;
- Missile Trajectories;
- Missile Vibration;
- Angular Velocity;
- Free Flight;
- Mathematical Models;
- Missile Control;
- Missile Launchers;
- Vibration Effects;
- Launch Vehicles and Space Vehicles