An Analysis of the Effects of Transverse Vibration on the Attitude Motion of Free-Flight Rockets.
Final rept. 15 Dec 78-15 Dec 79,
AUBURN UNIV ALA DEPT OF AEROSPACE ENGINEERING
Pagination or Media Count:
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.