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.
An Analysis of the Effects of Transverse Vibration on the Attitude Motion of Free-Flight Rockets
1979
103 pages
Report
No indication
English
Lateral Motion of Free-Rolling Tail Rockets in Free Flight
Online Contents | 2005
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