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A launch vehicle stability analysis using the parameter plane method

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1 Author(s)
S. Seltzer ; Marshall Space Flight Center, AL, USA

An attitude control system, which uses the acceleration vector attitude as the control variable, has been postulated for control of the first stage of a large space booster. The goal of this system is to minimize lateral drift. A stability analysis of this system based upon the parameter plane method is described.

Published in:

IEEE Transactions on Automatic Control  (Volume:15 ,  Issue: 5 )