Title :
A launch vehicle stability analysis using the parameter plane method
Author_Institution :
Marshall Space Flight Center, AL, USA
fDate :
10/1/1970 12:00:00 AM
Abstract :
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.
Keywords :
Space-vehicle launching; Acceleration; Control systems; Differential equations; Engines; Feedback control; Geometry; Shape; Space vehicles; Stability analysis; System analysis and design;
Journal_Title :
Automatic Control, IEEE Transactions on
DOI :
10.1109/TAC.1970.1099552
