DocumentCode
804305
Title
A launch vehicle stability analysis using the parameter plane method
Author
Seltzer, S.
Author_Institution
Marshall Space Flight Center, AL, USA
Volume
15
Issue
5
fYear
1970
fDate
10/1/1970 12:00:00 AM
Firstpage
611
Lastpage
612
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;
fLanguage
English
Journal_Title
Automatic Control, IEEE Transactions on
Publisher
ieee
ISSN
0018-9286
Type
jour
DOI
10.1109/TAC.1970.1099552
Filename
1099552
Link To Document