Demonstration of the Dynamic Flowgraph Methodology using the Titan II Space Launch Vehicle Digital Flight Control System

1995 ◽  
Vol 49 (3) ◽  
pp. 335-353 ◽  
Author(s):  
M. Yau ◽  
S. Guarro ◽  
G. Apostolakis
Keyword(s):  
Control System ◽  
Flight Control ◽  
Launch Vehicle ◽  
Flight Control System ◽  
Space Launch

A Linear Quadratic Integral Design Approach for the Automatic Control System of a Launch Vehicle

2015 ◽  
Vol 772 ◽  
pp. 410-417 ◽  
Author(s):  
Adrian Mihail Stoica ◽  
Cristian Emil Constantinescu ◽  
Silvia Nechita
Keyword(s):  
Control System ◽  
Flight Control ◽  
Launch Vehicle ◽  
Design Approach ◽  
Flight Control System ◽  
Linear Quadratic ◽  
Atmospheric Disturbances ◽  
Modeling Uncertainties ◽  
Quadratic Integral ◽  
The Stability

This paper presents a design approach for the automatic flight control system of a launch vehicle using a linear quadratic integral technique together with a fixed gain Kalman filter. Its purpose is to analyse the stability and tracking robustness performances of the control system designed via this approach when atmospheric disturbances, modeling uncertainties and structural flexible modes of the launcher are taken into account.

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