A Linear Quadratic Integral Design Approach for the Automatic Control System of a Launch Vehicle
2015 ◽
Vol 772
◽
pp. 410-417
◽
Keyword(s):
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.
2016 ◽
Vol 859
◽
pp. 116-123
2012 ◽
Vol 433-440
◽
pp. 7011-7016
◽
Keyword(s):
2021 ◽
Vol 39
(5)
◽
pp. 995-1004
1983 ◽
pp. 453-463
◽
Keyword(s):
1995 ◽
Vol 49
(3)
◽
pp. 335-353
◽
Keyword(s):