Attitude control of a small conventional launcher

Author

Amato, F. ; Ambrosino, G. ; Filippone, E. ; Iervolino, R.

Author_Institution

Dipt. di Informatica, Matematica, Elettronica e Trasporti, Universita degli Studi Mediterranea di Reggio Calabria, Italy

Volume

1

fYear

2002

fDate

2002

Firstpage

284

Abstract

In this paper the attitude control problem for the small launch vehicle VEGA is discussed. In particular, a direct optimisation method is applied to the determination of the parameters of a prescribed mission trajectory, in order to compute a reference pitch attitude angle time history. The attitude and engine-thrusters control system, which allows to track the obtained reference attitude, are designed by using a fuzzy logic approach. The effectiveness of the proposed method is illustrated via simulation performed into the MATLAB™/SIMULINK™ environment.

Keywords

attitude control; fuzzy control; optimal control; space vehicles; MATLAB; SIMULINK; VEGA; attitude control; attitude control system; direct optimisation method; engine-thrusters control system; fuzzy logic; launcher; mission trajectory; reference attitude tracking; reference pitch attitude angle time history; Attitude control; Control systems; Force control; Fuzzy logic; Motion control; Optimal control; Space technology; Torque control; Vehicles; Velocity control;

fLanguage

English

Publisher

ieee

Conference_Titel

Control Applications, 2002. Proceedings of the 2002 International Conference on

Print_ISBN

0-7803-7386-3

Type

conf

DOI

10.1109/CCA.2002.1040199

Filename

1040199