학술논문
Attitude control of a small conventional launcher
Document Type
Conference
Author
Source
Proceedings of the International Conference on Control Applications Control applications Control Applications, 2002. Proceedings of the 2002 International Conference on. 1:284-289 vol.1 2002
Subject
Language
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/spl trade//SIMULINK/spl trade/ environment.