Open AccessRocket tracking and decoupling eigenstructure control law
Author(s) -
Patrizia Oliva,
Waldemar C. Leite Filho
Publication year - 2000
Publication title -
revista brasileira de ciências mecânicas
Language(s) - English
Resource type - Journals
ISSN - 0100-7386
DOI - 10.1590/s0100-73862000000200002
Subject(s) - control theory (sociology) , linearization , robustness (evolution) , decoupling (probability) , rocket (weapon) , attitude control , engineering , feedback linearization , euler angles , yaw , computer science , control engineering , aerospace engineering , nonlinear system , control (management) , mathematics , physics , artificial intelligence , biochemistry , chemistry , quantum mechanics , gene , geometry
A control law was designed for a satellite launcher ( rocket ) vehicle using eigenstructure assignment in order that the vehicle tracks a reference attitude and also to decouple the yaw response from roll and pitch manoeuvres and to decouple the pitch response from roll and yaw manoeuvres. The design was based on a complete linear coupled model obtained from the complete vehicle non linear model by linearization at each trajectory point. After all, the design was assessed with the vehicle time varying non-linear model showing a good performance and robustness. The used design method is explained and a case study for the Brazilian satellite launcher ( VLS Rocket ) is reported