%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@archivingpolicy denypublisher denyfinaldraft12
%3 15397730601044853.pdf
%X Nowadays, attitude control systems (ACS) of satellites demand better performance, resulting in the application of new advanced nonlinear control theory. In this paper, a nonlinear control law for a satellite attitude control is presented. It is based on an extension of the linear quadratic regulator (LQR) theory. The control law designed by this technique comprehends two parts: the first one based on the linear equations of motion and the second one based on the nonlinear equations of motion. From simulations, one observes that the extension of the LQR theory has improved the control system performance.
%T Design of satellite control system using optimal nonlinear theory
%@electronicmailaddress gadelha@dem.inpe.br
%K nonlinear theory, satellite attitude control.
%@secondarytype PRE PI
%@usergroup administrator
%@usergroup jefferson
%@group DMC-INPE-MCT-BR
%F 10083
%@issn 1539-7734
%@issn 1539-7742
%2 sid.inpe.br/mtc-m05@80/2008/06.17.15.30.13
%B Mechanics Based Design of Structure and Machines
%@versiontype publisher
%P 351-364
%4 sid.inpe.br/mtc-m05@80/2008/06.17.15.30
%@documentstage not transferred
%D 2006
%V 34
%@doi 10.1080/15397730601044853
%A Souza, Luiz Carlos Gadelha de,
%@dissemination PORTALCAPES
%@area ETES