%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%X This work discusses and simulates the discrete time control of an assymetric satellite with a large flexible appendage (with a single vibration mode) in the three attitude axis: roll, pitch and yaw- The model of the satellite was done by assumed modes method and in the simulations we considered disturbing effects as the atmosferic drag, the solar pressure radiation, and others. We used a Fuzzy-LQR control applied to each attitude axis and we comparing its performance with the usual Proportional plus Derivative discrete by Bilinear (PDB). These simulations were done in the same computational environment and the samplig time was Ts = 0.01 seconds, and we used the MatLab/Simulink software.
%E Winter, Othon Cabo,
%E Prado, Antonio Fernando Bertachini de Almeida,
%T Three axis discrete fuzzy attitude control of a low earth orbit (LEO)assymetric satellite with a flexible appendage
%@isbn 85-17-00006-4
%@electronicmailaddress tredi@ele.puc-rio.br
%@electronicmailaddress bastos@ele.puc-rio.br
%@electronicmailaddress marcelo@dem.inpe.br
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL, astrodinâmica, trajetórias espaciais, mecânica celeste, manobras orbitais, astrodynamics, spacecraft trajectories, celestial mecanics, orbital maneuvers.
%B Advances in space dynamics 3: applications in astronautics
%@usergroup administrator
%@usergroup jefferson
%@group
%@group
%@group DMC-INPE-MCT-BR
%3 winter.pdf
%C São José dos Campos
%@copyholder SID/SCD
%@secondarykey INPE-11529-PRE/6918
%2 sid.inpe.br/marciana/2004/11.11.08.36.49
%@affiliation PUC-Rio
%@affiliation PUC-Rio
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%I INPE
%P 188-196
%4 sid.inpe.br/marciana/2004/11.11.08.36
%D 2002
%@documentstage not transferred
%7 3
%A Tredinnick, Marcelo R. A. C.,
%A Bastos, João,
%A Souza, Marcelo Lopes de Oliveira e,
%@dissemination NTRSNASA; BNDEPOSITOLEGAL.
%@area ETES