%0 Book Section
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%3 Trigolo.pdf
%X Nowadays a c-Cat number of space missions have been using satellites whose mechanical structure consists basically of two parts. The first, is the body of the satellite. which contains cvcr~ instrumentation involved with the objectives of the mission. including the Attitude Control System (ACS). That structure must be rigid enough to support the mechanical loads during the launch phase. The second part, consists of long and/or wide flexible appendices. such as, solar panels, communication antennas. telescopic structures, robotic flexible arms, whose purpose is to manipulated equipment or to put some sensors out ofthc interference ofthe satellite main body. Ally to that, there is the need to have a satellite as lightest as possible, which drives a commitment between rigidity and flexibility. Due to the former, forces and torques during attitude maneuvers can provoke structural vibration and leaves the satellite with residual vibration. Great temperature differences are also a source structural vibration. A primary consequence ofthat structural vibration is the interaction with the ACS. which in turn can be severely limited in its performance. To study and understand the rigid and the flexible interaction motion problem, it is necessary to develop high no linear dynamic model. In this paper an artificial satellite mathematical model formed by a rigid central platform and a rigid solar panel is presented using the Substructure Modeling Approach. A stability analysis is carried out having an actuator action based on a passive procedure which consist of a rotor inside of a viscous liquid. In these preliminary analysis the Root Locus method is applied for a simple satellite model in order to investigate the system poles behavior as a function of the control law gain. It is shown that the stability is reach only when the satellite rotation is around the axes of biggest inertia.
%E Winter, Othon Cabo,
%E Prado, Antonio Fernando Bertachini de Almeida,
%T Attitude control system performace of a satellite
%@isbn 85-17-00006-4
%@secondarytype PRE LN
%K ENGENHARIA E TECNOLOGIA ESPACIAL.
%B Advances in space dynamics 3: applications in astronautics
%@usergroup administrator
%@usergroup jefferson
%@group DMC-INPE-MCT-BR
%C São José dos Campos
%@copyholder SID/SCD
%@secondarykey INPE-11527-PRE/6917
%2 sid.inpe.br/marciana/2004/11.11.08.32.42
%I INPE
%P 178-187
%4 sid.inpe.br/marciana/2004/11.11.08.32
%D 2002
%@documentstage not transferred
%7 3
%A Trigolo, Adriana,
%A Souza, Luiz Carlos Gadelha,
%@dissemination NTRSNASA; BNDEPOSITOLEGAL.
%@area ETES