TY - GEN
T1 - Performances comparison of linear and sliding mode attitude controllers for flexible spacecraft with reaction wheels
AU - Abdulhamitbilal, E.
AU - Jafarov, E. M.
PY - 2006
Y1 - 2006
N2 - In this study, two control algorithms for the three axes stabilized geosynchronous communication satellite Intelsat V are given. The spacecraft is assumed to be controlled via reaction wheels. First, linear control method is used to design an attitude feedback control algorithm for a rigid satellite with attitude angles. Linearized form of the spacecraft dynamics are given in attitude angles representation. Second, sliding mode control method is used for the attitude controller with equivalent control term for flexible satellite. The performances and disadvantages are discussed on design example for both cases. Modeling and simulation are done by using MATLAB-Simulink programming. The results show that using attitude linear controller may cause the mission cost to be high and decrease the maneuver performances for a geosynchronous satellite mission. Also linear attitude controller does not include neglected nonlinear effects, flexibility effects, etc. That is why the linear attitude controller has a very long settling time. On the other hand, attitude sliding mode controller for geosynchronous satellite with flexible solar arrays uses energy optimally with a great performance and relative small settling time. Moreover, attitude sliding mode controller includes all effects of nonlinear dynamics which is robust to bounded external disturbances and unmodelled dynamics.
AB - In this study, two control algorithms for the three axes stabilized geosynchronous communication satellite Intelsat V are given. The spacecraft is assumed to be controlled via reaction wheels. First, linear control method is used to design an attitude feedback control algorithm for a rigid satellite with attitude angles. Linearized form of the spacecraft dynamics are given in attitude angles representation. Second, sliding mode control method is used for the attitude controller with equivalent control term for flexible satellite. The performances and disadvantages are discussed on design example for both cases. Modeling and simulation are done by using MATLAB-Simulink programming. The results show that using attitude linear controller may cause the mission cost to be high and decrease the maneuver performances for a geosynchronous satellite mission. Also linear attitude controller does not include neglected nonlinear effects, flexibility effects, etc. That is why the linear attitude controller has a very long settling time. On the other hand, attitude sliding mode controller for geosynchronous satellite with flexible solar arrays uses energy optimally with a great performance and relative small settling time. Moreover, attitude sliding mode controller includes all effects of nonlinear dynamics which is robust to bounded external disturbances and unmodelled dynamics.
UR - https://www.scopus.com/pages/publications/33845585233
U2 - 10.1109/VSS.2006.1644543
DO - 10.1109/VSS.2006.1644543
M3 - Conference contribution
AN - SCOPUS:33845585233
SN - 1424402085
SN - 9781424402083
T3 - Proceedings of the 2006 International Workshop on Variable Structure Systems, VSS'06
SP - 351
EP - 358
BT - Proceedings of the 2006 International Workshop on Variable Structure Systems, VSS'06
T2 - 2006 International Workshop on Variable Structure Systems, VSS'06
Y2 - 5 June 2006 through 7 June 2006
ER -