Nonlinear decoupling sliding mode control and attitude control of spacecraft
Control of a class of uncertain nonlinear systems which can be decoupled by state-variable feedback is considered. A variable-structure-control (VSC) law is derived so that in the closed-loop system the output variables asymptotically track given output trajectories in spite of any uncertainty in the system. On the basis of this result, a control law is derived for the attitude control of an orbiting spacecraft in the presence of uncertainty using reaction jets. The controlled outputs are the three Euler angles which describe the orientation of the spacecraft relative to an orbital frame. Simulation results are presented to show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainty in the system.
Computer science; Control systems; Nonlinear control systems; Nonlinear systems; Output feedback; Sliding mode control; Space vehicles; State feedback; Trajectory; Uncertainty
Aeronautical Vehicles | Aerospace Engineering | Controls and Control Theory | Electrical and Computer Engineering | Electrical and Electronics | Multi-Vehicle Systems and Air Traffic Control | Power and Energy | Signal Processing | Space Vehicles | Systems Engineering and Multidisciplinary Design Optimization
Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.
Singh, S. N.,
Nonlinear decoupling sliding mode control and attitude control of spacecraft.
IEEE Transactions on Aerospace and Electronic Systems, 25