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- W2322817962 abstract "This paper presents the application of the Receding Horizon approach to the spacecraft momentum management problem. Attitude control of a satellite in a circular orbit under the in∞uence of constant disturbances is considered. Control designs are demonstrated for a simplifled planar case as well as for the full dynamics of the spacecraft. The response of the receding horizon controller is compared to a controller derived from Lyapunov conditions. The receding horizon approach demonstrates its ability to align the spacecraft to a torque equilibrium attitude and regulate the momentum of the control even when torque and rate constraints are included in the problem. I. Introduction Spacecraft attitude control has been an important area of research and has received a large amount of attention. Spacecraft dynamics provide a rich area of research because their behavior is nonlinear and they are in many cases to operate over a large range of operating conditions. A common choice of actuators to control the satellite is the momentum exchange device. Momentum exchange devices such as control moment gyros (CMG’s) or reaction wheels maintain control of the satellite by transferring momentum from the spacecraft so that it follows a designed trajectory. If a constant disturbance such as an aerodynamic torque acts on the spacecraft, the momentum in the control can build up as result of the constant control torque required to reject the disturbance. These momentum exchange devices can be desaturated by the alignment of the spacecraft with a torque equilibrium attitude (TEA). When such an attitude is obtained, the gravity gradient torque and gyroscopic torques balance the disturbance torque to create an equilibrium attitude. No control input is required to maintain this attitude, allowing the momentum to desaturate. For a spacecraft in a" @default.
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- W2322817962 date "2007-06-15" @default.
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- W2322817962 title "Spacecraft Momentum Management and Attitude Control Using a Receding Horizon Approach" @default.
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- W2322817962 doi "https://doi.org/10.2514/6.2007-6442" @default.
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