Attitude Stabilization of an Underactuated Spacecraft with Two Reaction Wheels

Abstract

Abstract: Under the assumption that the total angular momentum of the system is not zero, Euler angles of the spacecraft at rest with respect to the inertial frame can not be controlled tO zero when there are only two flywheels output torque.Furthermore,the angular rate stabilization and spin-axis stabilization achieved based on the assumption can not satisfy various demands of attitude control.A kind of attitude stabilization scheme tO the most extent was firstly proposed,which was the spacecraft angular velocity stabilization as well as the spacecraft line-of-sight aiming at an arbitrarily given inertial direction.Then,the expected orientation of spacecraft with zero angular velocity was derived with a new attitude parameterization and LQR controller was designed based on the linearized system.The simulation results demonstrate that the LQR controller can achieve the expected attitude stabilization scheme,which not only satisfies the attitude control demand of the spacecraft with antennae or camera,but also enhances the reliability of the underactuated spacecraft.

Key words: Reaction wheel, Attitude stabilization control, Dynamic equation, Linear optimization, Optimal control, Underactuated spacecraft

Jin Lei Xu Shijie (School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 100191). Attitude Stabilization of an Underactuated Spacecraft with Two Reaction Wheels[J]. Chinese Space Science and Technology.

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Attitude Stabilization of an Underactuated Spacecraft with Two Reaction Wheels

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