关键词: 反作用飞轮, 姿态稳定控制, 动力学方程, 线性优化, 最佳控制, 欠驱动航天器

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