论文部分内容阅读
本文讨论了自旋卫星向任意目标姿态机动的动力学问题.文中导出了一组受一串脉冲控制力矩作用的卫星姿态运动的解析表达式.这些公式描述了角动量、章动角和姿态相位角与控制力矩、控制次数之间的变化规律,可以直接应用于卫星姿控系统和姿态确定的设计.必须指出的是:关于将卫星自旋轴控制到垂直于轨道平面或将自旋轴控制到指向太阳,都是本文所得结果的两个特例.
In this paper, we discuss the dynamical problem of a satellite moving to any target attitude. In this paper, we derive a set of analytic expressions of the satellite attitude motion under a series of impulse control moments. These formulas describe the angular momentum, nutation angle and attitude phase Angle and control torque, the number of changes between the control rules can be directly applied to the satellite attitude control system and attitude determination must be pointed out that: the satellite spin axis control perpendicular to the plane or the spin axis control To point to the sun, are two special cases of the results obtained in this paper.