敏捷小卫星姿态机动切换算法

Switch algorithm for quick small satellite attitude maneuver

以刚体小卫星作为研究对象,提出了一种切换控制算法对小卫星机动进行控制,并对控制力矩陀螺的力矩进行合理调节以避免饱和奇异。描述了敏捷小卫星模型,介绍了单框架控制力矩陀螺(SGCMG)的框架组成,讨论了小卫星切换控制并法。利用添加零运动的伪逆操纵律对单框架控制力矩陀螺系统进行操控,仿真结果指出,小卫星俯仰轴在14 s内机动45°,平均速度可达3.2°/s。结果表明这种切换算法可满足小卫星敏捷性需要。

By taking aim at the application of Single Gimbal Control Moment Gyroscope（SGCMG） to quick small satellites, a switch control algorithm was presented to control the maneuver of small satellite. The small satellite with rigid bodies was used as a model, and the switch control for toques of small satellite with SGCMG was adjusted to avoid saturation singularity. SGCMG was controlled by pseudo-inverse steer law with zero-motion. The simulations show that the small satellite is capable of large angle maneuver with rotation of 45^o at 14 s and average rate of 3.2 ^o/s. It proves that this switch algorithm can meet requirement for quick small satellite.