A generic model of a nanosatellite attitude control and stabilization system was developed on the basis of magnetorquers and reaction wheels, which are controlled by PID controllers with selectable gains. This approach allows using the same architectures of control algorithms (and software) for several satellites and adjusting them to a particular mission by parameter variation. The approach is illustrated by controlling a satellite attitude in three modes of operation: detumbling after separation from the launcher, nominal operation when the satellite attitude is subjected to small or moderate disturbances, and momentum unloading after any reaction wheel saturation. The generic control algorithms adjusted to each mode of operation were implemented in a complete attitude control system. The control system model was embedded into a comprehensive simulation model of satellite flight. The simulation results proved the efficiency of the proposed approach.

中文翻译：

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卫星姿态控制系统的通用模型

在磁矩和反作用轮的基础上，开发了一种纳米卫星姿态控制和稳定系统的通用模型，它们由具有可选增益的PID控制器控制。这种方法允许对几颗卫星使用相同的控制算法（和软件）架构，并通过参数变化将它们调整到特定任务。通过在三种操作模式下控制卫星姿态来说明该方法：与发射器分离后退避；在卫星姿态受到较小或中等干扰时的标称运行；以及任何反作用轮饱和后的动量卸载。调整为每种操作模式的通用控制算法均在完整的姿态控制系统中实施。控制系统模型被嵌入到卫星飞行的综合仿真模型中。仿真结果证明了该方法的有效性。