以典型的航天员推离动作对飞船的扰动力矩作为控制系统仿真的输入参数，分析姿态控制系统受到扰动后的响应。
Put the disturbance moments of typical astronaut's push-off act as the input datas of the control system simulation, and analyze the response of the attitude control system after disturbed.
仿真结果表明：即使系统存在不确定性和外界干扰，仍可在闭环系统中实现精确的姿态控制。
Simulation results show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainties and external disturbances in the system.
为验证模型有效性，将其应用于某三轴稳定对地定向卫星姿态动力学仿真中，得到了相应的太阳光压干扰力矩曲线。
As illustration, these models are applied to an attitude control dynamics simulation of a three-axis stability satellite and the corresponding toques were plotted in curves.
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