摘要
针对航天器快速绕飞姿态控制和脉宽调制,提出了脉宽调制指令算法,结合航天器转动惯量、期望状态、控制力矩等进行了姿态控制可行性分析。基于误差四元数的姿态滑模控制,结合不同的控制力矩和脉宽调制档次,采用姿态角误差分析了脉宽调制、控制力矩、姿控精度的关系。通过数值仿真,验证了脉宽调制控制指令的有效性和姿态控制应用的可行性。
A PWM （Pulse Width Modulation） command algorithm is proposed for fast spacecraft circumnavigation attitude control and pulse width modulation. A feasibility analysis is given for attitude control taking into account factors including rotation inertia, desired states and control torque. Error quaternion-based sliding mode control is implemented from different levels of torque and PWM. The relationship between PWM, control torque and attitude control precision is illustrated through attitude angle errors. Numerical simulation verifies the validity of the algo-rithm and its feasibility for attitude control.
出处
《飞行器测控学报》
2012年第5期15-19,共5页
Journal of Spacecraft TT&C Technology
关键词
快速绕飞
脉宽调制
误差四元数
滑模控制
fast circumnavigationl Pulse Width Modulation （PWM）
error quaternion
sliding mode control
