利用能量/动量飞轮的偏置动量姿态控制系统

研究偏置动量姿态控制系统中的集成能量与姿态控制问题。利用一对正 反转飞轮提供偏置角动量并同时储 /放能以满足星载设备的能源需求。滚动 /偏航运动由俯仰轴磁矩控制。设计了力矩形式的飞轮的控制律 ,使之提供期望的俯仰控制力矩 ,并以给定的功率储 /放能。保持两只飞轮正 反转可以完全避免飞轮控制律中的系统奇异。提出了利用动能反馈的飞轮储能功率规划方案 ,以使系统维持能量平衡 ,避免由于能量过剩引起的飞轮饱和。飞轮的最小转动惯量受最大偏置角动量和最小能量的限制 ,结合几何方法对这种限制条件进行了分析。数值仿真结果证明了控制方案的有效性。

Bias Momentum Attitude Control System Using Energy/Momentum Wheels

The integrated power and attitude control for a bias momentum attitude control system is investigated. A pair of counter-spinning wheels is used to provide the bias angular momentum and store/discharge energy for power requirement of the devices on the spacecraft. The roll/yaw motion is controlled by pitch magnetic dipole moment. The torque-based control law of the wheels is designed, so that the desired pitch control torque is provided and the operation of charging/discharging energy is carried out based on the given power. System singularity in the control law of wheels is fully avoided by keeping the wheels counter-spinning. A power management scheme using kinetic energy feedback is proposed to keep energy balance, which can avoid wheel saturation caused by superfluous energy. The minimum moment of inertia of the wheels is limited by the maximum bias angular momentum and the minimum energy, such constrains are analyzed in combination with the geometrical method. Numerical simulation results are presented to demonstrate the effectiveness of the control scheme.