基于磁控及角速率估计的微卫星姿态稳定研究

method of utilizing a single pitch momentum wheel and three magnetic torque rods to do three-axis satellites attitude control is developed. An attitude and attitude rate estimation technique based on star sensor to provide all the required angular rates without dynamic gyro is presented. Nonlinear equations of motion are developed and then linearized in a time varying form. The equations are reduced to linear time invariant using the periodic nature of the equations in an orbit. Magnetic control laws are developed using constant coefficient linear quadratic regulator. For the attitude determination, orbital model is used to generate reference Euler angle, and two more linear system models are used within a Linear Kalman Filter- one for the roll and yaw of the satellite and a second for the pitch. Optimal Control Law is used to provide negative feedback control. The new algorithms can provide a simple yet effective means of determining and controlling satellite attitude.