Based on extended kalman filter ( ekf ) algorithm , an traditional attitude determination scheme using star sensors and gyros was studied , and proved not able to achieve the required precision . so a new idea called instrument - in - loop was presented what using the attitude information contained in the payload ' s data for the control loop . the simulation proved that the instrument - in - loop method can greatly improve the precision of attitude determination with low cost 建立了svom卫星各种姿态敏感器的测量模型，研究了基于推广卡尔曼滤波算法的“星敏感器+光纤陀螺”定姿方案，指出了其无法满足svom卫星的定姿精度要求，并提出了instrument - in - loop的思想，即利用卫星有效载荷测量数据中蕴含的高精度姿态信息来滤波定姿，从而在避免使用昂贵的星敏感器的同时大大提高了系统的定姿精度。
