Abstract: Abstract：The problems of spinning angle velocity determination for satellites with attitude anomaly are investigated. A spinning angle velocity determination method based on sun sensors measurement is proposed, and the influence of individual error source on the angle rate determination error is obtained by deliberate analysis. According to the error analysis conclusion, a strategy is presented to maintain the determination precision for a smaller spinning angle rate by using different measurement data with larger time interval in spinning angle velocity calculation. The effectiveness of the proposed method is demonstrated by numerical simulations, and by applying the method with telemetry data of sun sensors the actual spinning angle velocity is also obtained for a satellite inorbit out of control．  

Key words: Keywords：satellite, attitude anomaly, spinning angle velocity, sun sensor, measurement error