When guided munitions is launched, sensor zero will shift by high impact, which would produce zero error in process of solving overload by accelerometer, therefore, in this paper, the overload filtering algorithm based on disturbance model was designed. Firstly, a memory attenuated extended Kalman filter for overload parameter identification of satellite-guided munitions was designed by analyzing long and short period of trajectory disturbance, and the short period disturbance of accelerometer and trajectory was filtered out through least squares algorithm to calibrate overload zero error. What's more, the experimental results and firing practice show that correction algorithm has less computational cost and is more accurate and simpler for application in engineering.