A method of satellite inertial velocity matching with maneuver assistance is proposed to address the issue of low accuracy in aerial alignment of attitude angles for rolling missiles using velocity matching and maneuver assistance. Under the guidance mode of satellite and inertial combination, based on observability analysis, maneuver assistance adopts the form of longitudinal proportional guidance and gravity compensation guidance law, combined with Kalman filtering to complete the aerial alignment of attitude angle. Compared to the satellite inertial velocity matching method, this method has better alignment effect. Adjusting the navigation ratio has a relatively small impact on the speed and accuracy of roll angle alignment, and its main function is to complete the closure of the guidance circuit and ensure guidance accuracy; Adjusting the compensation coefficient within a certain range (1.0~2.0) has a certain impact on the roll angle alignment speed and accuracy. Increasing the compensation coefficient can improve the alignment speed and accuracy. When the compensation coefficient is greater than 2.0, there is a loss of guidance accuracy.