Abstract: A new kind of problem for TVC vehicle spinning in the boost stage had been researched. The study of non-linear flying dynamics modeling and dynamic properties of TVC vehicles reveal dominant coupled factors that affect the attitude stability and attitude precision of the pitch channel and yaw
channel. The paper emphasizes the inertial delay coupled effects between vehicle's pitch servo system and yaw servo system, which have always been neglected. An uncoupled plan and control algorithm are put forward from the standpoint of engineering implementation to provide theoretical guidance and reference for further research on this complicated flying control.