Research of New-Type Flying Control for Spinning TVC Vehicle

A new kind of problem for TVC vehicle spinning in the boost stage is researched. On the basis of research of the non-linear flying dynamics modeling and dynamic properties of TVC vehicle, the dominant coupled factors which affected the attitude stability and attitude precision of pitch channel and yaw channel were found. The inertial delay coupled effects between pitch servo system and yaw servo system were emphasized, which were ever neglected, and the uncoupled plan and control algorithm were put forward from the point of engineering realization. It is to provide the theoretical guidance and reference for the furthermore research of this complicated flying control.