Modal analysis of the missile conveyance’metal hose is carried out in this paper.

In order to avoid cross couplings between the vertical and lateral motion,decoupling control of a double-channel control rolling missile autopilot was studied.

Based on the characteristics of rolling missile with double-channel control,the autopilot loop is transferred from body coordinate system to quasi-body coordinate system after a rolling transfer.

The analysis of the character, principle, and realization for the guidance technology of rolling missile is made.

A moving mass control of rotating missile is a kind of new control mode,it differs from other control modes because it generates an angle of attack and an angle of sideslip directly from the mass motion.

Trajectory simulation of rotating missile is the basis of optimization designs for fins of missile and trajectory.

The analyses on the variable centroid controlled spinning missile were made by utilizing the root locus method.

Study on single-channel control for rotary missile;

The paper then applies the above mentioned decoupling control theory in the decoupling guidance design of rolling missiles.

The mechanism of dynamic instability of rolling missile was analyzed by describing the dynamics of rolling missile as a closed loop with dynamic negative feedback.