Derivation of Linearization Small Deviation Motion Equations of Blended Control System

The linearization small deviation motion model is the basis of stability analysis to attitude control system. Endoatmospheric tactics missile weapons widely adopt aerodynamic rudders as actuators, but only depending on aerodynamic rudders can´t satisfy with control requirements at the initial flight phase where the missile´s dynamic pressure is relatively minor. On the other hand, gas rudders are usually used at the starting control phase to augment the control force. In practice, the linkage mode with gas rudders and aerodynamic rudders is the better way to control the missilepsilas attitude. In this paper, the integrated dynamic model of the above blended control missile is established. And complete linearization small deviation motion equations on pitching, yawing and roll loops are derived in details. For this kind of tactics missiles, the research can provide technology supply to dynamic characteristic analysis and designing attitude control system, and establish the basis of the missile´s motion stability analysis.