Modeling and dynamic characteristic analysis of BTT missile

With reasonable hypothesis, the non-linear 6 DOF model involving various couplings was established, and the couplings were divided into four groups. The effect of aerodynamic configuration and static stability to dynamic characteristic is developed based on transfer function. For stable missile, there is null point in the right plan for rear control missile, which is non-minimum phase system, while there is no null point in the right plan for canard control missile, which is minimum phase system. There is import influence to feedback gain of angular velocity loop by static stability. For unstable missile, high gain must be keep to make angular velocity loop stable for rear control missile, while the gain can not be high to make angular velocity loop stable for canard control missile.