Dynamic analysis and control design for a spinning missile with impulsive attitude control motors

Impulsive attitude control motor array mounted on missile and spinning missile models are built. Jet interaction is taken into account in dynamic model using force and moment amplification factors which are defined in the form of vector. The advantage of this definition is displayed. Missile which rolls in a low rate is simply analyzed when only stabilization aerodynamic moment being considered. A new coordinate system is defined in which the gyro motion of missile can be conveniently depicted. Meaningful conclusion from dynamic analysis results in the simplification of missile dynamic equations which will be applied in the design of control strategy. Eventually, control strategy and ignition logic are designed. Simulation results are showed when several jet interaction data are set and ignition logic uses enumeration arithmetic and fast arithmetic respectively. The results show the efficiency of control strategy and ignition logic, and conclude that the influence of the main moment amplication factor is primary when jet interaction is considered.