Abstract: For an endo-atmospheric missile with lateral attitude jet engines and aerodynamic fins,attitude control is investigated under the condition of body spinning.Choosing the lateral accelerations of the missile as the output,the mathematical models of the attitude control system are constructed,analyzed and simplified.Both dual path control and single path vectored control are considered.Based on the discrete characteristics of the attitude thrusters,respective controllers are designed to realize the fast tracking of the lateral accelerations.In the design,the lateral jet magnification factors are also estimated on-line to cope with the jet interaction effect.Finally,numerical simulation is conducted,and the simulation results show the effectiveness of the proposed method.

Key words: nonlinear control systems, attitude control, tracking, jet engines, prediction