Aiming at the problem that aerodynamic characteristics of low rotation rocket would change when the fuze nose swings. The influence of Fuze nose swing angle on the rocket aerodynamic parameter was analyzed. The simulation of aerodynamic characteristics was implemented and the result was used for the simulation of control ability. Thus it can provide a basis for the design of trajectory correction rocket. The simulation result shows that lift coefficient and pitching-moment coefficients would increase significantly with the increasing of fuze nose swing angle. The capability of trajectory correction of the fuze nose swing rocket could meet the requirement of two-dimensional trajectory correction in the status of stable flight.