针对低旋火箭弹在引信头锥摆动时改变了全弹的气动特性问题,进行了气动特性仿真,分析了引信头锥摆动角对火箭弹气动参数的影响,并利用气动仿真得到的数据进行控制能力的仿真,从而为弹道修正火箭弹设计提供依据。仿真结果表明:升力系数和俯仰力矩系数随引信头锥摆动角的增大都有显著的增大,且在稳定飞行时引信头锥摆动火箭弹的修正能力可以满足火箭弹二维弹道修正的要求。

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.