为了提高火箭增程弹射表编拟和弹道仿真的精度,文中利用样条函数与参数微分修正技术构建弹道时变参数整体辨识方法,给出了发动机标准特性参数与非标准特性参数的转换模型,实现了从多普勒雷达径向速度数据获取发动机动态推力。射表编拟实践和仿真验证表明,该方法有效、可行。

In order to improve accuracy of firing tables production and trajectory simulation for rocket assisted projectile, the integral ballistic parameter identification method was constructed by spline function and parameters differential correction technology, and transformation model for standard and nonstandard engine parameters was given, identification of dynamic engine thrust from radial velocity measured by Doppler radar was realized. The simulation results show that the method is effective and feasible.