发射系统指向角度标校方法

Calibration method for pointing angle of launch system

针对传统瞄星方法存在的效率低和“受制于天”的问题,提出了一种基于模型的标校方法。该方法把安装平台抽象为分段线性的平板模型,其误差用俯仰、偏航、滚转3个参数表示,得到包含模型误差的指向角度。同时,采用高精度卫星导航设备建立虚拟空间基准,利用二者的等价关系,通过牛顿迭代法求解出误差参数,并进行修正。理论和仿真分析表明:只需要2个测量点就可以解算整个模型,提高了标校效率;只要基准点距离身管1 km以上,基准点的测量精度对标校精度的影响就可忽略;通过合理选择基准点,可以将指向角度标校残差控制在0.001 rad。

ed into a linear flat plate model,and its error was represented by three parameters of pitch,yaw and roll,and thus the pointing angle including the model error was obtained.Meanwhile,a virtual space datum can be established by high-precision satellite navigation equipment.Using the equivalent relationship between the two,the error parameters were solved and corrected by the Newton iteration method.Theoretical and simulation analysis shows that the entire model can be calculated with only 2 measurement points,which improves the calibration efficiency,that the influence of the measurement accuracy of the datum can be ignored as long as the reference point is more than 1 km away from the barrel,and that by reasonable selection of the reference point,the calibration residual of the pointing angle can be controlled within 0.001 rad.