为克服现有舰载导弹扩大扇面发射方法的不足,推导出一方程组,能直接计算出导弹转弯的扇面装订角,使导弹在转弯后的前置航向直接对准新的自控段终点,也可根据战术需要确定在任一时刻导弹的转弯角度进行航路规划。对计算参数的取值及主要干扰因素进行了分析。然后用非解析解的近似计算法进行了计算,并对计算结果用作图法进行了精度验证。 In order to overcome the shortcomings of existing shipborne missiles in expanding the fan-out method, an equation system can be deduced to directly calculate the fan-bound angle of the missile, so that the pre-heading course of the missile after turning is directly aligned with the end point of the new automatic control section. According to the tactical needs to determine at any one time the missile angle of turn for route planning. The parameters of the calculation and the main interference factors were analyzed. Then the approximate calculation method of non-analytical solution was used to calculate the accuracy of the calculation results.