摘要
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 method to enlarging launching sector angle of the shipborne missile,a set of equations is derived. Thus,the sector setting angle can be calculated directly while the missile is turning,so that the heading lead angle of the missile can aim directly at the new terminal of the program-conttolled flight distance after the missile turn. Also,the turning angle can be determined at any time to meet the tactical needs,so as to perform flight-path programme. In addition,the values and the principal interference factors of the calculating parameters are analyzed and calculated by approximate calculation of nonanalytic solution,and accuracy examination on calculating results is carried out by means of construction method.
出处
《战术导弹技术》
1999年第4期16-21,27,共7页
Tactical Missile Technology
