论文部分内容阅读
为研究舵机控制精度,利用matlab/simulink软件建立六自由度舵控火箭弹弹道仿真模型。用蒙特卡洛法对舵控火箭弹分别考虑舵偏角误差和起控时刻误差时进行模拟打靶,统计出成功子样中舵控火箭弹的弹着点分布情况。在加入相关干扰误差的情况下分别对舵偏角误差和起控时刻误差下的落点散布进行了仿真分析,计算出不同射角下的横向和纵向修正值。分析了各自因素舵控火箭弹弹道特性和精度的影响,为以后舵控系统的高精度设计提供了相关参考。
In order to study the control accuracy of servo, a six-degree-of-freedom rudder-controlled projectile trajectory trajectory simulation model was established by using matlab / simulink software. Monte-Carlo method was used to simulate rudder-controlled rocket missile rudder deflection error and starting time error respectively, and the distribution of rocket-propelled rocket launchers in success sub-sample was calculated. Under the circumstance of adding perturbation error, the scatter of rudder deflection under the error of rudder and the error of starting moment were simulated and analyzed respectively, and the horizontal and vertical correction values were calculated under different angles of incidence. The influence of the rudder-controlled rocket projectile’s ballistic characteristics and accuracy is analyzed, which provides reference for the high-precision design of the rudder control system in the future.