摘要
超高速制导炮弹在发射时承受高过载,需要在发射后进行空中对准;MEMS惯组在高过载冲击后,测量精度下降。针对制导炮弹MEMS惯组精度低导致空中对准误差大的问题,在不增加弹上额外机构的前提下,借鉴旋转调制的思想,通过弹体在空中的自身旋转,实现MEMS惯组自补偿来提高空中对准精度。在超高速制导炮弹弹体单轴(滚转轴)转动下,推导了基于旋转调制方法的滚转角辨识算法。根据建立的弹道模型,使用不同滚转角、不同发射方位角的弹道进行仿真,并对单条弹道进行蒙特卡洛仿真。仿真结果表明,滚转角辨识精度在3°以内。与传统滚转角辨识方法相比较,表明了旋转调制方法的准确性。
Hypervelocity guided projectiles are survived the high-g loads within the initial launch and required in-flight alignment after power on,the measurement accuracy of MEMS IMU will decrease after high-g load shocks.In order to solve the problem of low accuracy of in-flight alignment,on the premise of not increasing extra mechanism on the projectile,the idea of rotational modulation is presented to realize the self-compensation of MEMS IMU.The method of improving the accuracy of in-flight alignment through the rotation of the projectile itself in the air is proposed.The roll angle identification algorithm based on the rotational modulation method is derived under the single-axis(roll axis)rotation of the projectile.Based on the established ballistic model,the Monte Carlo simulations are carried out using trajectories with different roll angles,different launching azimuths.The simulation results show that the accuracy of roll angle identification is within 3°.Compared with the traditional roll angle identification method,the accuracy of the rotation modulation method is demonstrated.
作者
陈凯
黄鹏
焦勇
曾诚之
李振毫
杨涛
CHEN Kai;HUANG Peng;JIAO Yong;ZENG Chengzhi;LI Zhenhao;YANG Tao(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,Shaanxi,China;Northwest Industries Group Corporation,Xi’an 710043,Shaanxi,China;Xi’an Aerospace Propulsion Institute,Xi’an 710025,Shaanxi,China)
出处
《弹箭与制导学报》
北大核心
2025年第6期1044-1050,共7页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家自然科学基金面上项目(62373303)。
关键词
超高速制导炮弹
发射坐标系
旋转调制方法
滚转角辨识
空中对准
Hypervelocity guided projectile
Launch-centered earth-fixed frame
Rotation modulation method
Roll angle identification
In-flight alignment
