摘要
为实时准确测量制导炮弹飞行姿态角以实现精确控制,针对制导炮弹的炮射环境等,将磁阻传感器与角速率陀螺组合使用,根据地磁场的基本性质、磁阻传感器测量姿态角的工作原理和制导炮弹的绕心运动学方程,提出了制导炮弹飞行姿态角的解算方法.以某制导炮弹为算例,采用增加测量噪声的三轴角速度数据作为姿态测量传感器的输出信号,利用文中方法对该模拟仿真信号进行了弹体飞行姿态角的计算.结果表明,采用三轴磁阻传感器和两轴角速率陀螺组合测量制导炮弹飞行姿态角的方法在理论上是可行的,对于信噪比大于等于5的仿真信号,姿态角的解算精度能够满足弹道精度控制的要求,为制导弹箭飞行姿态角的实时测量提供了一定的参考.
To measure the flight attitude angles of Guided Projectile（GP） rapidly and accurately to realize the precise control,magnetometers and angular rate gyros was combined considering the gun-launched condition of GP.According to the fundamental characteristics of geomagnetic field,the principle of measuring the attitude angles with magnetometers and kinematics equation around the gravity center of GP,an approach of calculating the attitude angles of GP was proposed.Taking a certain type of GP for an example,the data of triaxial angular velocities with the addition of measurement noise was considered as the output signal of the sensors.Through the approach proposed in this paper,the signal was used to obtain the attitude angles.The results indicate that it is feasible in theory to obtain the attitude angles by the combination of magnetometers and gyros.For the signal with the noise-signal ratio of 5 or more,the accuracy of the attitude can meet the requirement of trajectory control.Some results concluded are useful for further research.
出处
《弹道学报》
EI
CSCD
北大核心
2011年第3期37-42,共6页
Journal of Ballistics
基金
江苏省"青蓝工程"资助项目
南京理工大学卓越计划
紫金之星资助项目
南京理工大学科技发展基金项目(XKF09075)
关键词
制导炮弹
姿态角
磁阻传感器
角速率陀螺
组合测量
guided projectile
attitude angle
magnetometers
angular rate gyros
combinative measurement
