火箭弹MEMS陀螺捷联惯导系统  

MEMS Gyro Strapdown Inertial Navigation System(SINS) for Rockets

作　　者：李星海[1] 陈述奇[1] 蔡体菁[2] 张巧云[1] 胡旭伯[1] 刘姝[1] 

机构地区：[1]中国电子科技集团公司第26研究所,重庆400060 [2]东南大学仪器科学与工程系,江苏南京210096

出　　处：《压电与声光》2012年第5期703-707,共5页Piezoelectrics & Acoustooptics

摘　　要：火箭弹正朝着远程化、精确制导化方向发展,制导装置是其中的核心。该文采用微机电系统(MEMS)陀螺、石英挠性加速度计、高动态GPS接收机、高速导航计算机等硬件及捷联惯性导航和卡尔曼滤波算法,研制了小型捷联惯性/GPS组合导航系统。该组合导航系统具有体积小,精度高,成本低等特点,试验表明该惯导系统可以满足增程火箭弹制导要求。The rockets are being developed toward the long range and precision guide,the guidance device is the core of the rockets.Based on the strapdown inertial navigation technology and Kalman filtering technique,a miniature strapdown inertial navigation/GPS integrated navigation system has been developed by using MEMS gyro,quartz flexible accelerometer,high-dynamic GPS receiver and high-speed navigation computer.The integrated navigation system has the features of small size,high accuracy and low cost.The experimental results showed that the inertial navigation system could satisfy the requirements of the guidance of the range-extended rockets.

关 键 词：微机电系统(MEMS)陀螺 捷联惯导系统 卡尔曼滤波 火箭弹 

分 类 号：V241[航空宇航科学与技术—飞行器设计]