高速火箭弹GFMINS/GPS组合导航系统  

GFMINS/GPS integrated navigation systems for high speed rocket projectiles

作　　者：岳鹏[1] 史震[1] 杨杰[1] 程子健[1] 

机构地区：[1]哈尔滨工程大学自动化学院,黑龙江哈尔滨150001

出　　处：《华中科技大学学报（自然科学版）》2011年第11期10-14,共5页Journal of Huazhong University of Science and Technology(Natural Science Edition)

基　　金：国家高技术研究发展计划资助项目(2008AA09Z204)

摘　　要：针对高速火箭弹发射出膛瞬间,弹上微机电系统(MEMS)陀螺难以承受上百g的加速度,使得弹上的微惯导系统(Micro-INS)无法完成导航任务,提出用MEMS加速度计构成的无陀螺微惯性导航系统(GFMINS)代替传统MINS与小型GPS构成GFMINS/GPS组合导航系统,实现火箭弹的定位要求.同时,针对GFMINS中角速度误差随时间积累较快的问题,应用分段式定常系统(PWCS)的可观测性分析方法,在奇异值分解的基础上,对系统进行可观测性分析,并确定了组合系统反馈校正变量.最后,以某型火箭弹的运动模型为算例进行了仿真,结果表明GFMINS/GPS组合导航系统的导航精度满足实际需求.The micro-electro-mechanical systems（MEMS） gyro in the high speed rocket projectile could not bear an acceleration with some hundreds of g while it fires,and so the micro inertial navigation system（Micro-INS） was unable to work for the navigation task.A kind of gyro free inertial navigation system（GFINS） with multiple MEMS accelerometers was proposed to replace the MINS system and small GPS integrated navigation systems to achieve the navigation target.In order to restrain the rapid growth of angular velocity errors,the observability analysis method of piece-wise constant system（PWCS） was used to analyses the observability of system states based on singular value decomposition for the system sates feedback correction variables.Finally,a trajectory of rocket projectile was tracked by this GFMINS/GPS integration navigation in simulation experiment.The results show that the proposed GFMINS/GPS integrated navigation system performances satisfactorily.

关 键 词：无陀螺微惯导系统 全球定位系统 卡尔曼滤波 分段式定常系统 奇异值分解 

分 类 号：V224[航空宇航科学与技术—飞行器设计]