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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.
In view of the moment when a high-speed rocket launches a muzzle, the MEMS gyroscope can hardly withstand the acceleration of hundreds of g so that the Micro INS can not complete the navigation task. A MEMS accelerometer is proposed (GFMINS) instead of the traditional MINS and small GPS to form a GFMINS / GPS integrated navigation system, to achieve the requirements of rocket positioning.At the same time, in view of the problem that the angular velocity error of GFMINS accumulates faster with time, Based on the analysis of singular value decomposition, the observability of the system is analyzed and the feedback variables of the combination system are determined.Finally, taking the motion model of a certain type of rocket as an example The simulation results show that the navigation accuracy of GFMINS / GPS integrated navigation system meets the actual needs.