动力调谐陀螺仪的瞬态动力学及误差分析  

Analysis on transient dynamics and error for dynamically tuned gyro

作　　者：刘光斌[1] 吴瑾颖[1] 吴懿[2] 

机构地区：[1]第二炮兵工程学院,西安710025 [2]中国人民解放军96623部队,江西赣州341000

出　　处：《电光与控制》2008年第5期79-83,共5页Electronics Optics & Control

摘　　要：为了建立陀螺仪在过载—振动复合环境下的误差模型,应用有限元分析软件ANSYS,针对某型导弹使用的动力调谐陀螺仪的结构,建立基于具体参数的实体和有限元动力学模型,并开展了陀螺仪的瞬态动力学分析研究,由此计算由于陀螺转子和平衡环的质心偏移造成的陀螺仪漂移误差,得到在过载—振动复合环境下陀螺仪漂移角速度与在过载、振动单一环境下漂移角速度之间的关系。To constitute the error model of a gyroscope in overload-vibration combined environment, we studied the structure of the Dynamically Tuned Gyroscope （DIG） used on a certain type of missile based on ANSYS, a finite element analysis software platform. We built up the finite-element dynamic model according to the accurate structure parameters, and studied the transient dynamics of the gyroscope. Then we calculated out the gyro drift error caused by mass center deviation of the gyro rotor and equilibrium ring, and obtained the relationship of gyro drift angular speed in overload-vibration combined environment and the drift angular speed in simple overload or vibration environment. The result showed that the former is not an accumulated result of the later two.

关 键 词：动力调谐陀螺仪 导弹控制系统 有限元法 误差分析 

分 类 号：V271.4[航空宇航科学与技术—飞行器设计] TJ76[兵器科学与技术—武器系统与运用工程]