摘要
针对弹载惯测组合加速度计面临振动环境下测量精度超差问题,构建弹体-惯测组合的两自由度动力学分析模型,配合有限元仿真手段,从全弹结构和惯测组合内部结构两部分进行分析。研究了减振垫刚度、惯测组合内部架构固有频率特性以及加速度计布局等因素对弹载惯测组合振动响应的影响机理。提出的设计准则包括:降低减振垫刚度有利于减小加速度计的振动响应,但需要避免弹体-惯测组合两自由度系统固有频率过于接近;设计保证质心接近惯测组合减振中心,在存在质心偏心时,需减小加速度计到惯测组合减振中心在垂直于激励方向的距离;优先保证惯测组合内部架构基频高于外部激励的最高频率,如无法实现,需保证内部架构线角耦合频率高于外部主要激励的最高频率。
Aiming at solving the problem of measurement precision in vibration environment of the missile borne IMU accelerometers,the 2 DOF model of missile body-IMU is established,and the structure of missile body and the internal structrue of IMU are analyzed by finite element simulation.The influence factors of IMU vibration response which include the stiffness of damping pads,the natural frequency features of internal structure and the layout of accelerometers are studied.The proposed design criteria include:Reducing the stiffness of damping pads is beneficial to reduce the vibration response of accelerometers,and it is necessary to avoid the natural frequencys of 2 DOF model of missile body-IMU that are getting too close;The design can ensure that the center of mass is close to the center of damping pads,when the center of mass is eccentric,the distance from the accelerometer to the center of damping pads which is perpendicular to the direction of excitation needs to be reduced;The first natural frequency of the internal structure of IMU is greater than the maximum frequency of the external excitations,if it can not be realized,the translaion-rotation coupling frequency of the internal structure is required to be greater than the maximum frequency of the external main exciutations.
作者
邱东
Qiu Dong(The General Design Institute of Hubei Aerospace Technology Academy,Wuhan 430040,China)
出处
《航天控制》
CSCD
北大核心
2021年第5期56-62,共7页
Aerospace Control
关键词
惯测组合
加速度计
弹体
动力学
振动
Inertial measurement unit(IMU)
Accelerometer
Missile body
Dynamics
Vibration
