用于光学遥感器耐受卫星平台微振动环境地面测试的六自由度平台

Six DOF platform applied in ground test of optical remote sensor alleviation margin in satellite micro-vibration environment

考虑空间卫星平台微振动环境对高分辨率空间光学遥感器成像质量的制约,提出了在地面测试光学遥感器耐受空间微振动环境裕度的六自由度激振平台的设计方案。建立了平台的运动学与动力学模型,推导出促动器音圈电机的传递函数并建立了Simulink模型。基于设计的模型研制了六自由度平台。对振动平台样机进行了振动加速度控制精度的验证实验,实验以典型的卫星平台微振动频率点为测试输入。实验结果表明平台振动频率为7~40 Hz时,其加速度输出相对误差可控制在7%以内。该平台借鉴了Stewart平台的并联构型,其结构简单、刚度大,振源输出精确可控,满足地面试验应用要求。

As the micro-vibration of a satellite platform restricts the imaging quality of a highresolution space optical remote sensor,this paper designs a six DOF（Degree of Freedom）platform for the ground test of optical remote sensor alleviation margin in satellite micro-vibration environment.The kinematics and dynamics models of the platform were constructed,and the transfer function,Simulink model of a voice coil actuators were derived.Based on the models,the platform with six DOFs was manufactured.A confirmatory experiment on the vibration acceleration control accuracy of the platform was carried out,in which the micro-vibration frequency of the typical satellite was taken as the input signal.The results show that the relative error of output acceleration has been controlled in 7%in frequencies from 7 Hz to 40 Hz.The platform takes the parallel construct of the stewart model,it has advantages in simpler structure,bigger stiffness and a controllable vibration source,and obtained results meet the requirements of the ground test applications.