可见红外一体化敏捷小卫星微振动抑制方法

Micro-vibration suppression method for agile & visible/infrared integrated small satellite

随着光学遥感小卫星高分辨率、高集成度、高敏捷等需求提升,部分卫星同时配置可见红外一体化相机与控制力矩陀螺(control moment gyroscope,CMG),兼顾轻小型化与全天时、多目标、多模式成像要求。针对此类卫星存在CMG、红外相机制冷机等多个扰振源,且对于相机成像质量影响大、抑制难等挑战,对基于上述扰振源的微振动综合抑制方法进行了研究,包括设计、安装CMG隔振器、将红外相机制冷机压缩机与相机光机主体隔振安装,设计、安装阻尼桁架实现相机主体与卫星平台舱结构之间的隔振等。通过综合应用上述扰源减振、终端隔离等措施,经分析计算与整星微振动及在轨实际测试与验证,能够有效降低微振动对图像质量的影响,即使对于可见红外一体化相机,分辨率为亚米级的可见光通道在轨动态调制传递函数(modulation transfer function,MTF)也能够达到0.1,微振动对可见相机MTF的影响因子可控制到0.991。

With increasing demand for high resolution,integration and agility of optical remote sensing small satellites,visible/infrared dual-color common aperture camera as well as CMG(control moment gyroscope) are installed to meet the requirements of miniaturization,all-day and night,multi-target and multi-model imaging.On such satellites there are several kinds of components with micro-vibration,including CMG,infrared camera cryocooler,etc.,which has a great influence on image quality of camera and is difficult to suppress.Therefore,a comprehensive method for suppressing micro-vibration caused by above-mentioned disturbance sources is proposed,including CMG vibration isolator,isolating installation between cryocooler and camera optical structure,and damping truss is designed and installed to realize isolation between camera optical and satellite platform structure.Using above integrated disturbance source damping and terminal isolation measures,through analysis,calculation,satellite micro-vibration experiment verification and in-orbit test,the effect of micro vibration on image quality can be effectively reduced.Even for visible infrared integrated camera,the in-orbit dynamic MTF(modulation transfer function)of visible channel with sub-meter resolution can reach 0.1,and the influence factor of micro vibration on MTF can be controlled at 0.991.