高分多模卫星微振动抑制设计与验证

Micro-vibration Attenuation Design and Verification for GFDM-1 Satellite

敏捷型遥感卫星在轨运行期间,星上控制力矩陀螺等扰动源会引起微振动,微振动传递到高分辨率相机等敏感载荷会影响载荷性能,进而影响卫星成像质量,因此需对传递到敏感载荷的微振动进行抑制,以保证卫星高分辨率指标的实现。以高分多模卫星(GFDM-1)的微振动抑制需求为背景,确定了整星微振动抑制技术路线与微振动抑制总体方案,开展了扰动源特性研究,完成了扰动源、星体结构和敏感载荷的减隔振设计与验证,并通过星载微振动测量设备对相机等关键位置的在轨微振动响应进行了测量,对卫星微振动抑制方案进行了飞行验证。在轨微振动测量数据表明:高分多模卫星微振动抑制方案可有效满足敏感载荷相机的微振动抑制需求,可为我国后续敏捷遥感卫星的微振动抑制设计与验证提供参考。

During the operation of agile satellite on orbit,control moment gyroscopes installed on the satellite can cause micro-vibration disturbance,which can be transfered to sensitive payloads such as high resolution camera,affect their performance,and then further affect the satellite’s imaging quality.Therefore,the micro-vibration transferred to sensitive payloads must be attenuated to guarantee the realization of the high resolution index.Based on the micro-vibration attenuation requirement of GFDM-1 satellite,micro-vibration attenuation technology roadmap and overall solution are defined,characteristics of disturbance source are researched;micro-vibration attenuation design and verification of disturbance source,satellite structure and sensitive payload is performed,the on-orbit micro-vibration of critical position such as the camera installing interface is measured by the equipments on board;and the micro-vibration attenuation approach is verified on orbit.Measured data on orbit shows that,the micro-vibration attenuation approach of GFDM-1 satellite can effectively meet the micro-vibration attenuation requirement of the sensitive payload camera,and can provide reference for the micro-vibration attenuation design and verification for the ongoing agile remote sensing satellite of China.