【摘要】 为全面分析飞轮微振动对高分辨率光学遥感小卫星系统的不利影响，建立遥感小卫星光学–姿控–结构全链路集成分析模型，在设计阶段评估隔振系统对微振动的抑制程度，计算相机综合像移结果。首先，以飞轮扰振为输入建立两级隔振动力学模型；然后建立线性光学系统像移与镜体自由度的函数关系，构建卫星姿态控制系统简化模型，计算卫星在隔振下的姿态角速度稳态误差和像移；最后开展地面测量和在轨微振动校验。结果表明：集成分析模型计算的相机最大像移为0.129 8 px，卫星在扰振力矩作用下姿态稳定度为7.5×10^-6 rad/s；地面试验中相机像移频域单方向最大为0.114 8 px，姿态稳定度7.5×10^-6 rad/s；在轨成像相机像移频域最大为0.084 6 px，期间姿态稳定度达到7.0×10^-6 rad/s。建模计算和实际测试结果处在同一水平，验证了模型的有效性。更多还原

【Abstract】 In order to comprehensively analyze the adverse effects of flywheel micro-vibration on highresolution optical remote sensing small satellite system, a full-link integrated analysis model for optical-attitude control-structure was established to evaluate the suppression of micro-vibration by the vibration isolation system in the design stage and to calculate the integrated image offset of the camera. Firstly, a two-stage vibration isolation dynamics model was built with flywheel vibration as input. Then, the image offset of the linear optical system as a function of the mirror body’s degrees of freedom was created, a simplified model of the satellite attitude control system was constructed, and the steady-state error of the satellite attitude angular velocity and image offset under vibration isolation were calculated. Finally, ground measurements and on-orbit microvibration verification were carried out. The results show that the maximum value of image offset calculated by the integrated analysis model is 0.129 8 px with a satellite attitude stability of 7.5×10^-6 rad/s under the action of the disturbance moment; the maximum value of single-direction image offset of the ground measurement in the frequency domain is 0.114 8 px with a satellite attitude stability of 7.5×10^-6 rad/s; and the maximum value of image offset of the on-orbit imaging in the frequency domain is 0.084 6 px with a satellite attitude stability of7.0×10^-6 rad/s. The modeling and testing results are at the same level, which verifies the effectiveness of the model.更多还原