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为了补偿空间相机由于地面定标环境和在轨工作环境不同及发射时振动冲击引起的焦面离焦,保证空间相机在轨成像质量,设计了焦面调焦机构。首先,针对尺寸超长焦面,采用增设调焦内框来增加焦面基板刚度,通过蜗轮蜗杆传动驱动丝杠运动实现机构自锁。其次,利用有限元分析软件patran/nastran建立了调焦机构的有限元模型,用mpc模拟导轨连接,对调焦机构进行模态分析。最后,对调焦机构进行了力学试验验证和精度测试。试验及测试结果表明:设计的调焦机构动态刚度高,一阶计算模态为228.7 Hz,而试验得到一阶模态为223.9 Hz,两者相差2%;调焦灵敏度达0.25μm,调焦精度达到6.3μm,焦面基板两端同步误差达到±4μm,满足航天相机对调焦机构高分辨率、高精度、高可靠性的要求。
In order to compensate the focal plane defocusing caused by the vibration impact during the calibration of the space camera and the working environment in the orbit of the space camera and to ensure the imaging quality of the space camera in orbit, a focal focusing mechanism is designed. First of all, for the size of the long focal plane, the use of additional focus within the frame to increase the focal plane stiffness of the substrate, through worm gear drive screw movement to achieve institutional self-locking. Secondly, finite element model of focusing mechanism was established by using finite element analysis software patran / nastran, and the mode of focusing mechanism was analyzed by mpc analogue rail connection. Finally, the focusing mechanism is verified by mechanical test and precision test. The test and test results show that the designed focusing mechanism has a high dynamic stiffness, the first order modal is 228.7 Hz, and the first order mode is 223.9 Hz, the difference between them is 2%. The focusing sensitivity is 0.25 μm and the focusing Accuracy of 6.3μm, the synchronization error of the substrate at both ends of the focal plane to ± 4μm, to meet the space camera focusing mechanism high-resolution, high precision, high reliability requirements.