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首页> 外文会议>Integrated modeling of complex optomechanical systems >Modeling and verification of the diffraction-limited visible light telescope aboard the solar observing satellite HINODE
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Modeling and verification of the diffraction-limited visible light telescope aboard the solar observing satellite HINODE

机译：太阳观测卫星HINODE上的衍射极限可见光望远镜的建模和验证

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HINODE, Japanese for "sunrise", is a spacecraft dedicated for observations of the Sun, and was launched in 2006 to study the Sun's magnetic fields and how their explosive energies propagate through the different atmospheric layers. The spacecraft carries the Solar Optical Telescope (SOT), which has a 50 cm diameter clear aperture and provides a continuous series of diffraction-limited visible light images from space. The telescope was developed through international collaboration between Japan and US. In order to achieve the diffraction-limited performance, thermal and structural modeling of the telescope was extensively used in its development phase to predict how the optical performance changes dependent on the thermal condition in orbit. Not only the modeling, we devoted many efforts to verify the optical performance in ground tests before the launch. The verification in the ground tests helped us to find many issues, such as temperature dependent focus shifts, which were not identified only through the thermal-structural modeling. Another critical issue was micro-vibrations induced by internal disturbances of mechanical gyroscopes and momentum wheels for attitude control of the spacecraft. Because the structural modeling was not accurate enough to predict how much the image quality was degraded by the micro-vibrations, we measured their transmission in a spacecraft-level test.
机译：HINODE，日语为“日出”，是专门用于观测太阳的航天器，于2006年发射升空，用于研究太阳的磁场及其爆炸能量如何在不同的大气层中传播。该航天器装有太阳光学望远镜（SOT），该望远镜具有50厘米直径的净孔径，并提供来自太空的一系列连续的衍射极限可见光图像。该望远镜是通过日本和美国之间的国际合作开发的。为了达到衍射极限性能，望远镜的热和结构模型在其开发阶段被广泛使用，以预测光学性能如何根据轨道上的热条件而变化。不仅是建模，我们还付出了很多努力来验证发射前地面测试中的光学性能。地面测试中的验证帮助我们发现了许多问题，例如与温度有关的焦点偏移，这些问题并非仅通过热结构建模才能识别。另一个关键问题是由机械陀螺仪和用于控制航天器姿态的动量轮产生的内部扰动引起的微振动。由于结构建模的准确性不足以预测微振动会降低多少图像质量，因此我们在航天器级测试中测量了它们的传输。

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