Development of critical technologies for high-precision space optics

高精度空间光学关键技术开发

• 批准号: 07554047
• 负责人: TSUNETA Saku
• 金额: $ 1.66万
• 依托单位: National Astronomical Observatory
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 1995
• 资助国家: 日本
• 起止时间: 1995 至 1996
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-07554047/
• 关键词: CFRP; graphite-epoxy composite material; graphite-cyanate composite material; composite material; light weight mirror; space precision structure; space telescope; large space mirror; グラファイト・シアネート・複合材料

We have performed the development and characterization of the graphite cyanate composite pipes for high-precision space optics such as the planned SOLAR-B satellite. Fundamental mechanical. thermal, and hygroscopic properties of unidirectional graphite-cyanate laminates were evaluated. The orientation of the fibers of a model pipe structure was designed to minimize the longitudinal thermal deformation. A model pike was fabricated based on the design, and we have performed series of measurements to evaluate the thermal expansion behavior (a few 0.1 ppm), the hygroscopic performance (10times better than the conventional graphite-epoxy composite), the thermal conductivity (111 w/mk), and the long-term stability. Excellent performance was verified, and the composite material was turned out to be the most promising candidate for the next-generation space-optics.We then proceeded to the design and fabrication of the ultra light-weight mirror that can be used as the primary mirror of a solar space telescope. The mirror consists of zerodure glass thin mirror supported by the graphite cyanate composite structure. The surface plate of the graphite cyanate composite structure that interfaces the glass mirror has an CTE matched to that of the glass over the surface, and the back-structure behind it has a large thermal conductivity to dump the heat load on the glass surface. The glass surface was polished to paraboloid with surface figure error as high as lambda/44 (lambda=633 nm), after the assembly of the structure (glass plate + composite material back structure). However, further investigation is needed to improve the long term stability of the surface figure.

我们已经完成了用于高精度空间光学器件（如计划中的SOLAR-B卫星）的氰酸石墨复合管的开发和表征。基础机械。评价了单向石墨-氰酸酯层压板的热和吸湿性能。设计了一个模型管道结构的纤维方向，以最小化纵向热变形。根据设计制造了一个模型派克，我们进行了一系列测量来评估热膨胀行为（0.1 ppm）、吸湿性能（比传统石墨-环氧树脂复合材料好10倍）、热导率（111 W/MK）和长期稳定性。在此基础上，我们进行了超轻太阳空间望远镜主镜的设计与制作。该反射镜由氰酸石墨复合结构支撑的零纯玻璃薄镜组成。与玻璃反射镜接合的氰酸石墨复合结构的表面板具有与表面上的玻璃的CTE匹配的CTE，并且其后面的背面结构具有大的导热性以将热负荷倾倒在玻璃表面上。在组装结构（玻璃板+复合材料背结构）之后，将玻璃表面抛光成抛物面，其表面形状误差高达λ/44（λ =633 nm）。然而，需要进一步的研究来提高表面图形的长期稳定性。