Structural Design of Large Aperture Rectangular Mirror for Space Telescope

Zhi Lai Li

doi:10.4028/www.scientific.net/AMM.256-259.855

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 256-259Structural Design of Large Aperture Rectangular...

Structural Design of Large Aperture Rectangular Mirror for Space Telescope

Abstract:

Structural design of large aperture mirror is one of the key technologies for space telescope development. To meet the requirements of high stiffness, strength and thermal dimensional stability, some factors such as support scheme, materials selection, lightweight design and flexible support design were taken into account. The three supports location of the mirror was determined according to the modal analytical solution. By adjusting the parameters of flexure hinge, influences of gravity, assembly stress and thermal stress on the mirror were reduced obviously. Finite element analysis (FEA) results indicate that the surface accuracy reach to rms10.2nm and 10.8nm under the gravity along optical axis direction and 5°C uniform temperature rise respectively, the fundamental frequency of the mirror component is 268Hz. Dynamics test shows that the first order natural frequency is 256Hz, which shows an error less than 5% compared to FEA results.

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Periodical:

Applied Mechanics and Materials (Volumes 256-259)

Pages:

855-858

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.256-259.855

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Online since:

December 2012

Authors:

Zhi Lai Li

Keywords:

Finite Element Analysis (FEA), Flexure Hinge, Modal Analysis, SiC Mirror, Space Telescope

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