Mirror lightweight for a spaceborne remote sensing instrument

Chia Yen Chan; Bo Kai Huang; Ting Ming Huang; Yi Cheng Chen; Fong Zhi Chen

doi:10.3319/TAO.2016.03.29.02(EOF5)

Mirror lightweight for a spaceborne remote sensing instrument

Chia Yen Chan, Bo Kai Huang, Ting Ming Huang, Yi Cheng Chen, Fong Zhi Chen

Department of Mechanical Engineering

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

The paper aims at obtaining the optimum lightweight configuration for a primary mirror (M1) with honeycomb patterns for a space satellite. The finite element analysis and Zernike polynomial fitting based on the Taguchi Method are applied to the whole optimization process. Geometrical control factors and levels were selected to minimize the ratio of various mass reduction ratios (MRRs) to the product of the corresponding maximum mirror structural deflection and optical surface peak-to-valley wavefront aberrations under launch accelerations. The optimum lightweight M1 with a MRR of 0.5 and a mass of 9.72 kg is attained and a mirror blank based on this design was manufactured. The performance of the optimum lightweight mirror is simulated and the simulation results satisfy the requirements of space specifications.

Original language	English
Pages (from-to)	139-147
Number of pages	9
Journal	Terrestrial, Atmospheric and Oceanic Sciences
Volume	28
Issue number	2
DOIs	https://doi.org/10.3319/TAO.2016.03.29.02(EOF5)
State	Published - Apr 2017

Keywords

Finite element analysis
Mass reduction ratio
Mirror lightweight
Space specification
Taguchi Method
Wavefront aberration

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10.3319/TAO.2016.03.29.02(EOF5)

Cite this

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title = "Mirror lightweight for a spaceborne remote sensing instrument",

abstract = "The paper aims at obtaining the optimum lightweight configuration for a primary mirror (M1) with honeycomb patterns for a space satellite. The finite element analysis and Zernike polynomial fitting based on the Taguchi Method are applied to the whole optimization process. Geometrical control factors and levels were selected to minimize the ratio of various mass reduction ratios (MRRs) to the product of the corresponding maximum mirror structural deflection and optical surface peak-to-valley wavefront aberrations under launch accelerations. The optimum lightweight M1 with a MRR of 0.5 and a mass of 9.72 kg is attained and a mirror blank based on this design was manufactured. The performance of the optimum lightweight mirror is simulated and the simulation results satisfy the requirements of space specifications.",

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AU - Chan, Chia Yen

AU - Huang, Bo Kai

AU - Huang, Ting Ming

AU - Chen, Yi Cheng

AU - Chen, Fong Zhi

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AB - The paper aims at obtaining the optimum lightweight configuration for a primary mirror (M1) with honeycomb patterns for a space satellite. The finite element analysis and Zernike polynomial fitting based on the Taguchi Method are applied to the whole optimization process. Geometrical control factors and levels were selected to minimize the ratio of various mass reduction ratios (MRRs) to the product of the corresponding maximum mirror structural deflection and optical surface peak-to-valley wavefront aberrations under launch accelerations. The optimum lightweight M1 with a MRR of 0.5 and a mass of 9.72 kg is attained and a mirror blank based on this design was manufactured. The performance of the optimum lightweight mirror is simulated and the simulation results satisfy the requirements of space specifications.

KW - Finite element analysis

KW - Mass reduction ratio

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KW - Space specification

KW - Taguchi Method

KW - Wavefront aberration

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Mirror lightweight for a spaceborne remote sensing instrument

Abstract

Keywords

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