Abstract
We present the optomechanical analysis results for a 1-m light-weight mirror system for a space telescope. The mirror has partially-closed pockets at the back surface and three square bosses at the rim for flexure mounting. The mirror design is optimized to satisfy the performance requirements under launch loads and a space environment. Mirror surface distortions due to gravity, assembly, isothermal loads, and moisture absorption are investigated. Mechanical safety issues such as mirror fracture, flexure yielding, and adhesive breakage are also examined.
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