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 rms 10.2 nm and 10.8 nm under the gravity along optical axis direction and 5 °C uniform temperature rise respectively, the fundamental frequency of the mirror component is 268 Hz. Dynamics test shows that the first order natural frequency is 256 Hz, which shows an error less than 5% compared to FEA results.
Structural Design of Large Aperture Rectangular Mirror for Space Telescope
2012
4 Seiten
Aufsatz (Konferenz)
Englisch
Structural Design of Primary Mirror Subassembly for Space Telescope
Tema Archiv | 2013
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