Integrated modeling for determining launch survival and limitations of actuated, lightweight mirrors
Name
Cohan-2009-Integrated modeling for determining launch survival and limitations of actuated, lightweight mirrors.pdf
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481.28 KB
Format
Adobe PDF
Checksum (MD5)
52ab84105c6155e851d7e3f5e1aecd8e
Author(s)
Cohan, Lucy E.
Miller, David W.
Date Issued
July 2008
Journal
Proceedings of SPIE
Publisher
The International Society for Optical Engineering
Citation
Cohan, Lucy E., and David W. Miller. “Integrated modeling for determining launch survival and limitations of actuated lightweight mirrors.” Space Telescopes and Instrumentation 2008: Optical, Infrared, and Millimeter. Ed. Jacobus M. Oschmann et al. Marseille, France: SPIE, 2008. 70102I-12. © 2008 SPIE--The International Society for Optical Engineering
Version
Final published version
Abstract
The future of space telescopes lies in large, lightweight, segmented aperture systems. Segmented apertures eliminate manufacturability and launch vehicle fairing diameter as apertures size constraints. Low areal density, actuated segments allow the systems to meet both launch mass restrictions and on-orbit wavefront error requirements. These systems, with silicon carbide as a leading material, have great potential for increasing the productivity, affordability, and manufacturability of future space-based optical systems. Thus far, progress has been made on the manufacturing, sensing, actuation, and on-orbit control of such systems. However, relatively little attention has been paid to the harsh environment of launch. The launch environment may dominate aspects of the design of the mirror segments, with survivability requirements eliminating many potentially good designs. Integrated modeling of a mirror segment can help identify trends in mirror geometries that maximize launch performance, ensuring survivability without drastically over designing the mirror. A finite element model of a single, ribbed, actuated, silicon carbide mirror segment is created, and is used to develop a dynamic, state-space model, with launch load spectra as disturbance inputs, and mirror stresses as performance outputs. The parametric nature of this model allows analysis of many geometrically different mirror segments, helping to identify key parameters for launch survival. The modeling method described herein will enable identification of the design decisions that are dominated by launch, and will allow for development of launch-load alleviation techniques to further push the areal density boundaries in support of the creation of larger and lighter mirrors than previously possible.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Article is made available in accordance with the publisher's policy and may be subject to US copyright law. Please refer to the publisher's site for terms of use.
Persistent DSpace Link
DOI of Published Version
http://dx.doi.org/10.1117/12.789079
