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Proceedings Paper

Flight hardware for the Hubble Space Telescope solar array damper
Author(s): Joseph R. Maly; Satya M. Anandakrishnan; Scott C. Pendleton; E. Shade; J. W. Sills Jr.
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Paper Abstract

The Hubble Space Telescope (HST) is currently operating with two flexible solar arrays (or 'wings'), referred to as SA2, that were installed during Servicing Mission 1. These flexible solar arrays are to be replaced with two rigid solar arrays, SA3, during Servicing Mission 3B which is currently scheduled for May, 2001. The key requirements for these arrays are to: (1) increase long term power to support the HST mission, (2) improve the jitter performance while maintaining stability margin requirements, and (3) withstand re-boost loads without astronaut or ground intervention. Analysis of the original SA3 design showed that the Pointing Control System (PCS) stability margin requirements would be violated because of the modal characteristics of the SA3 fundamental bending modes. One of the options to regain the stability margins was to increase the damping of these modes. Damping of 1.5% of critical of the SA3 fundamental bending modes, at the HST system level, is needed to meet stability margin requirements. Therefore, the development of a discrete damping device was undertaken to provide adequate damping of the SA3 fundamental bending modes for all operational conditions.

Paper Details

Date Published: 27 April 2000
PDF: 12 pages
Proc. SPIE 3989, Smart Structures and Materials 2000: Damping and Isolation, (27 April 2000); doi: 10.1117/12.384570
Show Author Affiliations
Joseph R. Maly, CSA Engineering, Inc. (United States)
Satya M. Anandakrishnan, Lockheed Martin Technical Operations (United States)
Scott C. Pendleton, CSA Engineering, Inc. (United States)
E. Shade, Lockheed Martin Technical Operations (United States)
J. W. Sills Jr., Lockheed Martin Technical Operations (United States)

Published in SPIE Proceedings Vol. 3989:
Smart Structures and Materials 2000: Damping and Isolation
T. Tupper Hyde, Editor(s)

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