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The Use, Evolution and Lessons Learnt of Deployable Static Solar Array MechanismsThis paper focuses on the mechanisms incorporated into SSTL's static deployable arrays; namely the sprung-hinges and hold down and release mechanism (HDRM). Combined, the HDRM and hinges form the hold down release system (HDRS). The deployable static solar array HDRS has been successfully used on several missions, first launched upon the DMC-CFESAT spacecraft in 2007 for a U.S. customer (Figure 1), and later used on DMC-UK2 and EXACTVIEW-1 launched in 2009 and 2012, respectively. The simple, robust and low-cost solution HDRS has been evident in allowing missions to satisfy an ever increasing power demand, allowing the solar arrays to increase in size and have a preferable sun angle for increased cell efficiency. The system is now being employed on the first mission out of SSTL's U.S. office (SST-US) on the Orbital Test Bed platform. This paper shall cover details of the original design and development program, problems incurred on latter missions, and evolution of the HDRS for the present Orbital Test Bed mission. Both the original development and recent evolutions have taken place in rapid timescales, to satisfy the high-turnaround of SSTL missions.
Document ID
20150004077
Acquisition Source
Goddard Space Flight Center
Document Type
Conference Paper
Authors
Ferris, Mark
(Surrey Satellite Technology Ltd. Guildford, United Kingdom)
Haslehurst, Andrew
(Surrey Satellite Technology Ltd. Guildford, United Kingdom)
Date Acquired
April 2, 2015
Publication Date
May 1, 2014
Publication Information
Publication: The 42nd Aerospace Mechanism Symposium
Subject Category
Mechanical Engineering
Structural Mechanics
Distribution Limits
Public
Copyright
Public Use Permitted.
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