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Hypervelocity Impact (HVI)During 2003 and 2004, the Johnson Space Center's White Sands Testing Facility in Las Cruces, New Mexico conducted hypervelocity impact tests on the space shuttle wing leading edge. Hypervelocity impact tests were conducted to determine if Micro-Meteoroid/Orbital Debris impacts could be reliably detected and located using simple passive ultrasonic methods. The objective of Target Fg(RCC)-2 was to study hypervelocity impacts through the reinforced carbon-carbon (RCC) panels of the Wing Leading Edge. Fiberglass was used in place of RCC in the initial tests. Impact damage was detected using lightweight, low power instrumentation capable of being used in flight.
Document ID
20070031925
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Gorman, Michael R.
(Digital Wave Corp. Englewood, CO, United States)
Ziola, Steven M.
(Digital Wave Corp. Englewood, CO, United States)
Date Acquired
August 23, 2013
Publication Date
September 1, 2007
Subject Category
Composite Materials
Report/Patent Number
NASA/CR-2007-214885/VOL6
Funding Number(s)
CONTRACT_GRANT: NNL05AC19T
WBS: WBS 377816.06.03.03.06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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