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)-1 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.
Hypervelocity Impact (HVI), Volume 5, WLE High Fidelity Specimen Fg(RCC)-1
2007
178 pages
Report
No indication
English
Unmanned Spacecraft , Manned Spacecraft , Composite Materials , Carbon-carbon composites , Hypervelocity impact , Impact damage , Impact tests , Leading edges , Wings , Space shuttles , Micrometeoroids , Flat plates , Glass fibers , Sensors , Electromagnetic interference , Kinetic energy , Space debris
NTRS | 2007
|NTRS | 2007
|NTIS | 1991
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