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Flutter Analysis of the Thermal Protection Layer on the NASA HIADA combination of classical plate theory and a supersonic aerodynamic model is used to study the aeroelastic flutter behavior of a proposed thermal protection system (TPS) for the NASA HIAD. The analysis pertains to the rectangular configurations currently being tested in a NASA wind-tunnel facility, and may explain why oscillations of the articles could be observed. An analysis using a linear flat plate model indicated that flutter was possible well within the supersonic flow regime of the wind tunnel tests. A more complex nonlinear analysis of the TPS, taking into account any material curvature present due to the restraint system or substructure, indicated that significantly greater aerodynamic forcing is required for the onset of flutter. Chaotic and periodic limit cycle oscillations (LCOs) of the TPS are possible depending on how the curvature is imposed. When the pressure from the base substructure on the bottom of the TPS is used as the source of curvature, the flutter boundary increases rapidly and chaotic behavior is eliminated.
Document ID
20130013396
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Goldman, Benjamin D.
(Duke Univ. Durham, NC, United States)
Dowell, Earl H.
(Duke Univ. Durham, NC, United States)
Scott, Robert C.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 27, 2013
Publication Date
March 25, 2013
Subject Category
Aerodynamics
Report/Patent Number
NF1676L-16134
Meeting Information
Meeting: 22nd AIAA Aerodynamic Decelerator Systems Technology Conference
Location: Daytona Beach, FL
Country: United States
Start Date: March 25, 2013
End Date: March 28, 2013
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.08
Distribution Limits
Public
Copyright
Public Use Permitted.
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