Predictions of thermal buckling strengths of hypersonic aircraft sandwich panels using minimum potential energy and finite element methods
By: William L. Ko.
Contributors: NASA Dryden Flight Research Center.
Series: NASA technical memorandum -- 4643.
Publisher: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program; Available from the National Technical Information Service
Published: 1995
Place of publication: [Washington, D.C.]; [Springfield, Va
Language: eng
Format: Microform
Subjects: Aerodynamic heating.; Aerodynamic loads.; Aircraft design.; Applications programs (Computers); Aspect ratio.; Computer aided design.; Critical temperature.; Energy methods.; Finite element method.; Hypersonic aircraft.; Rayleigh-Ritz method.; Rectangular panels.; Sandwich structures.; Thermal buckling.
Notes: "NASA Dryden Flight Research Center."

Shipping List #: 96-0637-M.

Also available via Internet from the NASA web site. Address as of 6/21/05: http://www.nasa.gov/centers/dryden/pdf/88372main%5FH-2009.pdf; current access is available via PURL.

Microfiche. [Washington, D.C. : National Aeronautics and Space Administration, 1995]. 1 microfiche.