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Books on the topic 'Composite Honeycomb Sandwich Panels'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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1

Walker, Sandra P. Evaluation of composite honeycomb sandwich panels under compressive loads at elevated temperatures. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1998.

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2

M, McGowan David. Compression response of a sandwich fuselage keel panel with and without damage. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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3

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Optimization of composite sandwich cover panels subjected to compressive loadings. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

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4

Numerical and experimental investigation of hollow sphere structures in sandwich panels. Stafa-Zuerich: Trans Tech Publications, 2008.

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5

Chamis, C. C. Fiber composite sandwich thermostuctural behavior, computationalsimulation. [Washington, DC]: National Aeronautics and Space Administration, 1986.

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6

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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7

Jegley, Dawn C. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. Hampton, Va: Langley Research Center, 1992.

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8

United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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9

Ko, William L. Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. Edwards, Calif: Dryden Flight Research Facility, 1991.

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10

Viita-Aho, Tarvo. A finite element analysis of the response of composite sandwich panels to blast loading. Manchester: UMIST, 1992.

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11

Marshall, Rouse, and United States. National Aeronautics and Space Administration., eds. Response of composite fuselage sandwich side panels subjected to internal pressure and axial tension. [Washington, D.C: National Aeronautics and Space Administration, 1998.

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12

H, Jackson Raymond, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

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13

Marshall, Rouse, and United States. National Aeronautics and Space Administration., eds. Response of composite fuselage sandwich side panels subjected to internal pressure and axial tension. [Washington, D.C: National Aeronautics and Space Administration, 1998.

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14

Ko, William L. Compressive and shear buckling analysis of metal matrix composite sandwich panels under different thermal environments. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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15

Ko, William L. Open-mode debonding analysis of curved sandwich panels subjected to heating and cryogenic cooling on opposite faces. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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16

NASA Dryden Flight Research Center., ed. Open-mode debonding analysis of curved sandwich panels subjected to heating and cryogenic cooling on opposite faces. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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17

NASA Dryden Flight Research Center., ed. Open-mode debonding analysis of curved sandwich panels subjected to heating and cryogenic cooling on opposite faces. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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18

NASA Dryden Flight Research Center., ed. Open-mode debonding analysis of curved sandwich panels subjected to heating and cryogenic cooling on opposite faces. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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19

NASA Dryden Flight Research Center., ed. Open-mode debonding analysis of curved sandwich panels subjected to heating and cryogenic cooling on opposite faces. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1999.

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20

United States. National Aeronautics and Space Administration., ed. Damage Characteristics And Residual Strength Of Composite Sandwich Panels Impacted With And Without A... NASA/TM-1998-208122... Oct. 26, 1998. [S.l: s.n., 1999.

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21

McGowan, David M. Damage characteristics and residual strength of composite sandwaich panels impacted with and without compression loading: Presented at the 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, session no. 15--damage tolerance : Long Beach, California, April 20-23, 1998. [Washington, DC: National Aeronautics and Space Administration, 1998.

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22

McGowan, David M. Damage characteristics and residual strength of composite sandwich panels impacted with and without compression loading: Presented at the 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, session no. 15-damage tolerance : Long Beach, California, April 20-23, 1998. [Washington, DC: National Aeronautics and Space Administration, 1998.

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23

Keller, Thomas. Use of fibre reinforced polymers in bridge construction. Zurich, Switzerland: International Association for Bridge and Structural Engineering (IABSE), 2003. http://dx.doi.org/10.2749/sed007.

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<p>The aim of the present Structural Engineering Document, a state-of-the-art report, is to review the progress made worldwide in the use of fibre rein­forced polymers as structural components in bridges until the end of the year 2000.<p> Due to their advantageous material properties such as high specific strength, a large tolerance for frost and de-icing salts and, furthermore, short installation times with minimum traffic interference, fibre reinforced polymers have matured to become valuable alternative building materials for bridge structures. Today, fibre reinforced polymers are manufactured industrially to semi-finished products and ccimplete structural components, which can be easily and quickly installed or erected on site.<p> Examples of semi-finished products and structural components available are flexible tension elements, profiles stiff in bending and sandwich panels. As tension elements, especially for the purpose of strengthening, strips and sheets are available, as weil as reinforcing bars for concrete reinforcement and prestressing members for internal prestressing or external use. Profiles are available for beams and columns, and sandwich constructions especially for bridge decks. During the manufacture of the structural components fibre-optic sensors for continuous monitoring can be integrated in the materials. Adhesives are being used more and more for joining com­ponents.<p> Fibre reinforced polymers have been used in bridge construction since the mid-1980s, mostly for the strengthening of existing structures, and increas­ingly since the mid-1990s as pilot projects for new structures. In the case of new structures, three basic types of applications can be distinguished: concrete reinforcement, new hybrid structures in combination with traditional construction materials, and all-composite applications, in which the new materials are used exclusively.<p> This Structural Engineering Document also includes application and research recommendations with particular reference to Switzerland.<p> This book is aimed at both students and practising engineers, working in the field of fibre reinforced polymers, bridge design, construction, repair and strengthening.
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24

An examination of impact damage in glass/phenolic and aluminum honeycomb core composite panels. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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25

Compression response of a sandwich fuselage keel panel with and without damage. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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26

Okada, Ryo. Peel delamination of honeycomb sandwich panels. 2005.

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27

National Aeronautics and Space Administration (NASA) Staff. Optimization of Composite Sandwich Cover Panels Subjected to Compressive Loadings. Independently Published, 2018.

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28

Fiedler, Thomas. Numerical and Experimental Investigation of Hollow Sphere Structures in Sandwich Panels. Trans Tech Publications, Limited, 2008.

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29

Study of compression-loaded and impact-damaged structurally efficient graphite-thermoplastic trapezoidal-corrugation sandwich and semisandwich panels. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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30

Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

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31

Combined-load buckling behavior of metal-matrix composite sandwich panels under different thermal environments. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1991.

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32

National Aeronautics and Space Administration (NASA) Staff. Combined-Load Buckling Behavior of Metal-Matrix Composite Sandwich Panels under Different Thermal Environments. Independently Published, 2018.

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33

National Aeronautics and Space Administration (NASA). Damage Tolerance Comparison of Composite Hat-Stiffened and Honeycomb Sandwich Structure for Launch Vehicle Interstage Applications. Independently Published, 2020.

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34

Sullivan, Patrick D. An analysis of symmetric reinforcement of graphite/epoxy honeycomb sandwich panels with a circular cutout under uniaxial compressive loading. 1985.

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