Progressive Failure Studies of Composite Panels with and Without Cutouts Final Report ... Nasa PDF Download
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723748691
Category : Science
Languages : en
Pages : 28
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Book Description
Progressive failure analyses results are presented for composite panels with and without a cutout and subjected to in-plane shear loading and compression loading well into their postbuckling regime. Ply damage modes such as matrix cracking, fiber-matrix shear, and fiber failure are modeled by degrading the material properties. Results from finite element analyses are compared with experimental data. Good agreement between experimental data and numerical results are observed for most structural configurations when initial geometric imperfections are appropriately modeled.Jaunky, Navin and Ambur, Damodar R. and Davila, Carlos G. and Hilburger, Mark and Bushnell, Dennis M. (Technical Monitor)Langley Research CenterCOMPOSITE STRUCTURES; FAILURE ANALYSIS; BUCKLING; DYNAMIC STRUCTURAL ANALYSIS; COMPRESSION LOADS; FINITE ELEMENT METHOD; FIBER-MATRIX INTERFACES
Author: Navin Jaunky
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Book Description
Progressive failure analyses results are presented for composite panels with and without a cutout and subjected to in-plane shear loading and compression loading well into their postbuckling regime. Ply damage modes such as matrix cracking, fiber-matrix shear, and fiber failure are modeled by degrading the material properties. Results from finite element analyses are compared with experimental data. Good agreement between experimental data and numerical results are observed for most structural configurations when initial geometric imperfections are appropriately modeled.
Author: Damodar R. Ambur
Publisher: DIANE Publishing
ISBN: 1428995536
Category :
Languages : en
Pages : 25
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721520404
Category :
Languages : en
Pages : 26
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Book Description
Experimental and analytical results are presented for progressive failure of stiffened composite panels with and without a notch and subjected to in plane shear loading well into their postbuckling regime. Initial geometric imperfections are included in the finite element models. Ply damage modes such as matrix cracking, fiber-matrix shear, and fiber failure are modeled by degrading the material properties. Experimental results from the test include strain field data from video image correlation in three dimensions in addition to other strain and displacement measurements. Results from nonlinear finite element analyses are compared with experimental data. Good agreement between experimental data and numerical results are observed for the stitched stiffened composite panels studied. Ambur, Damodar R. and Jaunky, Navin and Hilburger, Mark W. and Bushnell, Dennis M. (Technical Monitor) Langley Research Center NASA/CR-2002-211757, NAS 1.26:211757, ICASE-2002-24
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1572
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781729236956
Category : Science
Languages : en
Pages : 48
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Book Description
A method for analysis of progressive failure in the Computational Structural Mechanics Testbed is presented in this report. The relationship employed in this analysis describes the matrix crack damage and fiber fracture via kinematics-based volume-averaged variables. Damage accumulation during monotonic and cyclic loads is predicted by damage evolution laws for tensile load conditions. The implementation of this damage model required the development of two testbed processors. While this report concentrates on the theory and usage of these processors, a complete list of all testbed processors and inputs that are required for this analysis are included. Sample calculations for laminates subjected to monotonic and cyclic loads were performed to illustrate the damage accumulation, stress redistribution, and changes to the global response that occur during the load history. Residual strength predictions made with this information compared favorably with experimental measurements. Lo, David C. and Coats, Timothy W. and Harris, Charles E. and Allen, David H. Langley Research Center RTOP 538-02-10-01
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721024797
Category :
Languages : en
Pages : 56
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Book Description
The present document is a final technical report under the NCC-1-233 research program (dated September 15, 1998; see Appendix 5) carried out within co-operation between United States'NASA Langley RC and Russia's Goskomoboronprom in aeronautics, and continues similar programs, NCCW-73, NCC-1-233 and NCCW 1-233 accomplished in 1996, 1997, and 1998, respectively. The report provides results of "The study of stability of compression-loaded multispan composite panels upon failure of elements binding it to panel supports"; these comply with requirements established at TsAGI on 24 March 1998 and at NASA on 15 September 1998.Zamula, G. N. and Ierusalimsky, K. M. and Fomin, V. P. and Grishin, V. I. and Kalmykova, G. S.Langley Research CenterSTABILITY TESTS; COMPRESSION TESTS; LOAD TESTS; COMPOSITE STRUCTURES; PANELS; FAILURE; BUCKLING; LOAD DISTRIBUTION (FORCES)
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722644987
Category :
Languages : en
Pages : 46
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Book Description
A method for analysis of progressive failure in the Computational Structural Mechanics Testbed is presented in this report. The relationship employed in this analysis describes the matrix crack damage and fiber fracture via kinematics-based volume-averaged variables. Damage accumulation during monotonic and cyclic loads is predicted by damage evolution laws for tensile load conditions. The implementation of this damage model required the development of two testbed processors. While this report concentrates on the theory and usage of these processors, a complete list of all testbed processors and inputs that are required for this analysis are included. Sample calculations for laminates subjected to monotonic and cyclic loads were performed to illustrate the damage accumulation, stress redistribution, and changes to the global response that occur during the load history. Residual strength predictions made with this information compared favorably with experimental measurements. Lo, David C. and Coats, Timothy W. and Harris, Charles E. and Allen, David H. Langley Research Center RTOP 538-02-10-01...
Author: Charles E. Harris
Publisher:
ISBN:
Category : Airframes
Languages : en
Pages : 42
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Book Description
