by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va .
Written in English
|Statement||Pascal K. Gotsis and C.C. Chamis, Levon Minnetyan.|
|Series||NASA technical memorandum -- 107231.|
|Contributions||Chamis, C. C., Minnetyan, Levon., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Get this from a library! Progressive fracture of fiber composite build-up structures. [Pascal K Gotsis; C C Chamis; Levon Minnetyan; United States. National Aeronautics and Space Administration.]. Progressive fracture of fiber composite build-up structures (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Pascal K Gotsis; C C Chamis; Levon Minnetyan; United States. National Aeronautics and Space Administration. An integrated computer code, CODSTRAN, was augmented for the simulation of the progressive damage and fracture of built-up composite structures under mechanical loading. Results show that damage initiation and progression have significant effect on the structural response. Computational methods for simulating progressive fracture in fiber composite structures are presented. These methods are integrated into a computer code of modular form. The modules include composite mechanics, finite element analysis, and fracture by: 7.
Structural ANalysis). It is used in the present paper to evaluate the global fracture of four composite shell problems and one composite built-up structure. Results show that the composite shells and the built-up composite structure global fracture are enhanced when internal pressure is combined with shear loads. I. IntroductionFile Size: 5MB. Keywords: micro mechanics, laminate theory, thin shells, thick shells, built-up structures, non-linearities. 1 Introduction The global fracture behavior of fiber composite structures has become of. Investigation of progressive damage and fracture in laminated composites using the smeared crack approach. Determining Effective Interface Fracture Properties of 3D Fiber Reinforced Foam Core Sandwich Structures. 1 January Recommended. Fiber fracture is often accompanied by debonding of the fiber–matrix interface in the neighborhood of the fiber fractures. Three types of behavior need to be considered when modeling UD composites. At relatively low applied loads, there is no microstructural damage or matrix yielding/plasticity.
The generic types of composite structural fracture illustrated in this report are: (1) single and combined mode fracture in beams, (2) laminate free-edge delamination fracture, (3) laminate center flaw progressive fracture, and (4) plate and shell structural Size: KB. Fracture: Conventionally, fracture is understood to be “breakage” of material, or at a more fundamental level, breakage of atomic bonds, manifesting itself in formation of internal surfaces. Examples of fracture in composites are fiber breakage, cracks in matrix, fiber/matrix debonds, and separation of bonded plies (delamination). Progressive damage and fracture of adhesively bonded graphite/epoxy composite structures are evaluated via computational simulation. Load induced damage in both the adhesive bond and the adjoining laminate is considered. An integrated computer code is used for the simulation of structural degradation under by: 3. ELSEVIER Theoretical and Applied Fracture Mechanics 25 () theoretical and applied hacture mechanics Progressive fracture of polymer matrix composite structures C.C. Chamis a,*, P.L.N. Murthy a, L. Minnetyan b a National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio , USA b Clarkson University, Potsdam, New York , USA Abstract An Cited by: