NDLI: Computational simulation of hot composites structures

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Computational simulation of hot composites structures

Content Provider	NASA Technical Reports Server (NTRS)
Author	Chamis, Christos C. Singhal, S. N. Murthy, P. L. N.
Copyright Year	1991
Description	Three different computer codes developed in-house are described for application to hot composite structures. These codes include capabilities for: (1) laminate behavior (METCAN); (2) thermal/structural analysis of hot structures made from high temperature metal matrix composites (HITCAN); and (3) laminate tailoring (MMLT). Results for select sample cases are described to demonstrate the versatility as well as the application of these codes to specific situations. The sample case results show that METCAN can be used to simulate cyclic life in high temperature metal matrix composites; HITCAN can be used to evaluate the structural performance of curved panels as well as respective sensitivities of various nonlinearities, and MMLT can be used to tailor the fabrication process in order to reduce residual stresses in the matrix upon cool-down.
File Size	697246
Page Count	20
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910009917
Archival Resource Key	ark:/13960/t09w5bx15
Language	English
Publisher Date	1991-01-01
Access Restriction	Open
Subject Keyword	Composite Materials Cooling Life Durability Curved Panels Computerized Simulation Laminates Finite Element Method Fabrication Temperature Effects Metal Matrix Composites Applications Programs Computers Thermal Analysis Composite Structures Residual Stress Structural Analysis Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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