Books on the topic 'Energy strain release rate'

Zimmerman, Richard S. Strain energy release rate as a function of temperature and preloading history utilizing the edge delamination fatigue test method. [Washington, DC: National Aeronautics and Space Administration, 1989.

Salpekar, Satish A. Combined effect of matrix cracking and stress-free edge on delamination. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

Li, Jian. Simplified data reduction methods for the ECT test for mode III interlaminar fracture toughness. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

Blais, Randy. Rockburst control in cut-and-fill mining by monitoring energy release rate. Sudbury, Ont: Laurentian University, School of Engineering, 1986.

N, Shivakumar K., and Langley Research Center, eds. Strain-energy release rate analysis of a laminate with a postbuckled delamination. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Convergence of strain energy release rate components for edge-delaminated composite laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Strain-energy release rate analysis of a laminate with a postbuckled delamination. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

S, Raju I., O'Brien T. Kevin, Langley Research Center, and United States. Army Aviation Research and Technology Activity., eds. Strain energy release rate analysis of delamination in a tapered laminate subjected to tension load. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

J, Minguet Pierre, O'Brien T. Kevin, and Langley Research Center, eds. A method for calculating strain energy release rates in preliminary design of composite skin/stringer debonding under multi-axial loading. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

A method for calculating strain energy release rates in preliminary design of composite skin/stringer debonding under multi-axial loading. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1999.

S, Raju I., O'Brien T. Kevin, and Langley Research Center, eds. Strain-energy-release rate analysis of the end-notched flexure specimen using the finite-element method. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

S, Raju I., O'Brien T. Kevin, and Langley Research Center, eds. Strain-energy-release rate analysis of the end-notched flexure specimen using the finite-element method. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

S, Raju I., O'Brien T. Kevin, and Langley Research Center, eds. Strain-energy-release rate analysis of the end-notched flexure specimen using the finite-element method. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Residual thermal and moisture influences on the strain energy release rate analysis of local delaminations from matrix cracks. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

Simple formulas for strain-energy release rates with higher order and singular finite elements. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1987.

Center, Langley Research, ed. Q3DG, a computer program for strain-energy-release rates for delamination growth in composite laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1986.

K, Binienda Wieslaw, Kreider K. L, and Lewis Research Center, eds. Analysis of multiple cracks in an infinite functionally graded plate. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1999.

K, Binienda Wieslaw, Kreider K. L, and Lewis Research Center, eds. Analysis of multiple cracks in an infinite functionally graded plate. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1999.

Analysis of interface crack branching. [Washington, D.C.]: National Aeronautics and Space Administration, 1989.

United States. National Aeronautics and Space Administration., ed. Analysis of delamination related fracture processes in composites: Semi-annual report. [Washington, DC: National Aeronautics and Space Administration, 1992.

United States. National Aeronautics and Space Administration., ed. Analysis of delamination related fracture processes in composites. [Washington, DC: National Aeronautics and Space Administration, 1992.

United States. National Aeronautics and Space Administration, ed. Analysis of delamination related fracture processes in composites: Preliminary final report. [Washington, DC: National Aeronautics and Space Administration, 1988.

United States. National Aeronautics and Space Administration., ed. Analysis of delamination related fracture processes in composites: Preliminary final report. [Washington, DC: National Aeronautics and Space Administration, 1988.

M, Arnold Steven, and United States. National Aeronautics and Space Administration., eds. Driving force analysis in an infinite anisotropic plate with multiple crack interactions. [Washington, DC]: National Aeronautics and Space Administration, 1995.

Combined effect of matrix cracking and stress-free edge on delamination. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1990.

Final technical report for computational simulation of composite behavior: NASA grant number NAG3-1264 : grant duration, November 30, 1991 to November 2, 1996. [Washington, DC: National Aeronautics and Space Administration, 1997.

Analysis of a generally oriented crack in a functionally graded strip sandwiched between two homogeneous half planes. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

K, Binienda W., Kreider K, and NASA Glenn Research Center, eds. Analysis of a generally oriented crack in a functionally graded strip sandwiched between two homogeneous half planes. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 1999.

Strain energy release rates of composite interlaminar end-notch and mixed mode fracture: A subulaminate/ply [i.e. sublaminate/ply] level analysis and a computer code. [Washington, D.C.]: National Aeronautics and Space Administration, 1987.

Kevin, O'Brien T., Rousseau Carl Q, and United States. National Aeronautics and Space Administration., eds. Fatigue life methodology for tapered composite flexbeam laminates. [Washington, DC: National Aeronautics and Space Administration, 1997.

Kevin, O'Brien T., Rousseau Carl Q, and Langley Research Center, eds. Fatigue life methodology for tapered composite flexbeam laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Kevin, O'Brien T., Rousseau Carl Q, and Langley Research Center, eds. Fatigue life methodology for tapered composite flexbeam laminates. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

Kevin, O'Brien T., Rousseau Carl Q, and United States. National Aeronautics and Space Administration., eds. Fatigue life methodology for tapered composite flexbeam laminates. [Washington, DC: National Aeronautics and Space Administration, 1997.

Eugene, Murr Lawrence, Staudhammer Karl P, Meyers Marc A, and EXPLOMET '85: International Conference on Metallurgical Applications of Shock-Wave and High-Strain-Rate Phenomena (1985 : Portland, Or.), eds. Metallurgical applications of shock-wave and high-strain-rate phenomena. New York: M. Dekker, 1986.

Staudhammer, Karl P., Marc A. Meyers, and Lawrence Eugene Murr. Metallurgical Applications of Shock-wave and High-strain Rate Phenomena (Mechanical Engineering (Marcell Dekker)). CRC, 1986.

Houillier, Pascal. Magnesium homeostasis. Edited by Robert Unwin. Oxford University Press, 2015. http://dx.doi.org/10.1093/med/9780199592548.003.0027.