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A multilayered thick cylindrical shell under internal pressure and thermal loads applicable to solid propellant rocket motors

https://doi.org/10.1007/s100100000042
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inferred← citeshttps://doi.org/10.2139/ssrn.4750286openalex-extracted
Herrmann Finite Elements for Viscoelastic Analysis with Mechanical and Transient Thermal Loads
inferred← citeshttps://doi.org/10.1016/j.ast.2016.09.020openalex-snapshot
Effects of liner properties on the stress and strain along liner/propellant interface in solid rocket motor
inferred← citeshttps://doi.org/10.1016/j.ijpvp.2013.06.001openalex-snapshot
Development of efficient finite elements for structural integrity analysis of solid rocket motor propellant grains
inferred← citeshttps://doi.org/10.1016/j.matpr.2019.01.020openalex-snapshot
Mathematical Model of One and Two-Step Methods Calculation of Thermal Fields and Stress-Strain State of Multilayer Cylindrical Constructions
inferred← citeshttps://doi.org/10.1179/026708402225007131openalex-snapshot
Tensile fracture of HTPB based propellant specimens
inferred← citeshttps://doi.org/10.21935/tls.v2i1.108openalex-snapshot
Mathematic model for describing the stress-tension behavior of an autoclave with integrated heating element
inferred← citeshttps://doi.org/10.3390/polym15041019openalex-snapshot
Numerical Analysis of Curing Residual Stress and Strain in NEPE Propellant Grain
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