Finite Element Modeling of Propellant and Inhibitor Interface Debonding

DOI

10.2991/mebe-15.2015.153How to use a DOI?

Keywords

Solid rocket motor; Interface debonding; Virtual crack closure technique; Cohesive zone model; Finite element method.

Abstract

Interface debonding is one of the most commonly observed failure in the Solid Rocket Motor(SRM). In order to investigate the debonding properties, the experiment was conducted by using double cantilever beam(DCB) specimen, and the strain energy release rate was obtained based on the load-displacement curve. Besides, two finite element methods, virtual crack closure technique(VCCT) and cohesive zone model(CZM), were employed to model the DCB debonding process. Finally, the load-displacement simulation curves obtained based on these models were compared with the experiment curves. The result shows that CZM can model the crack onset and propagation well. And, the VCCT approach, can model the propagation process, but overestimate the initial slope and load peak.

Copyright

© 2015, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Jia-quan Yu
AU  - Jian Zheng
AU  - Deng Jia
AU  - Chang-sheng Zhou
PY  - 2015/04
DA  - 2015/04
TI  - Finite Element Modeling of Propellant and Inhibitor Interface Debonding
BT  - Proceedings of the 2015 International Conference on Materials, Environmental and Biological Engineering
PB  - Atlantis Press
SP  - 665
EP  - 670
SN  - 2352-5401
UR  - https://doi.org/10.2991/mebe-15.2015.153
DO  - 10.2991/mebe-15.2015.153
ID  - Yu2015/04
ER  -