Thermodynamics-Based Viscoelastic-Viscodamage Constitutive Model for Solid Propellant

被引：0

作者：

Li H. ^{[1
]}

Fan X.-G. ^{[1
]}

Xu J.-S. ^{[1
]}

Chen X. ^{[1
]}

Liu J.-M. ^{[1
]}

机构：

[1] School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2022年 / 43卷 / 10期

关键词：

Constitutive model; Damage; Mechanical performance; Solid propellant; Viscoelasticity;

D O I：

10.13675/j.cnki.tjjs.210481

中图分类号：

学科分类号：

摘要：

To describe the nonlinear mechanical properties of solid propellant under various strain rates and confining pressure conditions，through assumping that nonlinear mechanical properties were induced by the damage，and based on the framework of irreversible thermodynamic，a new viscoelastic-viscodamage constitutive model was firstly developed. In the proposed viscodamage model，the linear viscoelasticity strain energy density was used as the damage driving force，and the effects of damage history，strain rate and confining pressure on the growth of damage were considered. Then，through the experimental data of the literature，the model parameters identification，validation and the relative errors analysis of one-dimensional version of the constitutive model were carried out. Based on the time-pressure superposition principle，the master curve of damage initiation parameter S0 was constructed. Finally，the uniaxial tension tests of NEPE propellant were conducted to verify the ap- plicability of the developed constitutive model to the large-deformation nonlinear mechanical properties of current solid propellant. The results show that the damage initiation parameter S0 increases with the increasing of confining pressure and strain rate. With the coupled effects of confining pressure and strain rate，the value of S0 at relative atmospheric pressure 5.516MPa and 0.24s-1 is 10.7 times of its value at relative atmospheric pressure 0MPa and 6×10-4s-1. In addition，the maximum relative error of maximum strength of the model predictions is 6.15% for HTPB propellant. The model predictions are in good agreement with the two kinds of experimental results，indicating that the established constitutive model can well predict the mechanical responses of HTPB propellant under different strain rates and confining pressure conditions，as well as the large-deformation nonlinear mechanical behaviors of current NEPE propellant. It can provide a theoretical basis for the numerical analysis of the structural integrity of solid propellant grains under ignition pressurization loading. © 2022 Journal of Propulsion Technology. All rights reserved.

引用

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