固体推进剂黏弹性参数的确定及细观损伤演化

doi:10.12382/bgxb.2022.1256

摘要/Abstract

摘要：

固体推进剂力学模型参数的准确性对其宏观力学响应预测具有重要的意义,为解耦标定固体推进剂非线性黏弹性模型参数,提出一种基于台阶应力松弛试验的模型参数确定方法。通过台阶应力松弛平衡响应确定固体推进剂弹性部分参数,通过小变形下的应力松弛确定无量纲松弛模量,分析一种固体推进剂力学响应。研究结果表明:固体推进剂在台阶应力松弛及单轴拉伸条件下的力学性能预测结果与试验结果吻合,验证了所提方法的有效性;由于平衡响应包含损伤,采用该方法标定的参数可用于预测含损伤固体推进剂力学响应。在此基础上,提出一种基于推进剂模型参数标定等效黏合剂力学参数的方法,并通过引入基于黏弹性脱湿准则的相界面模型建立代表性体积单元计算模型,实现在宽应变(~100%)范围内推进剂脱湿损伤分析,为推进剂宏观力学性能预测及细观损伤演化分析提供了支撑。

关键词: 黏弹性模型, 参数标定, 台阶应力松弛, 等效黏合剂, 相界面模型, 固体推进剂

Abstract:

Accurately determining the model parameters of solid propellant is of great importance for the prediction of its macroscopic mechanical response. A parameter determination method based on multi-step stress relaxation experiments is proposed to calibrate the nonlinear viscoelastic model parameters of solid propellants uncoupled. The proposed method determines the parameters for the elastic part by multi-step stress relaxation equilibrium response and the dimensionless relaxation modulus by stress relaxation in the case of small deformation. The proposed method is then used to analyze the mechanical response of solid propellants. The results show that the predicted results of multi-step stress relaxation and uniaxial tension under different strain rates of the material agree with the experimental results, which verifies the validity of the proposed method. Moreover, since the equilibrium response includes damage, the parameters calibrated by the proposed method can be used to predict the mechanical response of solid propellant with damage. Consequently, the parameters of the composite matrix are derived from the determined parameters of solid propellant, and a viscoelastic debonding criterion-based interface model is introduced to establish a representative volume element (RVE) model, thus achieving the interface debonding analysis in a wide range of strain (~100%), which provides an effective method supporting the prediction of mechanical response and microstructural damage evolution of solid propellants.

Key words: viscoelastic model, parameter calibration, multi-step stress relaxation, composite matrix, interface model, solid propellant

中图分类号:

TB333

乌布力艾散·麦麦提图尔荪, 吴艳青, 侯晓, 尹欣梅, 张鑫. 固体推进剂黏弹性参数的确定及细观损伤演化[J]. 兵工学报, 2024, 45(4): 1038-1046.

WUBULIAISAN Maimaitituersun, WU Yanqing, HOU Xiao, YIN Xinmei, ZHANG Xin. On the Determination of Viscoelastic Model Parameters and Microstructural Damage Evolution of Solid Propellants[J]. Acta Armamentarii, 2024, 45(4): 1038-1046.

图/表 12

图1 黏弹性材料响应示意图

Fig.1 Stress response of a hyper-viscoelastic solid

图2 基于台阶应力松弛标定黏弹性参数

Fig.2 Determination of viscoelastic model parameters through multi-step stress relaxation test

表1 NEPE推进剂基本组分

Table 1 Components of NEPE propellant

组分	GAP体系	AP	CL-20	Al	其他
质量分数/%	24.6	10.5	42.5	16.9	5.5
颗粒尺寸/μm		50~200	10~100	10

图3 NEPE推进剂单轴拉伸试验

Fig.3 Uniaxial tensile test of NEPE propellant

图4 NEPE推进剂台阶应力松弛试验及预测结果

Fig.4 Multi-step stress relaxation and predicted results of NEPE propellant

表2 NEPE推进剂无量纲应力松弛模量

Table 2 Dimensionless stress relaxation coefficients for NEPE propellant

i	m_i	τ_i/s
1	0.595	1.0
2	0.051	9.0
3	0.043	87.0
∞	0.311

图5 不同应变率下NEPE推进剂试验结果与仿真预测对比

Fig.5 Comparison between experimental and numerical results of NEPE propellant

图6 NEPE推进剂RVE模型

Fig.6 Packing RVE of NEPE propellant

图7 无损伤条件下NEPE推进剂仿真与试验结果对比

Fig.7 Comparison between experimental and simulated results of NEPE propellant before damage initiation

图8 变形过程中的能量分配关系示意图

Fig.8 Diagrammatic sketch of energy decomposition during deformation

图9 NEPE推进剂试验结果与细观仿真预测对比

Fig.9 Comparision between test and predicted results of NEPE propellant

图10 RVE中损伤演化过程

Fig.10 Damage evolution in the RVE

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