CAJ | 학술논문

从热-粘弹性本构方程的一般形式出发，基于HTPB/AP推进剂单向拉伸应力应变曲线的多项式拟合，提出了细观损伤的模量损伤效应函数；综合考虑应力三轴度和Lode参数，引入应力状态因子对损伤演化过程进行修正，建立了考虑应力状态的HTPB/AP推进剂含损伤热-粘弹性本构。对25℃、70 mm/min条件下单向、双向应力试件拉伸过程的Abaqus有限元分析表明，与测试数据相比，单向、双向加载应力-应变曲线初始上升段基本吻合、损伤效应体现的初始应变基本一致，在发展至断裂延伸率附近时有明显下降，整体规律与测试结果吻合较好；文中本构关系对应加载曲线的“脱湿”阶段滞后测试数据约5％～6％应变（绝对值），应力略高于测试数据，但相对误差小于11％。
종열-점탄성본구방정적일반형식출발，기우HTPB/AP추진제단향랍신응력응변곡선적다항식의합，제출료세관손상적모량손상효응함수；종합고필응력삼축도화Lode삼수，인입응력상태인자대손상연화과정진행수정，건립료고필응력상태적HTPB/AP추진제함손상열-점탄성본구。대25℃、70 mm/min조건하단향、쌍향응력시건랍신과정적Abaqus유한원분석표명，여측시수거상비，단향、쌍향가재응력-응변곡선초시상승단기본문합、손상효응체현적초시응변기본일치，재발전지단렬연신솔부근시유명현하강，정체규률여측시결과문합교호；문중본구관계대응가재곡선적“탈습”계단체후측시수거약5％～6％응변（절대치），응력략고우측시수거，단상대오차소우11％。
Based on general expression of thermal-viscoelastic constitutive equation, damage effect function of propellant Young’s modulus was formulated by fitting axial tensile stress-strain curves in forms of 5-order polynomials.Then stress triaxiality as well as Lode parameter was introduced to conceive stress field factor,with the purpose to modify the damage effect.Ultimately,consti-tutive equations involving damage for HTPB/AP propellant was established. Finite element analysis( FEA) on axial and biaxial ten-sile on the condition of( 25℃,70 mm/min) indicates that curves of FEA data are similar to testing results for both axial and biaxial tensile specimen,curves of FEA data shows decline when rupture is nearby,and the maximum relative error of stress is 11%.