固体发动机药柱应力应变仿真与试验验证研究

Study on the Stress-Strain Simulation and Experimental Validation for the Solid Motor Grain

目的研究某导弹固体发动机药柱在不同环境温度下的性能演变规律。方法利用ABAQUS有限元分析软件,仿真计算了药柱在-40,20,50℃下的应力应变情况,在此基础上通过推进剂拉伸应力松弛试验对仿真结果进行验证分析。结果最大应力应变发生在头部人工脱粘层的根部,药柱内部沿径向越靠近内孔表面,应力应变的数值越大,沿药柱的轴向,内孔表面的最大应力应变发生在靠近药柱中间位置。结论线粘弹性本构关系模型在较低应变水平下可以很好地模拟出推进剂的力学行为,当应变水平在14.3%以下时,试验和仿真的相对误差能控制在10%以内。

Objective To study the performance evolution rule of missile propellant at different ambient temperatures. Methods Using ABAQUS finite element analysis software, the stress and strain of the propellant were analyzed at three different ambient temperatures through the simulation calculation of grain structures. In addition, the propellant tensile stress relaxation test analyses were used to validate the simulation results. Results The maximum stress-strain occurred at the bottom of the head artificial debonding layer. In the internal grain, post along the radial, the closer to the surface of the inner hole, the greater value of stress and strain; while along the axial grain, the maximum stress-strain at the surface of the inner hole occurred near the middle position of the grain. Conclusion At low strain levels, the linear viscoelastic mechanical behavior and constitutive model could simulate the propellant well, when the strain level was below 14.3%, the relative error between the simulation and the test results could be controlled within10%.