固体火箭发动机绝热层脱粘的脉冲热像检测分析

Analysis on pulsed thermography of disbonds in insulator of solid rocket motors

为了给红外热像法在固体火箭发动机绝热层检测中的应用提供科学依据,用数值模拟法分析了绝热层脱粘脉冲热像检测的基本规律。得到了决策参数与结构参数之间的多变量关系,并对部分检测规律进行了实验验证。最大温差和最大对比度与脱粘尺寸之间的关系,可用分段线性函数近似描述,随着脱粘尺寸的增大,最大温差和最大对比度都增加;最大温差和最大对比度与绝热层厚度的关系是非线性函数关系,随着绝热层厚度增加,最大温差和最大对比度迅速下降;钢壳厚度的增加,对从绝热层一侧的单面法检测有利。所得数据和结论为固体火箭发动机绝热层脱粘的脉冲热像检测提供了指导。

In order to provide a scientific basis for the application of infrared thermography in the testing of insulators in solid rocket motors（SRMs） , the basic laws of pulsed infrared thermography（PIRT） of disbends in insulators were analyzed by using nu- merical simulation.The multi-parametric relationships between decision-making parameters and structure parameters were obtained, and a part of the testing laws was proved experimentally.The relations between the maximum temperature difference, the maximum contrast and the defect size can be described approximately by piecewise linear functions of the defect size, and both the maximum temperature difference and the maximum contrast increase with the increasing defect size.Both the maximum temperature difference and the maximum contrast are a non-linear function of the insulator thickness, and they decrease rapidly with the increasing insulator thickness.The obtained data and conclusions constitute a guideline for the PIRT of disbonds in the insulator of SRMs.