论文部分内容阅读
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 detection of solid rocket engine thermal insulation layer, the basic law of thermal insulation layer debonding pulse thermal imaging was analyzed by numerical simulation method. The multivariable relationship between decision parameters and structural parameters is obtained, and some test rules are verified by experiments. The relationship between the maximum temperature difference and the maximum contrast and the size of the debonding can be approximated by a piecewise linear function. As the debonding size increases, the maximum temperature difference and the maximum contrast ratio increase. The relationship between the maximum temperature difference and the maximum contrast ratio and the thickness of the heat insulating layer is non- With the increase of the thickness of the insulation layer, the maximum temperature difference and the maximum contrast decrease rapidly. The increase of the thickness of the steel shell is beneficial to the single-side method from the side of the insulation layer. The resulting data and conclusions provide guidance for the pulse thermal imaging of solid rocket motor debonding.