1.1 本试验方法包括层间断裂韧性的测定， K TL ，用于不同纤维方向的层压、模压或拉挤聚合物基复合材料，使用单调加载缺口试样的测试结果。如果材料响应是这样的: K TL 计算无效，提供了其他报告方法。 1.2 本试验方法适用于室温实验室空气环境。 1.3 可通过本试验方法进行试验的复合材料不受厚度或聚合物基体或纤维类型的限制，前提是试样尺寸和试验结果符合本试验方法的要求。本试验方法主要根据各种碳纤维-环氧树脂基体层压板的试验结果以及玻璃纤维-环氧树脂基体、玻璃纤维-聚酯基体拉挤成型和碳纤维-双马来酰亚胺基体层压板的附加结果制定 ( 1- 4. , 5. , 6. ) . 2. 1.4 提供了一系列偏心加载、单边缺口张力ESE（T）、具有比例平面尺寸的试样尺寸，但平面尺寸可能会随着所施加试验载荷的相关变化而变化和调整。试样厚度是可变的，与平面尺寸无关。 1.5 可以使用本试验方法中包含的样品配置以外的其他样品配置。特别重要的是，在 5.1 和 5.4 当使用替代试样配置和 K TL 计算 1.6 单位- 以国际单位制或英寸-磅单位表示的数值应单独视为标准值。每个系统中规定的值不一定是精确的等价物；因此，为确保符合本标准，每个系统应独立使用，且两个系统的值不得组合。 1.6.1 在文本中，英寸- 磅单位显示在括号中。 1.7 本标准并非旨在解决与其使用相关的所有安全问题（如有）。本标准的用户有责任在使用前制定适当的安全、健康和环境实践，并确定监管限制的适用性。 1.8 本国际标准是根据世界贸易组织技术性贸易壁垒（TBT）委员会发布的《关于制定国际标准、指南和建议的原则的决定》中确立的国际公认标准化原则制定的。 ====意义和用途====== 5.1 参数 K TL 通过该试验方法测定了聚合物基复合材料层压板在开放模式载荷下对缺口尖端损伤和有效跨层裂纹扩展的电阻。该结果仅适用于缺口尖端的损伤区与缺口长度和长度相比较小的情况- 平面试样尺寸。或者，对于表现出较大体积分布损伤的材料，观察到的力位移和离散损伤事件仍然是某些特定工程应用的有效结构响应。 5.2 该试验方法可用于以下目的。在研发方面( 一 ) K TL 数据可以定量地确定纤维和基体变量以及层压板的堆叠顺序对复合材料层压板跨层断裂阻力的影响；和( b )量化的分布式损伤测量可用于验证渐进复合材料损伤模型。在结构设计中， K TL 在试样几何形状和载荷的约束范围内，数据可用于评估复合材料层压板对边缘缺陷和缺口损伤增长的抵抗力。 5.3 跨层断裂韧性， K TL 以及由该测试方法确定的分布式损伤观察值可能是测试速度和温度的函数。 本试验方法适用于室温和准静态条件，但其可适用于其他试验条件，前提是符合 13.2 和 13.3 满足。应用 K TL 在设计服务部件时，应意识到本试验规定的试验参数可能不同于服务条件，可能导致不同于服务中看到的材料响应。分布式损伤观察也仅限于测试的材料和几何形状，但可能更普遍地应用于各种结构分析验证应用。 5.4 并非所有类型的层压聚合物基复合材料都会经历本试验方法中关注的包含缺口尖端损伤和有效跨层裂纹扩展。在这种情况下，力位移和离散损伤观察结果-不是 K TL –应使用。 5.5 报告部分要求报告可能影响跨层断裂韧性和离散损伤发展的项目； 这些包括以下内容:材料、材料制造方法、铺层方向的准确性、层压板堆叠顺序和总厚度、试样几何形状、试样制备、试样调节、测试环境、孔隙含量、钢筋体积百分比、缺口制备的尺寸和方法、试样/夹具对准和测试速度。

1.1 This test method covers the determination of translaminar fracture toughness, K TL , for laminated, molded, or pultruded polymer matrix composite materials of various fiber orientations using test results from monotonically loaded notched specimens. If the material response is such that the K TL calculation is not valid, alternate reporting methods are provided. 1.2 This test method is applicable to room temperature laboratory air environments. 1.3 Composite materials that can be tested by this test method are not limited by thickness or by type of polymer matrix or fiber, provided that the specimen sizes and the test results meet the requirements of this test method. This test method was developed primarily from test results of various carbon fiber – epoxy matrix laminates and from additional results of glass fiber – epoxy matrix, glass fiber-polyester matrix pultrusions and carbon fiber – bismaleimide matrix laminates ( 1- 4 , 5 , 6 ) . 2 1.4 A range of eccentrically loaded, single-edge-notch tension, ESE(T), specimen sizes with proportional planar dimensions is provided, but planar size may be variable and adjusted, with associated changes in the applied test load. Specimen thickness is a variable, independent of planar size. 1.5 Specimen configurations other than those contained in this test method may be used. It is particularly important that the requirements discussed in 5.1 and 5.4 regarding contained notch-tip damage be met when using alternative specimen configurations in conjunction with the K TL calculation. 1.6 Units— The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined. 1.6.1 Within the text, the inch-pound units are shown in brackets. 1.7 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use. 1.8 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee. ====== Significance And Use ====== 5.1 The parameter K TL determined by this test method is a measure of the resistance of a polymer matrix composite laminate to notch-tip damage and effective translaminar crack growth under opening mode loading. The result is valid only for conditions in which the damage zone at the notch tip is small compared with the notch length and the in-plane specimen dimensions. Alternately, for materials exhibiting distributed damage in a larger volume, observed force-displacement and discrete damage events are still valid structural responses for certain specific engineering applications. 5.2 This test method can serve the following purposes. In research and development, ( a ) K TL data can quantitatively establish the effects of fiber and matrix variables and stacking sequence of the laminate on the translaminar fracture resistance of composite laminates; and ( b ) quantified distributed damage measurements can be used to validate progressive composite damage models. In structural design, K TL data can, within the constraints of the specimen geometry and loading, be used to assess composite laminate resistance to damage growth from edge flaws and notches. 5.3 The translaminar fracture toughness, K TL , as well as distributed damage observations, determined by this test method may be a function of the testing speed and temperature. This test method is intended for room temperature and quasi-static conditions, but it can apply to other test conditions provided that the requirements of 13.2 and 13.3 are met. Application of K TL in the design of service components should be made with awareness that the test parameters specified by this test may differ from service conditions, possibly resulting in a different material response than that seen in service. Distributed damage observations are also limited to the material and geometry tested, but may be more generally applied to a variety of structural analysis validation applications. 5.4 Not all types of laminated polymer matrix composite materials experience the contained notch-tip damage and effective translaminar crack growth of concern in this test method. In such circumstances, the force-displacement and discrete damage observations – not K TL – shall be used. 5.5 The reporting section requires items that tend to influence translaminar fracture toughness and discrete damage progression to be reported; these include the following: material, methods of material fabrication, accuracy of lay-up orientation, laminate stacking sequence and overall thickness, specimen geometry, specimen preparation, specimen conditioning, environment of testing, void content, volume percent reinforcement, size and method of notch preparation, specimen/fixture alignment, and speed of testing.