在损伤容限的方法动态加载的旋翼机部件

在损伤容限的方法动态加载的旋翼机部件(中文5400字,英文3400字)
-风险评估最优检测规划的挑战
1.摘要
裂纹扩展损伤容限的使用作为一个实体直升机动力部件的方法受到越来越多的关注作为一个逻辑和可行的改善疲劳可靠性和结构的完整性。它在直升机上看到的只有有限的使用，因为增加了困难的周期检查被视为一个重要的负担，操作员。然而认证机构正在走向同时使用两种安全的生活每一个部件的损伤容限方法。为了减轻的成本问题，一种手段，以优化检查协议，使用风险通知基于损伤容限的疲劳可靠性模型及其维修优化在本文中的工具进行评估。这是要求保持同样的“6-9”水平结构可靠性的损伤容限，这是现在的标准做法生命安全验证。新开发的疲劳可靠性方法采用初始裂纹尺寸的变化，裂纹扩展速率，无损检查，飞行载荷和使用频谱。可靠性模型进一步整合优化技术的检验规划。
一个例子的情况下，使用裂纹扩展测试结果从直升机的主要用可靠性模型对转子主轴进行了评价。DT风险的概念评估和优化检测规划，NDI检测能力的影响和维修质量的风险降低，并结合煤层气物流的重要性要求证明。它的结论是疲劳可靠性模型成功地证明了损伤容限确定一个优化的检验协议，减少操作者的检查负担的同时提供所需的6-9的疲劳可靠性。

Dynamic Loaded Rotorcraft Components – From
Risk Assessment to Optimal Inspection Planning
Abstract. The use of Crack Growth Damage Tolerance as a substantiation methodology for helicopter dynamic components is receiving increased attention as a logical and viable improvement in fatigue reliability and structural integrity. It
has seen only limited use in helicopters because the addition of difficult periodic inspections was seen as a significant burden to the operator. However the certifying agencies are moving towards the simultaneous use of both Safe-Life and Damage Tolerance methodologies on each component. In order to mitigate the cost issue, a means to optimize the inspection protocol using a risk-informed damage tolerance based fatigue reliability model and maintenance optimization tool is evaluated in this paper. It was desired to maintain the same “6-9’s” level of
structural reliability for Damage Tolerance that is now the standard practice for safe-life substantiations. The newly developed fatigue reliability methodology incorporates the variabilities in initial crack size, crack growth rate, nondestructive inspections, flight loads, and the usage spectrum. The reliability model is further integrated with optimization technique for inspection planning. An example case using the crack propagation test result from a helicopter main rotor spindle is evaluated with the reliability model.