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首页> 外文会议>AHS International Annual Forum vol.2; 20070501-03; Virginia Beach,VA(US) >Obtaining Usage Credits from Monitoring of Helicopter Dynamic Components without Impacting Safe Life Reliability
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Obtaining Usage Credits from Monitoring of Helicopter Dynamic Components without Impacting Safe Life Reliability

机译：在不影响安全寿命可靠性的情况下，通过监视直升机动态组件获得使用积分

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摘要

US Army helicopters assign retirement times for each fatigue life limited component. Helicopter maintenance is currently based on aircraft flight hours. Each component retirement time is derived using the Prime Contractors / Original Equipment Manufacturer's (OEM's) safe life methodology which typically includes fatigue testing of production components to determine a working S/N curve, measurements of top of scatter loads from flight load surveys, and construction of a composite usage spectrum from pilot surveys. Efforts are being made under the Condition Based Maintenance (CBM) program to implement a usage monitoring system, and evaluate the actual fatigue damage based on aircraft usage. The retirement time for a particular component may then be refined based on the accumulated fatigue damage from each flight instead of a calculated number based upon the flight hours. Goals of the usage monitoring program are to identify how severely individual helicopters are used, and whether part retirement life can be extended. This paper introduces the process proposed by the US Army AMRDEC for usage monitoring on Army helicopters. The system monitors aircraft parameters for flight condition identification or regime recognition, and enables a remaining life estimate for each component tracked. Implementation of a usage monitoring system may affect aircraft reliability. Composite usage spectrums typically are very conservative, and contribute to overall system reliability. A study of UH-60 components1 indicates that for the assumed six-nines reliability, one-nine was estimated from the composite usage spectrum. By implementing a usage monitoring system, the component reliability could be reduced through loss of conservatism in the usage spectrum. This paper presents a process for calculating the Remaining Useful Life (RUL) based on data from usage monitors. A Life Factor is applied to the fatigue damage fraction from usage monitored flights. The Load Factor is derived and provides a reference that substantiates the methodology. An example analysis on extending the fatigue life of a helicopter component, without an impact to the reliability, is also provided. This methodology is essential to the implementation of usage monitoring. Finally, a summary and conclusions is provided to emphasize important aspects in the paper.
机译：美国陆军直升机为每个疲劳寿命有限的组件分配退役时间。直升机的维护目前基于飞机的飞行时间。使用主要承包商/原始设备制造商（OEM）的安全寿命方法得出每个组件的退役时间，该方法通常包括对生产组件进行疲劳测试以确定工作的S / N曲线，从飞行载荷调查中测量散落载荷的顶部以及构造试点调查的综合使用范围。根据状态维护（CBM）计划正在努力实施使用情况监视系统，并根据飞机的使用情况评估实际的疲劳损坏。然后，可以基于每次飞行的累积疲劳损伤而不是根据飞行时间计算出的数量来细化特定组件的退役时间。使用情况监视程序的目标是确定使用多架直升机的严重程度以及是否可以延长部分退役寿命。本文介绍了美国陆军AMRDEC提出的监视陆军直升机使用情况的过程。该系统监视飞机参数以进行飞行状态识别或状态识别，并启用所跟踪的每个组件的剩余寿命估算。使用情况监视系统的实施可能会影响飞机的可靠性。复合使用频谱通常非常保守，并有助于提高整个系统的可靠性。对UH-60组件1的研究表明，对于假定的六九个可靠性，从组合使用范围中估计出九个。通过实施使用情况监视系统，可以通过减少使用范围中的保守性来降低组件的可靠性。本文介绍了一种基于使用情况监视器中的数据计算剩余使用寿命（RUL）的过程。将寿命因数应用于来自使用情况监控航班的疲劳损坏分数。得出了负载因子，并提供了证实该方法的参考。还提供了在不影响可靠性的情况下延长直升机部件疲劳寿命的示例分析。该方法对于使用监控的实施至关重要。最后，提供总结和结论以强调本文的重要方面。

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