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Advanced aircraft service life monitoring method via flight-by-flight load spectra.

机译：通过按飞行载荷频谱监测飞机的高级使用寿命。

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摘要

This research is an effort to understand current method and to propose an advanced method for Damage Tolerance Analysis (DTA) for the purpose of monitoring the aircraft service life. As one of tasks in the DTA, the current indirect Individual Aircraft Tracking (IAT) method for the F-16C/D Block 32 does not properly represent changes in flight usage severity affecting structural fatigue life. Therefore, an advanced aircraft service life monitoring method based on flight-by-flight load spectra is proposed and recommended for IAT program to track consumed fatigue life as an alternative to the current method which is based on the crack severity index (CSI) value.;Damage Tolerance is one of aircraft design philosophies to ensure that aging aircrafts satisfy structural reliability in terms of fatigue failures throughout their service periods. IAT program, one of the most important tasks of DTA, is able to track potential structural crack growth at critical areas in the major airframe structural components of individual aircraft. The F-16C/D aircraft is equipped with a flight data recorder to monitor flight usage and provide the data to support structural load analysis. However, limited memory of flight data recorder allows user to monitor individual aircraft fatigue usage in terms of only the vertical inertia (NzW) data for calculating Crack Severity Index (CSI) value which defines the relative maneuver severity. Current IAT method for the F-16C/D Block 32 based on CSI value calculated from NzW is shown to be not accurate enough to monitor individual aircraft fatigue usage due to several problems.;The proposed advanced aircraft service life monitoring method based on flight-by-flight load spectra is recommended as an improved method for the F-16C/D Block 32 aircraft. Flight-by-flight load spectra was generated from downloaded Crash Survival Flight Data Recorder (CSFDR) data by calculating loads for each time hack in selected flight data utilizing loads equations. From the comparison of interpolated fatigue life using CSI value and fatigue test results, it is obvious that proposed advanced IAT method via flight-by-flight load spectra is more reliable and accurate than current IAT method. Therefore, the advanced aircraft service life monitoring method based on flight-by-flight load spectra not only monitors the individual aircraft consumed fatigue life for inspection but also ensures the structural reliability of aging aircrafts throughout their service periods.
机译：这项研究旨在了解当前方法，并提出一种先进的损伤容限分析（DTA）方法，以监控飞机的使用寿命。作为DTA中的一项任务，当前用于F-16C / D方框32的间接飞机跟踪（IAT）方法不能正确表示影响结构疲劳寿命的飞行使用严重性的变化。因此，提出了一种基于逐次飞行载荷谱的先进飞机寿命监测方法，并推荐给IAT程序以跟踪消耗的疲劳寿命，作为基于裂缝严重性指数（CSI）值的当前方法的替代方法。损害容忍度是飞机设计理念之一，旨在确保老化的飞机在整个服役期间就疲劳失效而言满足结构可靠性。 IAT计划是DTA的最重要任务之一，它能够跟踪单个飞机主要机身结构部件中关键区域潜在的结构裂纹扩展。 F-16C / D飞机配备了飞行数据记录器，以监控飞行情况并提供数据以支持结构载荷分析。但是，飞行数据记录器的内存有限，使用户只能根据垂直惯性（NzW）数据来监视各个飞机的疲劳使用情况，以计算定义相对机动性严重程度的裂纹严重性指数（CSI）值。由于基于若干问题，目前基于NzW计算出的CSI值的F-16C / D模块32的IAT方法不够准确，无法监测单个飞机的疲劳使用情况。对于F-16C / D Block 32飞机，建议使用机载载荷谱作为改进方法。通过使用载荷方程式计算选定飞行数据中每次飞行的载荷，从下载的坠毁幸存飞行数据记录器（CSFDR）数据生成逐次飞行载荷谱。通过使用CSI值和疲劳测试结果对内插疲劳寿命进行比较，可以明显看出，通过飞行载荷谱提出的先进IAT方法比目前的IAT方法更可靠，更准确。因此，基于飞行载荷频谱的先进飞机使用寿命监测方法不仅可以监测单个飞机消耗的疲劳寿命以进行检查，而且可以确保老化的飞机在其整个服务期内的结构可靠性。

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  • 作者

    Lee, Hongchul.;

  • 作者单位

    State University of New York at Binghamton.;

  • 授予单位 State University of New York at Binghamton.;
  • 学科 Engineering Aerospace.;Engineering Mechanical.
  • 学位 Ph.D.
  • 年度 2009
  • 页码 128 p.
  • 总页数 128
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空、航天技术的研究与探索;机械、仪表工业;
  • 关键词

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