• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Asia Pacific Symposium on Safety; 20051102-04; Shaoxing(CN) >Reliability Assessment to Helicopter Dynamic Components Fatigue Safe Life
【24h】

Reliability Assessment to Helicopter Dynamic Components Fatigue Safe Life

机译：直升机动力组件疲劳安全寿命的可靠性评估

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Helicopter dynamic components experience high-frequency cyclic loads in practically every flight regime. It is investigated that the accident rate of helicopter appears to be high compared to fixed-wing. The safe life methodology was used to determine when a fatigue life-limited structural component needs to be replaced. The safe lives versus reliability level with a given confidence level are obtained. Based on the fatigue characteristic test and parent parameter of dynamic component, the _(P-S-N) curve was determined by the probabilistic fatigue strength reduction factor. The flight spectrum was compiled on the basis of the twenty perennial service histories and the mission profile was accomplished due to the flight spectrum and the statistical results of typical flight subjects in service. According to the flight survey data of a helicopter dynamic component and the rain flow counting methods of "There Peak-to-Trough Point", the statistical treatment, the hypothesis test and the regression analysis to every measured state of 183 flight conditions were carried out, then the distribution types and the damage of different conditions were determined. Then the fatigue load spectrum is established by versus analytic demonstration. The safe life curves with different risks of failure are determined by Miner's linear cumulative damage calculation. The results can be adopted by the optimal life management approach based on a mixture of the traditional safe-life and damage tolerance techniques.
机译：直升机动力组件几乎在每个飞行状态下都会经受高频循环载荷。据调查，与固定翼相比，直升机的事故率似乎较高。使用安全寿命方法来确定何时需要更换疲劳寿命受限的结构部件。获得了给定置信度下的安全寿命与可靠性水平。基于疲劳特性测试和动态分量的父参数，通过概率疲劳强度降低因子确定_（P-S-N）曲线。飞行谱是根据二十年的常年服役历史编制的，由于飞行谱和在役的典型飞行受试者的统计结果，完成了任务概况。根据直升机动力分量的飞行调查数据和“有峰至谷”的雨流计数方法，对183种飞行状态的每种测量状态进行了统计处理，假设检验和回归分析。 ，然后确定不同条件下的分布类型和破坏。然后通过对比分析建立疲劳载荷谱。具有不同失效风险的安全寿命曲线由Miner的线性累积损伤计算确定。结果可以通过基于传统安全寿命技术和破坏承受能力技术的最佳寿命管理方法来采用。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号