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首页> 外文会议>Symposium on Methods for the Assessment of Structural Integrity of Components and Structures; 20010425; Cambridge; GB >Fatigue-Based Assessments in Aircraft Structures - Designing and Retaining Aircraft Structural Integrity
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Fatigue-Based Assessments in Aircraft Structures - Designing and Retaining Aircraft Structural Integrity

机译：飞机结构中基于疲劳的评估-设计和保持飞机结构完整性

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The processes of fatigue substantiation of civil transport aircraft are reviewed. The requirements for safe life, fail safe and damage tolerance design are described and related to the written requirements of JAA and FAA regulators. The substantiation of fixed wing aircraft is contrasted with requirements for rotary wing aircraft, where safe life design rather than damage tolerant is still the norm. The contribution of Health and Usage Monitoring Systems (HUMS) to safety in safe life helicopter designs is assessed. Challenges to the fail-safe/damage-tolerant approach posed by ageing aircraft, and the introduction of alternative materials such as carbon fibre polymer composites are described. The actions taken by regulators, manufacturers and operators to maintain airworthiness in the face of these challenges are described.
机译：审查了民用航空器疲劳实体化的过程。描述了安全寿命，故障安全和损坏容忍设计的要求，并与JAA和FAA监管机构的书面要求有关。固定翼飞机的实证性与旋翼飞机的要求形成了对比，旋翼飞机的要求仍然是安全寿命设计而不是容忍损坏。评估了健康和使用情况监视系统（HUMS）对安全生活直升机设计中的安全性的贡献。描述了老化飞机对故障安全/容错方法的挑战，以及替代材料（如碳纤维聚合物复合材料）的引入。描述了监管机构，制造商和运营商为应对这些挑战而采取的保持适航性的措施。

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