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民机的结构设计必须按照耐久性/损伤容限要求进行,因其分析方法不像静强度那样成熟,适航当局在进行符合性审查时,特别注重全尺寸结构的疲劳和损伤容限试验。在部件试验中,因各部件试验可同时独立进行、载荷谱全面、加载点少及进度快,因此广泛用于民机研制过程中。部件疲劳试验的支持夹具提供与原结构相当的支持刚度。文章通过对某飞机襟翼子翼疲劳试验支持夹具的设计与分析,验证试验支持段可提供真实支持。研究表明,随着试验件与真实支持连接的静不定阶数增大,过渡段的设计趋于复杂。当支持夹具的设计过于复杂时,为保证结果准确有效,建议采用与试验件相连接的真实结构作为支持段。
Civil aircraft structural design must be carried out in accordance with the durability / damage tolerance requirements, because its analytical methods are not as mature as static strength, airworthiness authority in the compliance review, with special emphasis on full-size structure fatigue and damage tolerance test. In the component test, the test of each component can be carried out independently at the same time, the load spectrum is comprehensive, the loading point is less and the progress is faster, so it is widely used in the civil aircraft development process. The support fixture of the component fatigue test provides the same support stiffness as the original structure. Through the design and analysis of the fatigue test support fixture of a plane flaps wing, the article verifies that the test support section can provide real support. The research shows that the design of the transition section tends to be complicated as the static order of the test piece and the real support increases. When the support fixture design is too complicated, in order to ensure accurate and effective results, it is recommended to use the real structure connected with the test piece as the support section.