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针对某大型客机飞机缝翼全尺寸疲劳试验，深入分析了飞机缝翼结构特点、运动轨迹、支持边界精准模拟及试验系统可靠性等难点和风险点，实现了缝翼运动复杂轨迹准确模拟、试验多系统协同控制、复杂耦合失效模式试验系统可靠性提升等多项功能，形成了满足飞机缝翼全尺寸疲劳试验要求的技术方案。提出了缝翼试验支持边界精准模拟技术、缝翼随动加载技术以及试验系统多层级安全防护技术，采用新技术、新方法提高了试验技术水平，技术成果可为后续活动翼面疲劳试验提供参考。
Abstract：For the full-scale fatigue test of the slats of a large civil aircraft, an in-depth analysis was conducted on the structural features, kinematic behavior, boundary condition fidelity, and test system reliability of the slats. Specifically, high-fidelity simulation of the slat's movement trajectory, coordinated multi-system control, and enhanced robustness against coupled failure modes were successfully achieved. A comprehensive framework was established for full-scale slat fatigue testing, integrating constrained boundary simulation, adaptive follow-up loading, and multi-layered safety protection. The adoption of innovative technologies and methodologies has significantly improved the level of test technology, and the technical achievements can provide references for subsequent fatigue tests of movable aerodynamic surfaces.
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基本信息:
中图分类号:V216.3
引用信息:
[1]郭永跃,张建锋,张巍文.某大型客机飞机缝翼全尺寸疲劳试验技术[J].中国科技论文,2025,20(11):924-936.