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冲击响应和减轻飞行器灵感的飞机内折叠翼的冲击响应和减轻
Haibo Zhang1,2, Haolin Yang1, Yongjian Yang1,3
1School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China.
Biomimetics (Basel, Switzerland)
|October 25, 2024
概括
这项研究提出了一种新的飞机内折叠翼设计和空气弹性模型. 风洞测试证实了其变形能力和减轻冲击负载的潜力,控制器可将根曲折时刻降低高达47.3%.
科学领域:
- 航空航天工程 航空航天工程
- 生物飞机设计 生物飞机设计
- 航空弹性 航空弹性
背景情况:
- 飞机内折叠式机翼在飞机中提供了增强的机动性和强风阻力.
- 为变形结构开发可靠的气弹性模型对于飞行控制至关重要.
研究的目的:
- 为飞机内折叠翼提供结构实现和空气弹性建模方法.
- 为了研究机翼的变形能力和在空气动力学负荷下风暴反应.
主要方法:
- 使用不断变化的属性的递归近似计算结构短暂响应的计算.
- 合结构模型与不稳定的面板/粘性旋转粒子混合气动力学方法.
- 风洞测试用于验证变形能力和负载预测.
主要成果:
- 在空气动力学负荷下,在飞机内折叠翼的可控制的变形.
- 与风洞数据对比,验证了开发的气弹性模型的准确性.
- 风吹模拟显示了在开放和闭环系统上显著的风吹规模效应.
结论:
- 开发的方法准确地预测了折叠过程中的机翼负荷.
- 风吹缓解控制器有效地减少了翼根曲的时刻,有效性取决于风吹规模.
- 飞机内折叠式机翼有望提高飞机性能和安全性.
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