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论文:2023,Vol:41,Issue(5):942-949 |
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引用本文： |
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石欣桐, 杨宇, 葛文杰, 王志刚, 孙侠生. 基于多节转动机构的变弯度机翼后缘结构设计[J]. 西北工业大学学报 |
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SHI Xintong, YANG Yu, GE Wenjie, WANG Zhigang, SUN Xiasheng. Structure design of variable camber wing trailing edge based on multi-block rotating mechanism[J]. Journal of Northwestern Polytechnical University |
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| 基于多节转动机构的变弯度机翼后缘结构设计 |
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| 石欣桐1, 杨宇1, 葛文杰2, 王志刚1, 孙侠生3 |
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1. 中国飞机强度研究所 强度与结构完整性全国重点实验室, 陕西 西安 710065;
2. 西北工业大学 机电学院, 陕西 西安 710072;
3. 中国航空研究院, 北京 100012 |
| 摘要: |
| 变弯度后缘可以使飞机在整个飞行包线内始终保持最佳的气动性能,从而达到减少飞机燃油消耗以及空气污染物排放的最终目的,是新一代民用飞机的重要特征和发展方向之一。为解决大型飞机变弯度后缘高承载与大变形之间的设计矛盾,提出了一种基于多节转动的变弯度机翼后缘结构方案,建立了以实现光滑连续变形为目标的多节转动机构参数化优化方法,完成了多节转动变弯度后缘结构的设计与制备,并搭建地面试验平台对变弯度后缘原理样件的变形功能进行了验证。结果表明,通过所提出的多节转动机构优化方法设计得到的变弯度机翼后缘可以实现光滑连续变形,原理样机实际变形范围为上偏3.9°至下偏12.5°,与设计目标误差为16.7％,为解决大型飞机变弯度结构工程应用问题提供了设计参考。 |
| 关键词:
变形机翼
变弯度后缘
多节转动机构
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| Structure design of variable camber wing trailing edge based on multi-block rotating mechanism |
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| SHI Xintong1, YANG Yu1, GE Wenjie2, WANG Zhigang1, SUN Xiasheng3 |
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1. National Key Laboratory of Strength and Structural Integrity, Aircraft Strength Research Institute of China, Xi'an 710072, China;
2. School of Mechatronics, Northwestern Polytechnical University, Xi'an 710072, China;
3. Chinese Aeronautical Establishment, Beijing 100027, China |
| Abstract: |
| The variable camber trailing edge enables the aircraft to maintain the best aerodynamic performance throughout the flight envelope, so as to achieve the ultimate goal of reducing aircraft fuel consumption and air pollutant emissions. It is one of the important characteristics and development direction of the new generation civil aircraft. In order to solve the contradiction between the high load-bearing and the large deformation of the variable camber trailing edge of large aircraft, a structure scheme for variable camber trailing edge based on multi-block rotation was proposed. A parametric optimization method was established for smooth and continuous deformation of multi-block rotating mechanism. The multi-block rotating structure and driving system of variable camber trailing edge were designed, and the deformation function of the variable camber trailing edge demonstrator was preliminarily verified by ground test. The result shows that variable camber wing trailing edge designed by using the present optimization method of multi-block rotating mechanism can realize smooth and continuous morphing. The actual deformation range of the demonstration is 3.9 degrees up to 12.5 degrees down, and the error with the design target is 16.7％. It provides a design reference for solving the engineering application problem of variable camber structure for large aircraft. |
| Key words:
morphing wing
variable camber trailing edge
multi-block rotating mechanism
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| 收稿日期: 2022-10-25
修回日期:
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| DOI: 10.1051/jnwpu/20234150942 |
| 通讯作者: 杨宇(1980—),中国飞机强度研究所研究员,主要从事智能结构与结构健康监测研究。e-mail:yangyu@cae.ac.cn
Email：yangyu@cae.ac.cn |
| 作者简介: 石欣桐(1991—),中国飞机强度研究所工程师,主要从事智能结构与结构健康监测研究。
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