摘要
高超音速飞行器机翼变形技术是军事领域研究的重点内容,对提升飞行器性能有着至关重要的作用。伸缩机翼技术是机翼变形技术的主要研究方向之一,文中以四连杆机构为基本单元设计了大承载、机翼面积变形量大、结构性能稳定的伸缩机翼机构。从运动学角度研究了伸缩机翼的运动规律;通过静态应力仿真分析了其结构的稳定性;从模态特性角度分析了其在5阶不同振动频率下的变形情况。分析证明,设计符合伸缩机翼机构在高超音速环境下的动力学和静力学性能要求,为超高音速飞行器的机翼设计提供了一种简单、结构稳定、性能可靠的方案。
Wing deformation technology of hypersonic vehicle is the key content of military research and plays a vital role in improving aircraft performance.Telescopic wing technology is one of the main research directions of wing deformation technology.This paper designs a stretchable wing mechanism with large load,large deformation of wing area and stable structure performance with a four-bar linkage mechanism as the basic unit.The motion law of the telescopic wing is probed from Kinematics.The stability of the structure is analyzed by static stress simulation.The deformation under different vibration frequencies of order 5 is analyzed from the point of view of modal characteristics.The analysis shows that the design conforms to the dynamic and static performance requirements of the telescopic wing mechanism in hypersonic environment,which provides a simple,stable structure and reliable performance scheme for the wing design of ultra-high-pitch aircraft.
作者
徐晓涵
刘超
XU XiaoHan;LIU Chao(Beijing Key Laboratory of Optoelectronic Testing Technology,Beijing University of Information Technology,Beijing 100192,China;Beijing Laboratory of Biomedical Testing Technology and Instruments,Beijing University of Information Technology,Beijing 100192,China)
出处
《机械工程师》
2021年第6期31-33,36,共4页
Mechanical Engineer
基金
北京市自然科学基金青年基金项目(4164084)
北京市教育委员会科技计划一般项目(KM201611232006)。
关键词
伸缩机翼
高超音速飞行器
强度分析
模态特性
telescopic wing
hypersonic vehicle
strength analysis
modal characteristics
