基于参数化折叠板模型的Z型折叠机翼非线性动力学理论及实验研究

The Z-shaped folding wing is an important plan for designing morphing aircraft, which can strongly improve maneuverability and dramatically extend flight envelope for aircraft by folding transformation. A Z-shaped folding wing consists of inner wing, middle wing and outer wing, whose complicated configuration and environmental loads make it difficult to accurately analyze its dynamic characteristics, and further lead to severe challenges in the qualitative design and flight control of the Z-shaped folding wing morphing aircraft. This project will design the simulation models of a Z-shaped folding wing and its simplified folding plates, establish a parametric consistent relation between the both models through simulating on structural dynamics and flexible multi-body dynamics, construct parametric nonlinear dynamic model of folding plates for the Z-shaped folding wing, study the dynamic characteristics of the locking and transforming Z-shaped folding wing, explore the occurring mechanisms and parametric rules of dynamic phenomena, and design foundation excitation and wind tunnel experiments to validate and improve the theoretical results. This project mainly uses the nonlinear dynamics, flexible multi-body dynamics and other theories to conduct theoretical and experimental researches on the dynamic characteristics of Z-shaped folding wings and provides scientific guidance for improving our national technologies of morphing aircraft, which is of great engineering value and theoretical significance.

Z型折叠机翼是一种重要的可变体飞行器设计方案，它能通过折叠变形极大地提升飞行器的操控性能并显著地扩展飞行器的飞行包线。Z型折叠机翼由內翼、中翼和外翼组成，其复杂的构型和载荷环境使其动力学特性的精确分析极为困难，进而给Z型折叠机翼可变体飞行器的品质设计和飞行控制带来了严重挑战。本项目拟设计Z型折叠机翼及其简化折叠板的仿真模型，利用结构动力学和柔性多体动力学仿真研究来构建两者之间的一致性参数对应关系，进而建立Z型折叠机翼的参数化折叠板非线性动力学模型；研究Z型折叠机翼锁定状态和变体调整过程的动力学特性，探寻系统各种动力学现象的发生机理和参数影响规律；设计Z型折叠机翼的基础激励实验和风洞实验对理论研究结论进行验证和完善。本项目主要利用非线性动力学和柔性多体动力学等理论和方法开展Z型折叠机翼动力学特性的理论与实验研究，为促进我国可变体飞行器技术的发展提供科学指导，具有重要的工程价值和理论意义。

变体飞行器可以大幅度地改变自身构型以达到全航程的最优飞行效益，能够在多变的飞行环境中或者在执行多种任务时始终保持良好性能。折叠翼变体飞行器可以如同鸟类折叠收缩其翅膀一样依据飞行任务改变机翼构型，被认为极具发展前景。折叠翼变体飞行器机翼的运动变形特点给其动力学特性的精确分析和控制带来困难，也给飞行器的稳定性和操纵性设计带来了挑战。项目建立折叠翼变体飞行器的虚拟数字化模型和刚柔耦合动力学模型，利用数值仿真和动力学理论研究其运动和力学特性，设计折叠翼及其简化折叠板的仿真模型，利用结构动力学和柔性多体动力学仿真研究来构建两者之间的一致性参数对应关系，进而建立折叠翼的参数化折叠板非线性动力学模型；研究折叠翼锁定状态和变体调整过程的动力学特性，探寻系统各种动力学现象的发生机理和参数影响规律；设计折叠翼的基础力学实验对理论研究结论进行验证和完善。基于项目研究，发表期刊文章10篇，会议文章2篇，申请发明专利3项，制作折叠翼样机1架，搭建小型振动实验装置1套，培养硕士研究生5人。本项目主要利用非线性动力学和柔性多体动力学等理论和方法开展折叠翼动力学特性的理论与实验研究，促进航空航天相关领域的科学技术的融合发展，具有重要的理论意义和工程应用价值。

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