基于改进混合涡粒子法的倾转旋翼机旋翼/机翼气动干扰研究

杨一凡; 王潇

doi:10.7527/S1000-6893.2024.31040

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DOI: https://doi.org/10.7527/S1000-6893.2024.31040

基于改进混合涡粒子法的倾转旋翼机旋翼/机翼气动干扰研究

杨一凡 ,
王潇

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南京航空航天大学

收稿日期: 2024-08-05

修回日期: 2024-10-27

网络出版日期: 2024-10-29

基金资助

国防科技重点实验室基金;国家自然科学基金面上项目;跨域飞行交叉技术重点实验室基金;跨域飞行交叉技术重点实验室基金

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Enhanced Hybrid Panel-vortex Particle Method for Aerodynamic Analysis of Tiltrotor Rotor/Wing Interactions

YANG Yi-Fan ,
WANG Xiao

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Received date: 2024-08-05

Revised date: 2024-10-27

Online published: 2024-10-29

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摘要

针对倾转旋翼机悬停、前飞和过渡模式旋翼/机翼的气动干扰特性，根据Neumann边界条件和Hess等效原则提出了一种快速分析旋翼/机翼气动干扰的改进混合涡粒子方法。通过引入单面元-多涡粒子转换和涡粒子自适应数量控制策略，实现了自适应涡粒子数量，进一步优化了计算效率。与旋翼风洞实验数据对比表明自适应数量混合涡粒子方法相较于传统黏弹涡粒子方法可以在提高计算效率的同时得到与实验数据吻合良好的计算结果。随后开展旋翼/机翼气动干扰模型在悬停和过渡模式下的流场分析和数值模拟，探讨了旋翼/机翼气动干扰的影响。结果表明：旋翼/机翼气动干扰模型悬停时机翼阻塞下洗流，虽对旋翼有轻微的增升但机翼承受更大的向下载荷，严重影响旋翼/机翼模型的有效载荷；随着总距增加，机翼向下载荷引起的升力损失逐渐减小。直升机模式向飞机模式转换过程中，旋翼尾迹使机翼升力在倾转初期有明显损失，中期有明显提升，末期几乎无影响；机翼会改变旋翼的部分尾迹结果，但对旋翼性能影响较小。飞机模式前飞时，旋翼/机翼气动干扰较弱，但仍可观测到机翼的升阻比有所下降。这些发现将为倾转旋翼机气动弹性稳定性分析、高保真度飞行力学模型和性能优化提供有利支撑。

关键词： 混合涡粒子方法; 气动干扰; 倾转旋翼机; 过渡模式; 性能分析

本文引用格式

杨一凡 , 王潇 . 基于改进混合涡粒子法的倾转旋翼机旋翼/机翼气动干扰研究[J]. 航空学报, 0 : 0 -0 . DOI: 10.7527/S1000-6893.2024.31040

Abstract

Aiming to elucidate the complex aerodynamic interactions between rotor and wing during hovering, forward flight, and transition modes of tiltrotor aircraft, an enhanced hybrid panel-vortex particle method is developed. This method lever-ages Neumann boundary conditions and Hess equivalence principle for efficient computational analysis. By incorpo-rating a novel single panel-multi vortex particle conversion and adaptive vortex particle quantity control, computational efficiency is significantly improved without compromising accuracy. Validation against wind tunnel data demonstrates the method's precision and efficiency compared to traditional viscoelastic vortex particle methods. Subsequent numer-ical simulations and flow field analysis of the rotor/wing model unveil intricate aerodynamic interactions. In hovering mode, while the wing's blocked downwash slightly enhances rotor lift, the dominant negative lift due to significant wing download adversely impacts overall load-carrying capacity. Increasing collective pitch mitigates this lift loss. During transition, the rotor wake initially induces substantial lift loss on the wing, followed by a notable increase and negligible influence in later phases. Conversely, the wing's impact on rotor performance remains minimal. In forward flight, the rotor marginally augments wing lift and drag, albeit with a reduced lift-to-drag ratio. These findings provide valuable insights into the aerodynamic complexities of tiltrotor aircraft, contributing to the development of aeroelastic stability analysis, advanced flight control systems and performance optimization.

Key words： hybrid panel-vortex particle method; aerodynamic interactions; tiltrotor aircraft; transition mode; performance analysis

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