A Shear-Sliding Rigid-Flexible Coupled Skin Variable-Sweep Wing Design and Heat-Fluid-Structure Multifield Coupling Analysis

IF 1.1 4区工程技术 Q3 ENGINEERING, AEROSPACE

International Journal of Aerospace Engineering Pub Date : 2023-08-31 DOI:10.1155/2023/7078091

Hong Xiao, Hongwei Guo, Mingqi Li, Yu Zhang, Rongqiang Liu, Jianguo Tao

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引用次数: 0

Abstract

The variable-sweep wing is very attractive for cross-speed domain aircraft. The shear-sliding rigid-flexible coupled skin variable-sweep wing and its associated mechanism are designed and optimized. The variable-sweep wing has smooth continuous deformation and rigid-flexible coupling features. The calculation model of the sliding skin patch segmentation strategy is established, and the aerodynamic characteristics of the two-dimensional airfoil before and after the deformation of the wing skin are analyzed. According to the deformation characteristics of sliding skin, the configuration of the associated mechanism is determined, and the kinematic characteristics of the reference points of each skin are calculated. The kinematic simulation verifies the force of the mechanism model at the joint of skin surfaces during the deformation process. Considering the aerodynamic heat at supersonic speed, the heat transfer, heat distribution, and structural thermal modes between the flow field and the skin are calculated based on the finite element method. The dynamic characteristics of the swept wing with different flight speeds and different morphologies are analyzed. The natural frequencies are found to be reduced by about 30% to 50% compared to cold models at supersonic speeds. Based on the results of the thermal fluid-solid coupling calculation, the skeleton structure of the swept wing is optimized, and the skeleton structure with 25% mass reduction and better performance is obtained.

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剪切-滑动刚柔耦合蒙皮变后掠翼设计及热流固多场耦合分析

可变后掠翼对于跨速域飞行器非常有吸引力。设计并优化了剪切-滑动刚柔耦合蒙皮变后掠机翼及其相关机构。可变后掠翼具有平滑连续变形和刚柔耦合的特点。建立了滑动蒙皮补片分割策略的计算模型，分析了机翼蒙皮变形前后二维翼型的气动特性。根据滑动蒙皮的变形特性，确定了相关机构的配置，并计算了每个蒙皮参考点的运动学特性。运动学仿真验证了机构模型在变形过程中在蒙皮表面连接处的受力。考虑到超音速下的气动热，基于有限元法计算了流场与蒙皮之间的传热、热分布和结构热模式。分析了后掠翼在不同飞行速度和不同形态下的动力学特性。研究发现，与超音速下的冷模型相比，固有频率降低了约30%至50%。基于热流固耦合计算结果，对后掠翼的骨架结构进行了优化，得到了质量减少25%、性能更好的骨架结构。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Aerospace Engineering ENGINEERING, AEROSPACE-

CiteScore

2.70

自引率

7.10%

发文量

195

审稿时长

22 weeks

期刊介绍： International Journal of Aerospace Engineering aims to serve the international aerospace engineering community through dissemination of scientific knowledge on practical engineering and design methodologies pertaining to aircraft and space vehicles. Original unpublished manuscripts are solicited on all areas of aerospace engineering including but not limited to: -Mechanics of materials and structures- Aerodynamics and fluid mechanics- Dynamics and control- Aeroacoustics- Aeroelasticity- Propulsion and combustion- Avionics and systems- Flight simulation and mechanics- Unmanned air vehicles (UAVs). Review articles on any of the above topics are also welcome.