平角旋转机构约束的管射无人机二次折叠翼气动优化设计

昌敏; 孙杨; 白俊强; 孟晓轩

doi:10.7527/S1000-6893.2021.26331

航空学报 >

2022 , Vol. 43 >Issue 11: 526331 - 526331

DOI: https://doi.org/10.7527/S1000-6893.2021.26331

论文

平角旋转机构约束的管射无人机二次折叠翼气动优化设计

昌敏 ,
孙杨 ,
白俊强 ,
孟晓轩

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1. 西北工业大学无人系统技术研究院, 西安 710072;
2. 西北工业大学航空学院, 西安 710072

收稿日期: 2021-09-07

修回日期: 2021-09-26

网络出版日期: 2021-10-09

基金资助

国家自然科学基金（11902320）

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Aerodynamic design optimization of twice folding wing for tube-launched UAV constrained by flat-angle rotation mechanism

CHANG Min ,
SUN Yang ,
BAI Junqiang ,
MENG Xiaoxuan

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1. Unmanned System Research Institute, Northwestern Polytechnical University, Xi'an 710072, China;
2. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2021-09-07

Revised date: 2021-09-26

Online published: 2021-10-09

Supported by

National Natural Science Foundation of China (11902320)

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摘要

机翼分段折叠的二次折叠翼可有效增加管射无人机的展弦比，提升管射无人机的巡航效能。但连接分段机翼的第二展开机构使得内、外机翼过渡段包络面相对厚度增大，气动性能降低，恶化了二次折叠翼的巡航性能。因此，建立二次折叠翼气动设计方法具有重要意义。开展了考虑第二展开机构几何约束的二次折叠翼气动优化设计研究。首先，采用自由变形（FFD）技术对二次折叠机翼进行参数化建模。其次，结合CFD求解器和遗传算法搭建了气动优化设计系统。最后，在具体优化设计工作中，将第二展开机构几何约束转化为关键剖面的绝对厚度约束，通过求解FFD控制点影响因子将绝对厚度约束转化为控制点设计变量变化范围约束。应用该优化系统对二次折叠机翼在升力系数0.68设计工况下开展考虑机构约束的优化设计工作，结果表明，在满足机构约束的前提下，机翼气动阻力减幅达到9.3%，有效地改善了二次折叠机翼气动特性。

关键词： 管射无人机; 二次折叠翼; 平角旋转; 自由变形技术; 优化设计; 气动效率

本文引用格式

昌敏 , 孙杨 , 白俊强 , 孟晓轩 . 平角旋转机构约束的管射无人机二次折叠翼气动优化设计[J]. 航空学报, 2022 , 43(11) : 526331 -526331 . DOI: 10.7527/S1000-6893.2021.26331

Abstract

The twice folding wing can effectively increase the aspect ratio of the wing of tube-launched UAV and improve the cruising efficiency of the UAV. However, the flat-angle rotation deployment mechanism increases the thickness of the profile between the inner and outer wings, reducing the aerodynamic performance and worsening the cruise performance of the twice folding wing. Therefore, it is of great significance to establish the aerodynamic design method for the twice folding wing. In this paper, an aerodynamic optimization design for the twice folding wing is developed considering the geometric constraints of the second deployment mechanism. Firstly, the Free Form Deformation (FFD) technique is used to parameterize the twice folding wing. Then, combined with CFD solver and Genetic Algorithm, an aerodynamic optimization design system is developed. Finally, the absolute thickness constraint is transformed into the constraint of the variation range of the design variables for the FFD control points by solving the influence coefficient. The optimization design system is used to the design optimization of the twice folding wing under design conditions lift coeffiaient 0.68 considering constraints of mechanism. The result shows that the aerodynamic drag coefficient of the twice folding wing decreases by 9.3%, satisfying the constraint of the deployment mechanism. The developed optimization design system can effectively improve the aerodynamic characteristics of the twice folding wing.

Key words： tube-launched UAV; twice folding wing; flat-angle rotation; free-form deformation technique; optimization design; aerodynamic efficiency

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