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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   

  1. 西北工业大学
  • 收稿日期:2021-09-07 修回日期:2021-10-09 出版日期:2021-10-09 发布日期:2021-10-09
  • 通讯作者: 昌敏

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

Min Chang,sun   

  • Received:2021-09-07 Revised:2021-10-09 Online:2021-10-09 Published:2021-10-09
  • Contact: Min Chang

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。本文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,对过渡段包络面和第二展开机构进行参数化描述,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。其次,采用自由变形(FFD)技术对二次折叠机翼进行参数化建模,通过求解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。最后,结合CFD求解器和遗传算法搭建了气动优化设计系统。应用该优化系统对二次折叠机翼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, FFD技术, 优化设计, 气动效率

Abstract: The twice folding wing can effectively increase the aspect ratio of the wing of tube-launched UAV and improve the cruising efficiency. 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 twice folding wing. Therefore, it is of great significance to establish the aerodynamic design method of twice fold-ing wing. In this paper, the aerodynamic optimization design of twice folding wing considering the geometric con-straints of the second deployable mechanism is established. Firstly, the parameter of wing platform and the second deployment mechanism are defined and the geometric constraints of the second deployment mechanism were transformed into the absolute thickness constraints of the key sections. Then, the free form deformation (FFD) tech-nique is used to parameterize the twice folding wing, and the absolute thickness constraint is transformed into the variation range constraint of the design variables for the FFD control points by solving the influence coefficient. Fi-nally, combined with CFD solver and genetic algorithm, an aerodynamic optimization design system is developed. The optimization result shows that the aerodynamic drag coefficient of the twice folding wing decreases by 12.6%, 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, Optimization design, Aerodynamic efficiency

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