| 引用本文: | 杨广,刘振旭,肖洪,白玥,郭宏伟,刘荣强.平行四边形剪切变后掠翼设计及参数优化[J].哈尔滨工业大学学报,2025,57(4):105.DOI:10.11918/202405033 |
| YANG Guang,LIU Zhenxu,XIAO Hong,BAI Yue,GUO Hongwei,LIU Rongqiang.Design and parameter optimization of a parallelogram shear-based variable-sweep wing[J].Journal of Harbin Institute of Technology,2025,57(4):105.DOI:10.11918/202405033 |
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| 平行四边形剪切变后掠翼设计及参数优化 |
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杨广1,2,刘振旭1,2,肖洪1,2,白玥1,2,郭宏伟1,2,刘荣强1,2
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(1.哈尔滨工业大学 机电工程学院,哈尔滨 150001; 2.机器人技术与系统全国重点实验室(哈尔滨工业大学),哈尔滨 150001)
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| 摘要: |
| 为探索飞行器变形机翼不同变后掠方式下结构特性与气动特性的差异以及差异产生的物理机理,提出了两种基于平行四边形单元剪切变形拓扑的剪切式变后掠翼方案,并与传统旋转式变后掠翼进行对比研究。首先,通过机翼面积、展弦比、根梢比以及翼型相对厚度4个主要参数探讨了3种变形方式的结构特性。然后,开展了相应的宽速域绕流流场数值模拟,对比并分析了3种变形形式的气动特性与机理。最后,针对综合气动性能最优的对角剪切式变后掠翼,以超音速巡航状态下机翼面积、展弦比以及翼根弦长为优化目标函数对机翼四边形单元的长宽比进行参数优化,并研制可变形样机进行了风洞试验。结果表明:在宽速域范围内,对角剪切式变后掠翼能获得较优的升阻比,差异主要来源于对角剪切式变后掠翼尖截面处翼型完整且机翼相对厚度较小；当机翼四边形单元长宽比为1.75时,机翼的综合气动性能最佳。 |
| 关键词: 平行四边形 变后掠 机翼参数 气动特性 风洞试验 |
| DOI：10.11918/202405033 |
| 分类号:V211.41+2 |
| 文献标识码:A |
| 基金项目:国家自然科学基金重大项目(52192631)；机器人技术与系统全国重点实验室(哈尔滨工业大学)预研课题(SKLRS202412B) |
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| Design and parameter optimization of a parallelogram shear-based variable-sweep wing |
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YANG Guang1,2,LIU Zhenxu1,2,XIAO Hong1,2,BAI Yue1,2,GUO Hongwei1,2,LIU Rongqiang1,2
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(1.School of Mechatronics Engineering, Harbin Institute of Technology, Harbin 150001,China; 2.State Key Laboratory of Robotics and Systems (Harbin Institute of Technology), Harbin 150001, China)
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| Abstract: |
| To explore the differences in structural and aerodynamic characteristics of the variable-sweep wings on aircraft under various swept deformation methods, as well as the underlying physical mechanisms of these differences, this paper proposes two shearing variable-sweep schemes based on parallelogram unit shear deformation topology, and a comparative study was conducted with a conventional rotary variable-sweep wing. First, the structural characteristics of the three deformation modes are investigated by four main parameters: wing area, chord ratio, root-to-apex ratio and relative thickness of the wing. Then, numerical simulations of the winding flow field in a wide range of speeds are carried out to analyze the aerodynamic characteristics and mechanisms under the three deformation modes. Finally, for the diagonal shear variable-sweep wing with optimal aerodynamic performance, the length-width ratio of the parallelogram unit is optimized with the optimization objective functions of wing area, chord ratio and root chord length at supersonic cruise state. A deformable prototype is developed for wind tunnel testing. The results demonstrate that, across a wide range of speed, diagonal shear variable-sweep can obtain a better lift-to-drag ratio, the difference mainly arises from the fact that the airfoil of the wingtip section of the diagonal shear variable-sweep is intact and the relative thickness of the wing is smaller. When the aspect ratio of the parallelogram unit is 1.75, the comprehensive aerodynamic performance of the morphing wing is the best. |
| Key words: parallelogram variable-sweep wing parameters aerodynamic characteristics wind tunnel testing |
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