| 引用本文: | 陆陶冶,陈仁良,吉洪蕾,辛冀.共轴双旋翼悬停地面效应分析[J].哈尔滨工业大学学报,2017,49(10):45.DOI:10.11918/j.issn.0367-6234.201607105 |
| LU Taoye,CHEN Renliang,JI Honglei,XIN Ji.Performance analysis of coaxial-rotorfor hovering in ground effect[J].Journal of Harbin Institute of Technology,2017,49(10):45.DOI:10.11918/j.issn.0367-6234.201607105 |
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| 摘要: |
| 共轴双旋翼直升机在近地悬停时存在复杂的旋翼/旋翼/地面干扰效应.为分析近地悬停时共轴双旋翼流场及拉力变化，发展一种共轴双旋翼悬停地面效应计算方法.首先，分别采用升力面法和面元法模拟桨叶和地面对流场的作用，使用三阶精度时间步进格式进行桨叶尾迹计算，并在尾迹迭代过程中引入“等体积”法修正尾迹.然后，运用模型得到共轴双旋翼无地效的诱导速度分布和单旋翼地面效应下的拉力增益并与试验结果对比，验证方法的合理性.最后，基于算例，分析了共轴双旋翼在地面效应悬停状态下的特性，包括尾迹及流场特点、诱导速度与拉力分布、旋翼间干扰和拉力增益.结果表明：悬停地面效应下共轴双旋翼的尾迹发生卷起并径向扩展，其桨盘平面的诱导速度由上旋翼、下旋翼和地面共同引起；分析也表明了悬停地面效应下共轴双旋翼桨盘平面诱导速度及桨叶拉力分布更均匀，在相同功率下，共轴双旋翼的地面效应拉力增益大于同实度单旋翼的拉力增益.
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| 关键词: 直升机 共轴双旋翼 地面效应 悬停 自由尾迹 |
| DOI：10.11918/j.issn.0367-6234.201607105 |
| 分类号:V211.5 |
| 文献标识码:A |
| 基金项目:国家自然科学基金(8,6)；南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20150101) |
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| Performance analysis of coaxial-rotorfor hovering in ground effect |
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LU Taoye1,CHEN Renliang1,JI Honglei1,XIN Ji2
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(1.State Key Laboratory of Rotorcraft Aeromechanics(Nanjing University of Aeronautics and Astronautics), Nanjing 210016, China; 2.China Helicopter Research and Development Institute, Jingdezhen 333000, Jiangxi,China)
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| Abstract: |
| There are complex rotor/rotor/ground interference effects when a coaxial-rotor helicopter hovers near ground. A computational method based on free-wake model is developed to analyze the flow field and thrust of coaxial-rotor helicopter in ground effect. Firstly, the lifting-surface blade model and the ground panel model are taken in this method to simulate the effects of blades and ground to the flow field. A 3rd-order accuracy time-marching scheme is conducted to get the free-wake of coaxial-rotor. Also, the constant-volume-rectification method is incorporated to prevent numerical divergence. Then, the coaxial-rotor out of ground effect (OGE) and the single-rotor in ground effect (IGE) are used as examples to validate the method. Finally, based on the examples, the features are analyzed, including the characteristics of wakes and flow field, the distribution of velocity and thrust in rotor disk plane, the interference effects between two rotors and the gain of thrust. Calculated results show that the wake rolls up and expands radially in ground effect when hovering, besides the induced velocity in rotor disk plane is connected with upper rotor, lower rotor and ground. The results show that ground effect causes the more uniform distribution of induced velocity and thrust along the rotor. Besides, the gain of thrust for coaxial-rotor is higher than that of a single rotor when the power is kept the same.
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| Key words: helicopter coaxial-rotor ground effect hover free-wake |
