| 摘要: |
| 针对修正的Greensberg准定常气动理论建立了带后缘附翼的桨叶运动方程.在此基础上,研究了不同的附翼偏角下桨叶扭转角沿着展向的分布规律,同时,也研究了不同的附翼偏转角下桨叶挥舞方向的变形情况.数值结果表明:当附翼偏转角为6°时,桨尖的扭转角为-3.8°;当附翼偏转角为-6°时,桨尖的扭转角为3°.附翼偏转角对桨叶挥舞方向的变形也有很大的影响,当附翼偏转角为6°时,桨尖挥舞位移为0.16R,比附翼无偏转时减少了50.8%.因此,通过后缘附翼的偏转使桨叶产生扭转变形在理论上是可行的. |
| 关键词: 直升机 桨叶 后缘附翼 扭转变形 挥舞位移 |
| DOI：10.11918/j.issn.0367-6234.2010.02.013 |
| 分类号:V214.33 |
| 基金项目:中国博士后科学基金资助项目(20080440888) |
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| Torsion of blade with trailing-edge flap under air loads |
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YIN Wei-long1,2
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1.YIN Wei-long 1,2 (1.Center for Composite Materials and Structures,Harbin Institute of Technology,Harbin 150080,China;2.Postdoctoral Mobile Station of Mechanics,Harbin Institute of Technology,Harbin 150080,China
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| Abstract: |
| The method of twisting the blade using a trailing-edge flap is presented in this paper.The dynamic model of the rotor blade with the trailing-edge flap is developed based on the modified Greensberg quasi-static aerodynamic theory.The effect of flap deflection on the torsion of the blade is investigated.Results show that the angles of torsion are equal to-3.8° and 3° when the flap deflection is 6° and-6°,respectively.The flap deflection has a powerful effect on the blade bending deformation in flapping direction.When the flap deflection is 6°,the tip flapping displacement is 0.16 R.It is decreased by 50.8% in comparison with that without any flap deflection.So it is feasible to twist the blade by using the trailing-edge flap. |
| Key words: helicopter blade trailing-edge flap torsion flap |
