新型机翼后缘变弯运动机构仿真及其气动影响研究

发布时间：2018-06-28 20:24

本文选题：增升装置 + 空气动力学　；参考：《西北工业大学学报》2016年04期

【摘要】：采用计算流体力学方法和CATIA DMU Kinematics机构仿真,对一套可用于目前及未来民用客机机翼后缘变弯的增升装置系统进行研究,主要包括襟翼运动机构和扰流板下偏。通过运动学分析,采用的襟翼机构可保证巡航阶段后缘变弯过程中机构上下表面无缝,同时满足起降过程对襟翼的运动轨迹的要求。相比简单铰链机构,应用该机构的起飞构型线性段升力系数增加0.05,升阻比的增加量在0.2%~3%范围内;着陆阶段扰流板下偏,较未偏转扰流板的最大升力系数增加1.14%,且线性段上移0.15,显示了该机构具有较高的增升效率。在二维翼型上应用该机构实现后缘变弯度,升阻比有较大提升,且根据来流马赫数的不同改变后缘弯度可以有效地提高阻力发散马赫数。在某远程宽体客机翼身组合体构型上应用该机构实现巡航阶段后缘变弯度,巡航升阻比的增加量在0.345%~2.28%范围内。综上所述,在不增加机构复杂性和重量的前提下,研究的新型机翼后缘变弯运动机构能够有效地提高气动效率。
[Abstract]:Using computational fluid dynamics (CFD) method and CATIA DMU Kinematics mechanism simulation, a set of lifting device system, which can be used in the current and future civil airliner wing bending, is studied, including flap motion mechanism and spoiler downwardness. Through kinematics analysis, the flap mechanism adopted can ensure that the upper and lower surfaces of the mechanism are seamless in the process of changing the bending edge of the rear edge during cruising, and meet the requirements of the flap trajectory during the take-off and landing process. Compared with the simple hinge mechanism, the lift coefficient of the takeoff configuration of the mechanism is increased by 0.05, and the rise-to-drag ratio is increased within the range of 0.2%. Compared with the maximum lift coefficient of the undeflected spoiler, the maximum lift coefficient is increased by 1.14 and the linear section is moved up by 0.15, which shows that the mechanism has a higher lifting efficiency. The mechanism is applied to realize the variable curvature of the rear edge of the two dimensional airfoil, and the ratio of lift to drag can be improved greatly, and the resistance divergence Mach number can be effectively increased by changing the curve of the rear edge according to the different Mach number of incoming flow. The mechanism is applied to the wing body configuration of a long-range wide-body airliner to realize the change of curve of the rear edge in the cruising stage, and the increase of the cruise rise-to-drag ratio is within the range of 0.345% or 2.28%. In conclusion, without increasing the complexity and weight of the mechanism, the new wing trailing edge bending mechanism can effectively improve the aerodynamic efficiency.
【作者单位】：西北工业大学航空学院;
【分类号】：V211.41

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