Trim Drag Prediction for Blended-Wing-Body UAV Configuration

A rapid method of the trim drag prediction for the blended-wing-body unmanned aerial vehicle(UAV)configuration is proposed.The method consists of four steps.The first step is to parameterizedly model the blended-wing-body UAV configuration;the second is to analyze the aerodynamics of the geometric model;the third is to create aerodynamic surrogate model;and the final step is to predict the trim drag using the surrogate model.Hence,a tool for trim drag prediction is developed by integration of the four steps.The impacts of the allocation of control surfaces,position of gravity center and planform parameters on the trim drag are investigated by using the tool.Results show that using the control surface in outer wing for trim has an advantage of lower trim drag,and the position of gravity center has a primary impact on the trim drag.Moreover,the planform has secondary impacts on the trim drag.

有无涵道动力下的类BWB低速布局气动特性研究

随着航空飞行器的不断发展,新型非常规气动布局研究早已成为世界航空大国的关注焦点。基于TRIP 3.0软件平台通过等效盘模型应用到涵道风扇内外流一体化模拟中,完成对类BWB低速布局有无涵道风扇动力下的气动特性和流场影响分析。首先,对某单独螺旋桨验证算例进行分析;然后,对单独涵道风扇进行计算,得到设计推力下的涵道动力叶片数、安装角及转速等参数;最后,将设计推力下涵道动力参数应用到类BWB低速布局全机有无动力模拟中。结果表明:计算拉力和扭矩值与试验值吻合较好;尾部布置的涵道动力对机身后段及尾翼压力分布影响显著;涵道对前方气流抽吸作用,加速机身后段上表面气流流速,减小内侧平尾有效迎角,对机身和平尾升力以及俯仰力矩系数影响较大;在小迎角状态下,涵道动力对机身增升作用明显,会产生明显低头力矩,但对平尾作用正好相反,且两者增量大小相当,使得全机增升效果不显著,且俯仰力矩变化较小。

A deformation criterion of pressurized non-circular cross-section cabin and its effects on cruise performance of BWB civil aircraft

Blended-Wing-Body(BWB)aircraft is promoted as one of the most possible layouts to achieve more sustainable civil aviation.Due to the non-circular cross-section of the center-body,a bulge deformation forms over the upper surface of the body under the coupled loads of the internal pressurization of the cabin and the aerodynamic bending moments of the wing,which reduces the lift-to-drag ratio of BWB aircraft.Under a limited deformation,the relationship between the aerodynamic performance and the structural weight needs to be studied.In this work,the effects of stiffness constraints on the center-body deformation,structural weight of the airframe and aerodynamic performance were investigated by using an analytical model of the Pultruded Rod Stitched Efficient Unitized Structure(PRSEUS)for the airframe and the computational fluid dynamics method,respectively.The results show that as the stiffness constraint increases,the spacings between the rod stringers and the frame stiffeners decrease,and the structural weight increases inversely.A 5.2% reduction of the lift-to-drag ratio is encountered at cruise for a medium deformation design of 42.8 mm/m.A higher aerodynamic penalty is suffered when the stiffness constraint is further released.The final deformation criterion is different when the weight vector of the aerodynamic performance and structural weight is different.

基于分布式动力的翼身融合飞机整流罩气动设计

整流罩设计对基于分布式动力的翼身融合(BWB)飞机气动特性会产生显著影响。为了揭示在边界层吸入(BLI)效应下整流罩的设计参数对飞机气动特性的影响及其原因,采用计算流体力学(CFD)方法和Morris敏感度分析法对此布局飞机气动特性进行了详细研究,得到了整流罩主要设计参数对飞机气动特性影响的敏感度和耦合关系,并对典型设计参数下的流动特性进行分析。结果表明:对飞机气动特性影响较大的参数是整流罩特征截面2和3的最大厚度,这是因为其增大了当地截面的厚度和弯度,进而影响了整流罩表面的压力分布;在流量系数减小和进气边界弦向位置前移时,最大厚度增大会造成背风面发生局部分离;整流罩特征截面2和3的最大厚度对气动特性具有较强的耦合影响。

翼身融合飞机的空气动力学研究进展

翼身融合飞机(Blended Wing Body Aircraft-BWB Aircraft)是一种新型高升阻比无尾布局的大型运输机,其气动特性的研究是BWB布局飞机克服众多技术难题的基础。文章首先简述了BWB布局的研究历程,给出巨型BWB布局飞机的总体几何特征参数和基本性能,并简述风洞和自由飞试验情况;接着介绍BWB研究中的多学科优化平台,着重讨论气动优化技术,它是解决BWB布局气动问题的基础手段之一;然后综述BWB布局研究的热点领域:气动特性研究、气动弹性研究和发动机/机体一体化设计研究;最后提出BWB布局发展趋势的若干方面。

翼上大涵道比发动机BWB布局一体化气动优化

考虑动力影响的气动布局一体化设计是挖掘飞行器设计潜力的重要环节。基于非结构混合网格并行RANS求解器,面向消除梯度计算量对设计变量个数以及变形网格技术的依赖性需求,进行了全过程离散伴随方程的推导。在构造离散伴随方程的基础上,通过迭代反压调整建立精确流量控制进排气数值模拟技术,并推导离散伴随方程边界条件矩阵。进一步以某翼上安装大涵道比发动机翼身融合(BWB)布局为研究对象进行了一体化设计研究。优化结果表明,所提出的优化方法显著提升了气动性能,验证了方法在强约束、考虑动力影响的一体化设计问题中的实用性,为未来翼上布局民用飞机设计提供有力的技术支撑。