摘要：Civil aviation faces great challenges because of its robust projected future growth and potential adverse environmental effects. The classical Tube-And-Wing(TAW) configuration following the Cayley’s design principles has been optimized to the architecture’s limit, which can hardly satisfy the further requirements on green aviation. By past decades’ investigations the BlendedWing-Body(BWB) concept has emerged as a potential solution, which can simultaneously fulfill metrics of noise, emission and fuel burn. The purpose of the present work is to analyze the developments of critical technologies for BWB conceptual design from a historical perspective of technology progress. It was found that the high aerodynamic efficiency of BWB aircraft can be well scaled by the mean aerodynamic chord and wetted aspect ratio, and should be realized with the trade-offs among stability and control and low-speed performance. The structure concepts of non-cylinder pressurized cabin are of high risks on weight prediction and weight penalty. A static stability criterion is recommended and further clear and adequate criteria are required by the evaluations of flying and handling qualities. The difficulties of propulsion and airframe integration are analyzed. The energy to revenue work ratios of well-developed BWB configurations are compared,which are 31.5% and 40% better than that of TAW, using state-of-art engine technology and future engine technology, respectively. Finally, further study aspects are advocated.

摘要：Blended-Wing-Body(BWB) configuration, as an innovative transport concept, has become a worldwide research focus in the field of civil transports development. Relative to the conventional Tube-And-Wing(TAW) configuration, the BWB shows integrated benefits and serves as a most promising candidate for future ‘‘green aviation'. The objective of the present work is to figure out the effects of the stability margin and Thrust Specific Fuel Consumption(TSFC) on the BWB design in the framework of Multi-Disciplinary Optimization(MDO). A physically-based platform was promoted to study the effect static stability margin and engine technology level. Low-order physically based models are applied to the evaluation of the weight and the aerodynamic performance. The modules and methods are illustrated in detail, and the validation of the methods shows feasibility and confidence for the conceptual design of BWB aircrafts. In order to find out the relation between planform changes and the selection of stability and engine technology level, two sets of optimizations are conducted separately. The study proves that these two factors have dominant effects towards the optimized BWB designs in both aerodynamic shapes, weight distribution, which needs to be considered during the MDO design process. A balance diagram analysis is applied to find out a reasonable static stability margin range. It can be concluded that a recommended stability margin of a practical BWB commercial aircraft can be half of that of a conventional TAW design.

摘要：Strong shock waves and flow separation often occur during the integration of nacelle and airframe for blended-wing-bodies with podded engines. To address this problem, this paper presents an integration method with numerical simulations. The philosophy of channeling flow and avoiding the throat effect on the nacelle and airframe is established based on the analysis of flow interference in the initial configuration. A parametric integration design method is proposed from twodimensional plane to three-dimensional space with control mechanisms and selection principles of the key parameters determined by their influences. Results show that strong shock waves and flow separation can be successfully eliminated under the influence of both the reshaped channel and decelerated inflow below the nacelle. Supersonic regions around the nacelle are effectively reduced, concentrating mainly on the lip position. Thus, a significant cruise drag reduction(8.7%) is achieved though the pressure drag of the nacelle increases.

摘要：This paper puts forward a design idea for blended wing body（BWB）.The idea is described as that cruise point,maximum lift to drag point and pitch trim point are in the same flight *** to this design idea,design objectives and constraints are *** applying low and high fidelity aerodynamic analysis tools,BWB aerodynamic design methodology is established by the combination of optimization design and inverse design *** lift to drag ratio,pitch trim and acceptable buffet margin can be achieved by this design *** 300-passenger BWB configuration based on static stability design,as compared with initial configuration,the maximum lift to drag ratio and pitch trim are achieved at cruise condition,zero lift pitching moment is positive,and buffet characteristics is *** burn of 300-passenger BWB configuration is also significantly reduced as compared with conventional civil *** aerodynamic design is carried out under the constraints of BWB design requirements,the design configuration fulfills the demands for interior layout and provides a solid foundation for continuous work.

摘要：以跨声速机翼设计中权衡气动性能和总体设计要求的工程应用为出发点,在保证机翼结构重量和容积不变的约束下,提出了平面形状优化与剖面翼型优化结合的两步优化设计策略。应用神经网络和遗传算法,建立了相应的设计方法。采用两步优化方法进行跨声速机翼设计,第一步设计中,通过平面形状优化,增大机翼展弦比、减小诱导阻力是机翼气动性能改善的主要原因,但由于结构重量约束,平面形状变化不大,对机翼气动性能改善有限;第二步设计中,以第一步设计所优化的机翼平面形状为基础,并以机翼容积为约束,通过机翼剖面翼型优化,弱化较大马赫数下的激波、减小激波阻力是机翼气动性能改善的主要原因。经过这两步优化设计,机翼在两个设计点下的升阻比分别提高了3.02%和9.96%,阻力发散马赫数由0.854 0推迟到0.865 3,表明两步优化设计方法适合于工程应用。在无结构重量和容积约束下,采用单纯气动最优的平面形状和剖面翼型优化两种设计方法均可明显改善机翼气动性能,但不能满足机翼结构重量和容积不变的设计要求。

摘要：采用直接曲率法(DISC)反设计模块耦合NS方程流场求解程序,建立了具有跨声速翼型和机翼设计能力的气动设计平台。针对翼型表面光顺和跨声速设计中出现的收敛性问题,提出了基于最小二乘法原理的形状改变量曲线拟合方法,可显著改善跨声速设计收敛速度;提出的翼型前缘形状的多项式插值方法,可消除DISC方法中旋转变换而带来的翼型前缘不光顺问题,且具有加速收敛和增强设计稳定性的作用。

摘要：文章针对气动优化设计中高效率和高精度的矛盾,综合响应面方法和遗传算法的优点和不足,采用多项式响应面模型代替原始遗传算法中计算量庞大的目标特性分析模型,建立了多项式响应面模型和遗传算法相结合的翼型优化设计方法,在采用N-S方程进行气动求解达到较高的精度情况下,求解次数显著减少,优化效率大大提高。研究了设计变量对优化设计效率的影响,文中方法在较少设计变量、较少N-S方程求解次数情况下,即可得到满意的优化设计结果。设计区间对响应面模型精度的影响显著,合适的设计区间既可保证模型精度,减少响应面预测结果和CFD计算结果的偏差,又可获得最佳优化结果。文中方法适用于翼型的单设计点和多设计点优化设计问题,具有原理简单、适应面宽、快速易行,且精度高等特点,可广泛应用于工程设计问题中。

摘要：For the problem that the flow separation on the flap lowers the aerodynamic performance of high lift system,an investigation was carried out on using micro vortex generators(VGs) to control the separation on flap of the swept constant chord half-model(SCCH) high-lift configuration,at a small to medium angle of attack,by experimental and numerical *** basic flow characteristics of SCCH landing configuration were analyzed by using numerical method to provide required information for the design of micro ***,by keeping the cruise configuration intact,the preliminary design procedure and design methods of micro VGs were *** addition,the micro VGs were *** effects of VG's arrangement and geometric parameters,such as the arrangement mode,chordwise position,arrangement angle,height and spanwise distance,on controlling efficiency were investigated by using numerical *** the parameters of preliminary VGs were adjusted as the basis configuration for wind tunnel *** experiments were accomplished in NH-2 wind tunnel for validating the numerical method,as well as obtaining the design principles and methods of micro *** parameters of VGs were also optimized based on the *** experimental results showed that the numerical design method can serve as an efficient and accurate design *** lift and drag were increased by 10% and 14%,respectively in landing state,which satisfied the requirements for ***,it was concluded that the established design principles and methods for micro VGs in this investigation can be used in engineering application.

摘要：在分析基于线性理论的跨、超音速面积律设计方法的优点与不足的基础上,依据CFD方法在流场分析和气动力计算方面的优势,提出了面积律概念指导下的CFD技术减阻设计方法。与传统的超音速面积律方法比较,该方法给出了面积律作用的物理原因,直接建立了横截面积分布与流场品质之间联系,修形设计目标直观明确、减阻效果明显,且设计工作量小,具有进行复杂外形超音速减阻设计的能力。算例表明,该方法对复杂外形的强约束减阻设计具有很好的适应性,对现役飞机改型是一种工程上简单、易行、外形改动小、结果可靠的修形设计方法;对新型飞机设计具有方案颠覆性小、周期短的优点。具有良好的工程实用性和可操作性。

摘要：从研制中国未来具有全球市场竞争力的大型客机为出发点,结合波音和空客下一代大型客机的研究思路以及美国和欧洲近年来围绕大型客机的若干重大研究计划,较深入地分析了在我国的大型客机的研制中实现安全性、经济性、舒适性和环保性总体设计思想的重要性和必要性。在此基础上,就如何建立大型客机综合考虑安全性/经济性/舒适性/环保性设计与评价准则体系,评价思路与方法进行了探索和研究,这对我国大型客机的研制具有借鉴意义。此外,依据详实的数据,分析了2种新概念布局方案,即"BWB-C"型翼布局方案和"大载重浮升式飞机"方案,与目前常规布局方案飞机优缺点,同时分析了应用多学科精细设计方法对于提高大型客机飞机经济性的效果。在此基础上,指出了概念创新和多学科优化精细设计方法大规模应用对于提高大型飞机安全性/经济性/舒适性/环保性的重要意义。