8-美国未来亚声速运输机方案研究介绍.ppt

波音团队的概念设计方案 洛-马团队的概念设计方案 洛-马团队提出的各种布局方案 洛-马团队的几种方案的比较 洛-马团队的几种方案的评估结论 关于噪声要求 Noise Goal of -42dB below Stage 4 is “tough” Challenge. PSC with UHB UltraFan Engine and 6 degree Glide Slope get within 3dB of Goal. UHB Engine Contributes to Half of Goal. Reduced Weight, Higher Approach Path Suppression Technologies Contribute “other” Half. 动力装置（1998年） 先进涡扇发动机（2025年） 优先系统概念用的超扇发动机（2025年）UltraFan Engine 关于推进系统的结论 Propulsion is a “Key” ERA Vehicle Technology Driving to Extreme BPR is Best Path to Show “Simultaneous” Compliance with NASA ERA Goals Advanced Core Technology – High OPR LFC to Reduce Installed Nacelle Drag Further Optimization to Find Best Compromise between BPR, Nacelle Drag and Fan Weight may Result in a Lower BPR. 缩比验证机 诺-格团队的概念设计方案 诺-格团队的几种布局方案 先进技术的应用 评估结果 缩比验证机 缩比验证机的尺寸 缩比验证机的总体布置方案 缩比验证机的结构布置方案 噪声评估工具MIDAS的计算流程 方案设计分析与优化的流程 方案的评估 与NASA设计目标的对比 Fuel burn ：63.49% below that of the reference vehicle Noise ： 69.6 EPNdB below the FAR Stage 4 requirement Emission： 90.59% below the CAEP/6 requirement Balanced field length ：4,999 feet. reference vehicle Preferred configuration 先进技术应用对降低油耗的贡献 Technology contributions to mission fuel burn reduction 先进技术应用对降低噪声的贡献 Technology contributions to community noise reduction 先进技术应用对降低排放量的贡献 CAEP/6 LTO NOx Emissions Requirement and N+3 Achievements 先进技术成熟度的时间表 Assumed Technology Maturation and Implementation Timeframe 先进技术成熟度发展的规划 Swept-Wing Laminar Flow Slat Integration Raymer 的设计方案Conceptual Research Corporation Advanced Technology Subsonic Transport Study NASA TM-2011-217130 设计要求 性能要求 中型客机（180座级） 类似波音的 B737-800 油耗要求 与B737-800相比，降低70%。 噪声与排放 暂不考虑 总体布局方案 Tailless only concepts which actually reduce the total wetted surface area will be winners Propulsion Open rotors aft-fuselage-mounted engines Retracting canard and chin rudder A retracting canard horizontal tail surface is provided, mostly to counter the huge nose-down pitching moments created by the large wing flaps. An all-moving chin rudder (retracting