1、美国未来亚声速运输机N+2和N+3方案研究介绍余雄庆余雄庆南京航空航天大学南京航空航天大学NASA给出未来客机的设计目标N+2和N+3运输机的研究项目N+2N+3集成系统研究项目集成系统研究项目ISRP基础航空项目基础航空项目FAP环境责任环境责任航空计划航空计划ERA无人机系统无人机系统UAS亚声速亚声速固定翼固定翼SFW亚声速亚声速旋翼旋翼SRW超声速超声速SUP高超声高超声HYP波音波音诺诺 格格MITNASA波音波音洛洛 马马诺诺 格格Integrated Systems Research Program(ISRP)Goal:Conduct research at an integra
2、ted system-level on promising concepts and technologies and explore/assess/demonstrate the benefits in a relevant environment.Environmentally Responsible Aviation(ERA)ProjectTechnology development project,that will explore and assess new vehicle concepts and enabling technologies through system-leve
3、l experimentation to simultaneously reduce fuel burn,noise,and emissions.Unmanned Aircraft Systems(UAS)in the National Airspace System(NAS)Project The goal is to contribute capabilities that reduce technical barriers related to the safety and operational challenges associated with enabling routine U
4、AS access to the National Airspace System(NAS).Fundamental Aeronautics Program(FAP)GoalConduct cutting-edge research that will produce innovative concepts,tools,and technologies to enable revolutionary changes for vehicles that fly in all speed regimes.Subsonic Fixed Wing(SFW)Explore and develop too
5、ls,technologies,concepts,and knowledge for improved energy efficiency and environmental compatibility for sustained growth of commercial aviation.Subsonic Rotary Wing(SRW)Enable radical changes in the transportation system through advanced concept rotary wing vehiclesSupersonics(SUP)Develop tools,te
6、chnologies and knowledge to overcome the environmental&performance barriers to practical civil supersonic airliners.Hypersonics(HYP)Develop tools,technologies and knowledge to enable hypersonic air-breathing vehicles and high-mass entry into planetary atmospheres.Environmentally Responsible Aviation
7、N+2 Advanced Vehicle ConceptsN+2的设计方案介绍设计要求与完成内容Five Tasks Tasks 1-4 relate to a full sized concept Task 5 relates to a subscale testbed vehicleTask 1 Future Scenario What does the world that you are designing to look like?What is the NextGen scenario in 2025 that you are designing to?What is the in
8、terplay between your concept and NextGen?设计要求与完成内容Task 2-Preferred System Concept(PSC)Develop a conceptual design of a 2025 EIS subsonic transport passenger and/or cargo Compile Concept Data Packages Configuration geometry and dimensions Drag polars and performance predictions Weight statement Propu
9、lsion system performance and weights Compile Concept Data Packages for:1998 tube and wing Baseline system analysis toolset 2025 EIS tube and wing Separate configuration from technology设计要求与完成内容Tasks 3&4-Technology Development Roadmaps Technology Maturation Plans(TMPs)15 year Roadmap for each of the
10、critical technologies Key research,analyses,tool and method development Necessary ground and flight tests Starting and ending TRL&SRL Cost,schedule and technical outcome FY 2013 2015 Critical Technology Demonstrations Long poles and enabling technologies Scalability Sorted and prioritized by:Airfram
11、e Integrated Propulsion/Airframe Propulsion Subscale Testbed 设计要求与完成内容Task 5-Subscale Test-bed Vehicle Conceptual Design of a Subscale Testbed Vehicle(STV)Proposal for completing Preliminary Design of the STV ROM cost and schedule for completing design,construction and initial flight testing of the
12、STV STV requirements Same configuration as the PSC Same Mach and cruise speed as PSC Retractable Landing Gear Sufficient scale to demonstrate noise,emissions burn goals Adaptable/reconfiguarable for future modifications 研究团队BoeingPratt&Whitney Rolls-Royce MIT Cranfield AerospaceLockheed MartinRolls-
13、RoycePropulsionGeorgia TechAcousticsMetron AviationEnvironmentMiddle Georgia CollegeOperations Northrop Grumman Rolls-Royce propulsion Wyle Laboratories noise analysis and airspace integration Iowa State University technology maturation波音团队的概念设计方案波音团队提出的几种布局方案各布局方案的先进技术应用波音团队的优先系统方案（PSC）BWB方案的关键技术评估
14、结果：油耗与噪声评估结果：油耗与噪声缩比验证机缩比验证机-三面图缩比验证机：结构方案洛-马团队的概念设计方案洛-马团队提出的各种布局方案1998 Baseline 2025 Advanced Conventional 2025 Preferred System Concept 洛-马团队的优先系统方案（PSC）The Lockheed Martin ERA design is a non-traditional“Box Wing”concept for improved structural and aerodynamic efficiency.洛-马团队的几种方案的比较洛-马团队的几种方案的
15、评估结论油耗和排放量要求能满足要求，但低于第油耗和排放量要求能满足要求，但低于第4阶段要求的阶段要求的42dB的噪声要求不能满足的噪声要求不能满足。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 Tec
16、hnologies 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 D
17、rag 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诺-格团队的优先方案评估结果缩比验证机Baseline STV(55%Scale of PSC Cargo)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Advanced concept studies for commercial subsonic transport airc
18、raft for 2030-35 EISN+3 的设计方案的介绍完成内容 内容内容1：市场分析与设计要求拟定：市场分析与设计要求拟定 内容内容2：概念设计方案：概念设计方案 布局与总体布置布局与总体布置 先进技术的应用先进技术的应用 主要参数设计、分析与优化主要参数设计、分析与优化 方案评估与对比方案评估与对比 内容内容3：关键先进技术线路图与风险评估：关键先进技术线路图与风险评估研究团队1.Boeing,GE,GA Tech 2.NG,RR,Tufts,Sensis,Spirit 3.MIT,Aurora,P&W,Aerodyne4.GE,Cessna,GA Tech（20Pax）5.NAS
19、A,VA Tech,GT6.NASA波音团队N+3方案Subsonic Ultra Green Aircraft Research（SUGAR）NACA CR-2011-216847市场定位与设计要求 座级：座级：154座（二级布置）座（二级布置）航程：航程：3500 nm机队市场预测（机队市场预测（2030年）年）巡航速度巡航速度：0.785 起降场长：小于起降场长：小于8190 ft飞行任务剖面2008年的飞行剖面年的飞行剖面飞行任务剖面2030年的飞行剖面年的飞行剖面总体布局方案1.SUGAR Free Current technology,similar to 737 class ai
20、rcraft.Used as Baseline.2.Refined SUGAR Reference conventional configuration with estimated 2030-2035 technologies.Use as direct comparison to the advanced concepts.3.SUGAR High High span strut-braced wing configuration with advanced 2030-2035 N+3 technologies.Turbofan and open fan propulsion concep
21、ts are supplied by GE.4.SUGAR Volt Electric Trade Aircraft that builds off of SUGAR High configuration to add electric propulsion technologies.Considers a variety of electric-propulsionarchitectures(Battery electric only,fuel-cell gas turbine hybrid,battery electric gas turbine hybrid)which are supp
22、lied by GE.5.SUGAR Ray A HWB configuration that uses a similar suite of advanced technologies as the SUGAR High.Primary design emphasis is on reducing aircraft noise,while maintaining performance similar to the SUGAR High.发动机方案客舱布置方案客舱布置方案先进技术应用 气动技术气动技术 材料和结构技术材料和结构技术 系统技术系统技术 发动机技术发动机技术2030年预计可采用的
23、先进技术，分四个方面：先进气动技术先进材料和结构技术先进系统技术先进发动机技术分析与设计工具气动气动Aerodynamic Buildup MethodsCASES(Computer Aided Sizing and Evaluation System)a heritage empirical Douglas applicationvortex lattice methods to calculate induced drag.HWB reference drag buildup uses wing-body CFL3D RANS重量重量CWEP,a Boeing proprietary we
24、ights parametric estimating tool,is based on empirical data of current and existing commercial transports.It was calibrated to a SUGAR Free class aircraft using extensive in-house data.推进系统推进系统NPSS cycle models性能性能The Boeing Mission Analysis Program(BMAP)Low Speed Performance System(LSPS)总体参数选择和优化总体
25、参数选择和优化Boeings Aircraft Design Navigator(ADNav)It provides the capability to scale engine thrust and wing area and provides the ability to size airplanes to their optimum sizes given a set of constraints.各方案特性的评估方案评估（与NASA的目标对比）每座海里油耗每座海里油耗 和和 炭排放量炭排放量MIT团队的设计方案N+3 Aircraft Concept Designs and Trade
26、 Studies,Final ReportNASA/CR2010-216794市场分析与设计要求中型客机（中型客机（180座级）座级）类似类似Boeing B737-800大型客机（大型客机（350座级）座级）Boeing B777-200LR设计要求设计要求工作流程Step 1-Determine a baseline reference aircraft that can be used as the basis of comparison for each of the concepts generated.Step 2:Establish a well-documented missi
27、on scenario(including aircraft requirements such as payload capacity,range)to establish comparative parameters of the different aircraft concepts.Step 3:Develop metrics and tools for designing and evaluating vastly different aircraft configurations.Step 4:Develop candidate technologies and concepts
28、of the technologies that could have the greatest impact in terms of the evaluated metrics.Step 5:Group the technologies into aircraft concepts that employ the most favorable technology concepts.Step 6:Evaluate aircraft performance using mission scenario from Step 2Step 7:Compare and contrast aircraf
29、t concepts based on program objectives and metrics.中型客机总体布局方案Double Bubble Fuselage with lifting noseEmbedded aft enginesReduced cruise Mach 0.74 with unswept wingEliminates need for LE slat,via increased CLmax from unsweeping of wingConfiguration exploits synergy in fin stakesAllows for small verti
30、cal tails,via small engine-out yaw momentsRequires no typical weight penalty of T-tail,via twin pi-tail finsMulti-segment rearward acoustic liners for noise reduction客舱布置方案先进技术应用 Ultra high bypass ratio engines Advanced structural materials Reduced structural load margin through the use of the struc
31、tural health monitoring and gust load alleviation Natural laminar flow on the bottom wing Advanced engine component efficiencies Advanced engine component materials Variable area nozzle for noise reduction at takeoff and fan operability Rearward acoustic liners for noise reduction Undercarriage fair
32、ings for noise reduction Approach procedures to reduce noise Lean Direct Injection(LDI)advanced combustor分析与设计工具 TASOPT(Transport Aircraft System OPTimization)A program for simultaneously optimizing the airframe,engine,and operating parameters of a wing+tube transport aircraft Rely on low-order phys
33、ical models that implement fundamental structural,aerodynamic,and thermodynamic theory and associated computational methods for all primary predictions Main models:Weight and Structural Models Aerodynamic Models Engine Models Stability and trim Mission profiles设计方案的性能评估方案评估（与NASA的目标对比）先进技术应用对降噪的贡献Te
34、chnology Contributions to NASA noise reduction goal先进技术应用对减排的贡献Technology contributions to NASA LTO NOx reduction goal先进技术应用对降低油耗的贡献Technology contributions to NASA PFEI goal大型客机总体布局方案 HWB configuration with lifting nose Embedded aft engines Distributed propulsion system Thrust vectoring,variable ar
35、ea nozzle客舱布置方案先进技术应用气动气动 uses an all-lifting hybrid wing body(HWB)with control and low speed lift augmentation being provided by outer wing elevons,drooped leading edge,thrust vectoring and winglets.结构结构 Advanced materials and load reduction technologies such as gust load alleviation,flight envelop
36、e protection,predictive path planning,and structural health monitoring.边界层吸入（边界层吸入（Boundary Layer Ingestion）BLI by the engines could benefit the vehicle aerodynamic performance by eliminating kinetic energy dissipation in the wake and by reducing dissipation in the mixing of engine exhaust jet.推进系统推
37、进系统 advanced geared distributed turbofan propulsion system Major improvements in material technology and flowpath aerodynamics Advanced Lean Direct Injection(LDI)combustors分析与设计工具HWBOpt Matlab programHWBOpt program flow chart分析与设计工具HWBOpt Matlab program Mass the structural weight model for the HWB i
38、s based on a Response Surface Model(RSM)based on WingMod The propulsion system weight buildup uses various empirical weight models and weight scaling laws.The weight calculation of planetary gears uses the correlation from NASA GRC WATE+model.分析与设计工具HWBOpt Matlab program Engine Engine cycle performa
39、nce and sizing calculations were conducted using a semi-perfect gas cycle model.分析与设计工具HWBOpt Matlab program Aerodynamics AVL lift distribution,induced drag and neutral point were computed using a vortex-lattice analysis code.MSES Profile,viscous and wave drag for the outer wing 9%thick supercritica
40、l airfoil was computed offline using MSES at the cruise Mach number and a representative Reynolds number.The resulting drag polar is integrated as a lookup table as a function of sectional lift and sweep.Hoerner correlations The centerbody profile and viscous drag was computed using Hoerner correlat
41、ions for bodies of revolution.Validation Results from the Boeing CFD study of the Silent Aircraft and NASA SAX-40F designs were used to validate this analysis methodology分析与设计工具HWBOpt Matlab program优化A hybrid multi-objective genetic algorithm was utilized.方案设计结果主要几何参数主要几何参数三面草图三面草图方案评估与与NASA的设计目标对比的
42、设计目标对比先进技术应用对降低油耗的贡献Technology contributions to PFEI goal诺格公司团队的方案NASA N+3 Subsonic Fixed Wing Silent Efficient Low-Emissions Commercial Transport(SELECT)Vehicle StudyNASA CR 2010-216798工作流程市场分析座级预测座级预测市场分析航段距离统计分析航段距离统计分析设计要求总体布局方案候选方案候选方案总体布局方案发动机候选方案发动机候选方案总体布局方案最终方案：常规布局最终方案：常规布局+三轴涡扇三轴涡扇先进技术应用S
43、wept Wing Laminar FlowLarge Integrated StructuresAeroservoelastic StructuresM5 Ultra High-Performance FiberCarbon Nanotube Electrical Cables3-D Woven and Stitched CompositesAdvanced MetallicsLanding Gear FairingsAdvanced Acoustic Inlet LinerUltra-High Bypass Ratio of 18CMC Turbine BladesLean-Burn CM
44、C CombustorIntercooled Compressor StagesSwept Fan Outlet Guide VanesFan Blade Sweep DesignLihgt weight Fan/Fan CowlCompressor Flow ControlActive Compressor Clearance ControlVariable Geometry Nozzles发动机（三轴涡扇）发动机（三轴涡扇）机体机体分析与设计工具Flight Optimization System(FLOPS)FLOPS is a tool developed by NASA Langle
45、y Research Center that allows for the preliminary design and analysis of flight vehiclesOptimization MethodAirspace Concepts Evaluation System(ACES)ACES is a tool that simulates nationwide air traffic management,flight,and airspace operations center functionsNumerical Propulsion System Simulation(NP
46、SS)an industry standard software in engine developmentAcoustic Liner Design ProcessModel for Investigating the Detectability of Acoustic Signatures(MIDAS)System Effectiveness Rankings用用B737-800校正校正FLOPSACES Simulation Components and Data Flow Diagram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
47、burn：63.49%below that of the reference vehicleNoise：69.6 EPNdB below the FAR Stage 4 requirementEmission：90.59%below the CAEP/6 requirementBalanced field length：4,999 feet.reference vehiclePreferred 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Techn
48、ology 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 IntegrationRaymerRaymer 的设计方案的设计方案Conceptual Research CorporationAdvan
49、ced Technology Subsonic Transport StudyNASA TM-2011-217130设计要求 性能要求性能要求 中型客机（中型客机（180座级）座级）类似波音的类似波音的 B737-800 油耗要求油耗要求 与与B737-800相比，降低相比，降低70%。噪声与排放噪声与排放 暂不考虑暂不考虑总体布局方案Tailless only concepts which actually reduce the total wetted surface area will be winnersPropulsionOpen rotorsaft-fuselage-mounted
50、 enginesRetracting canard and chin rudderA 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).Fuselage conventional passenger compartment,cargo bay,cockpit,landing gear.关键技术
