Agenda. HISAC Composition and Objectives Main Design Problems Work Organisation General Progress

Transcription

1 HIgh Speed AirCraft (HISAC) A European `` Integrated Project 1

2 Agenda HISAC Composition and Objectives Main Design Problems Work Organisation General Progress 2

3 HISAC PARTNERS Industry SME Research Dassault Aviation Alenia Aeronautica CFS Engineering EADS Deustchland Rolls Royce RUAG Aerospace Sukhoï Civil Aircraft SENER SNECMA SONACA Volvo Aero Corp. ADSE ESTECO IBK INASCO NUMECA Others EUROCONTROL Centers ARA CIAM CNRS DLR FOI INRIA IoA ITAM NLR ONERA TsAGI Universities Chalmers Cranfield ECL LMFA EPFL ISVR KTH NTUA TCD Napoli 37 Partners from 5 sectors 3

4 HISAC PARTNERS SONACA NUMECA EEC TCD ADSE NLR VOLVO FOI Chalmers KTH EADS M IBK DLR IoA RRUK ARA CU SCA ISVR CIAM TsAGI DASSAV ITAM ECL LMFA ONERA SM CNRS CFS ALA INRIA RUAG Uni-NA DPA INASCO SENER EPFL ESTECO NTUA 37 Partners from 13 countries 05_DV_096_01 4

5 HISAC General Objectives Technically Feasible Environmentally Compliant Supersonic Small Size Transport Aircraft 5

6 Agenda HISAC Composition and Objectives Main Design Problems Work Organisation General Progress 6

7 Main Design Problems Cruise SONIC BOOM EMISSIONS N0x Descent Supersonic climb & acceleration Transonic Acceleration Reserve Subsonic climb OPERATIONS FROM REGIONAL AIRPORT NOISE Take off Landing RANGE > 3500 NM 7

8 Design Problems: Range CALCUTTA HONG KONG BANGKOK SINGAPORE JAKARTA DARWIN SYDNEY LOS ANGELES 2 x 4000 nm - M =1.8 8 hours 6500 nm - M = hours RIO DE JANEIRO BUENOS AIRES KARACHI JEDDAH MUSCAT BANGUI ADDIS ABABA GLOBAL JETS reach business jets range limit: ~ 6500 Mach = 0,8 time ~ 14 hours Demand for travel time reduction: -20% to 50% 8

9 Boom Intensity P max (N/m²) 140 Design Problems: Sonic boom SSBJ CONCORDE QSP TARGET : ACCEPTABLE NOISE LEVEL? 2 psf 0,3 psf Mass (tons) A/C Weight & Size Altitude Shaping Achievable Target : max overpressure 1 psf 2/3 reduction of initial overpressure? Robust to : - cruise altitude? - atmospheric tubulence? Boom shaping Is the achievable boom mitigation compatible with overland flight? 9

10 Supersonic Design Problems Breguet-Leduc formula: Lift/Drag ratio End of climb weight Range = x ln x TSFC End of cruise weight V Lift/Drag Ratio : Aerodynamic performance TSFC : Specific Consumption Engine Performance Mi/Mf : Structural index -- MFuel/Mtow need ( around 50%) 10

11 Supersonic Lift to Drag ratio Concorde SSBJ Same Span over Fuselage Diameter Ratio Improvement in L/D requires low wing thickness 11

12 Noise / Fuel Consumption Optimal Supersonic By Pass Ratio near to 0! Classical Subsonic By Pass Ratio above 4! How to reduce the impact of this constraint? 1. Aircraft : Engine Integration Drag minimisation 2. Engine : Variable geometry and Mixer-Ejector 12

13 Robustness / Sensitivity Some Structural Ratios (Mfuel / MTOW): Airbus A320 : 0.26 Falcon 2000 : 0.33 Falcon 2000 EX Easy : 0.40 Concorde : 0.52 Tupolev 144 : 0.5 SSBJ : 0.53 High Sensitivity of the General Performances to Uncertainties 13

14 Supersonic Design Problems Feasibility without any Major Engine Technological Step will require: Very low wing thickness Efficient aerodynamic engine integration Quality and Precision of Evaluations are Key Factors 14

15 Subsonic Design Problems Approach speed is the other major constraint Following aspects have to be analyzed: Angle of attack at landing (visibility constraint aspects) High lift device performances Approach instability : flap additional lift 15

16 Agenda HISAC Composition and Objectives Main Design Problems Work Organisation General Progress 16

17 HISAC General Logic Environmental Objectives & Constraints - WP1 (Community noise, Emissions, Sonic boom Criteria) Models, Tools & Methods - WP2 (Noise, Emission, Sonic Boom, Engine, Aerodynamic, MDO) Engine key technologies - WP3A (Variable Cycle Engine, Nozzle Noise reduction) Integration and Aircraft Definition (WP 4 & 5) Airframe key technologies - WP3B (Forced laminar flow, high lift devices, variable geometry wing) 3 TEAMS/ 1 BENCHMARK CASE 17

18 Requirements for First Loop 18

19 HISAC Break Down a Year 1 T 1 T 2 T 3 T 4 Year 2 Year 3 Year 4 T 5 T 6 T 7 T 8 T 9 T 10 T 11 T 12 T 13 T 14 T 15 T 16 Main milestones of the HISAC project Milestone M6 Administrative decision point M12 Milestone M18 Administrative decision point M24 Milestone M30 Administrative decision point M36 Milestone M42 WP1 Initial objectives Environmental objectives & criteria Environmental impact assessments WP2 Initial modelling Modelling developpment Modelling support & updates WP3 Key Technology Selection Key technologies studies & assessments Key technologies syntheses Models construction & tests WP4 Global acoustic, sonic boom & aerodynamic concepts Detailed shapes Numerical / experimental assessments Key integration syntheses Models construction & tests WP5 SelCo ectinfi on gur of ati theon AirFa cramili ft es First Iteration Design with available MDO process Decision Point & req tea uir ms em reo ent rie s nta up tio dat ns e Second Iteration Design with improved MDO process Decision Point & req tea uir ms em reo ent rie s nta up tio dat ns e Third Iteration Design with improved MDO process trade-off studies trade-off studies MDO Methods MDO Bencharking specific & global design syntheses 4 year study 26 MEuros 19

20 Planning Reference Configuration choice (10th March, 2006) Today End of Phase 1 T0 May 2005 WS1 WS2 WS3 November 2006 July 2005 Oct 2005 March 2006 Detailed external shape definition Cross check evaluations Derivatives studies Tools and Models 20

21 Agenda HISAC Composition and Objectives Main Design Problems Work Organisation General Progress 21

22 Team A : Dassault

23 Team B : Alenia Long Range Concept (Laminar wing shape) 23

24 Team C : Sukhoï Configuration 1 (low boom) Configuration 2 (variable geometry) Configuration 3 24

25 Reference Configuration Support for the crosscheck between the 3 Teams Models and Tools benchmarking Uncertainties reduction Support for Key Points Feasibility study Starting point for Wind Tunnel Models definition This configuration is not supposed to be the final one. 25

26 Reference Configuration 26

27 HISAC Reference Configuration is now defined Next main milestone is October 2006: Environmental Studies Results ( WP1 ) First Set of Tools Development ( WP2 ) First Results of Technology Studies ( WP3 ) Aerodynamic Models Definition ( WP4 ) First Results of Cross check and Update of Requirements for the Second Loop ( WP5 ) 27

28 HISAC A very ambitious project for Europe : Cooperation: 37 partners, 5 sectors, 13 countries including Russia High technology product Economically viable and Environmentally compliant 28

29 END 29

30 Work Programme Expected outcome HISAC Quantified Objectives: Environmental objectives Noise ICAO Chapter 4 less 8dB NOx emissions High altitude:less than 10g per kg fuel burnt (5g in the long term) At landing and take-off: comparable to subsonic aircraft Sonic boom less than 15 Pa (tbc) differential pressure (overland flight) Commercial characteristics objectives Size of cabin 8 to 16 passengers Speed transonic to M 1.8 Range 3500 to 4500 nm (~6000 to ~9000 km) Airfield length 7000 ft 30