Overview of Hypersonics in Europe
Laurent SERRE, ONERA
17th AIAA International Space Planes and Hypersonic Systems and Technology Conference Sept.24-28 2012 Tours, France
1 Hypersonics in Europe: general roadmap
2010 2011 2012 2013 2014 2015 EXPERT IXV SKYLON
Space access SPACE PLANE FAST 20XX
LAPCAT 1 & 2 ATLLAS 1 & 2
transport ZEHST Atmospheric HIKARI
LEA
forDMR HEXAFLY Methodology
SHEFEX 1, 2 & 3 CHATT HYPROB 2
Technologies Other R&T Combustion modelling, MHD… Hypersonics for space access
IXV Intermediate eXperimental Vehicle ESA Program, Thales Alenia Space prime contractor Validate technologies required for large down & cross range and precision landing on a real LEO rentry trajectory Recoverable system to allow post-flight technology inspection and analysis
Pre-flight reviews mid 2014 for ground segment and flight vehicle Flight in automn 2014
3 See AIAA papers by TAS, DEIMOS, UniRoma Hypersonics for space access
SKYLON (Reaction Engines Limited)
Fully reusable single stage to orbit launch vehicle Delivers 15 tonnes to a 300 km equatorial orbit Payload bay is 4.8m diameter by 13m length Objective: operational around 2020
Key innovation for SKYLON viability: SABRE (Synergistic AirBreathing Rocket Engine)
Combined cycle engine: airbreathing mode up to Mach 5 rocket mode to orbit
Key technology lightweight pre-cooler heat exchangers demonstrated in 2012
The next development phase (3) last 3 years and includes ground and flight system demonstrations see AIAA paper Roger Longstaff
4 Hypersonics for space access (Tourism & transport)
Astrium Spaceplane : a technology enabler for High Speed Transport
Blending Aviation & Space Several space missions : from scientific to space access for general public Two kind of propulsion : aero engines (turbofans) and rocket engine Certification of vehicle design & operations
A technology enabler for civil High Speed Transport «Stretched» flight envelope vs. legacy aviation : altitude & speed e.g. Management of several propulsion classes Certification of space-like products
Pre-development on going in Europe & abroad Operations by 2020
5 Hypersonics for space access (Tourism & transport)
FAST20XX Advanced concepts for suborbital transport EU FP7 Program, coordinated by ESA with 16 partners, 36 months until end 2012
Low energy concept (horizon 10/15 years) X-Prize type mission, small range few passengers, air-launched several launching strategies adressed
High energy concept: SpaceLiner (horizon 2040+ ) very long range ultra fast transport 50 (to 100) pax from e.g. Australia – Europe in 90 min fully re-usable, two stages, rocket propulsion Vertical TO, Horizontal landing
C0 2 and NO X free SpaceLiner 7-1 SpaceLiner 7-1 configuration integrating pre-sized subsystems will be defined by end 2012 + additional DLR and cooperation partners work outside of FAST 20XX (i.e windtunnel aerodynamic tests in preparation)
6 see 4 AIAA papers in HYTASP 4 – 15 – 30 & 46 on the SpaceLiner 3 industrial partners, 3 SME, 5 research institutions, 5 universities High speed airbreathing propulsion for passenger transportation
LAPCAT FP7 EU program, ending 2013 Long range transportation system (15000 – 18000 km) Large vehicles (300 passengers) System studies for Mach 5 & Mach 8 systems Design of small scale flight configuration for free-jet tests Preparation of demonstration program
Mach 5 SCIMITAR engine Low nox combustor
Mach 8 8.0
Nose-to-tail for large vehicles
Mach 8 free-jet tests in 7 Vehicle concepts HEG and F4 in 2013 see 2 AIAA papers J. Steelant, P. Viguier High speed airbreathing propulsion for passenger transportation
ATLLAS 2 FP7 EU program coordinated by ESA, 2011-2015 Development of technologies for high speed systems: System studies on vehicles to fix requirements Use of cryogenic methane for Mach 5/6 application Technology demonstration on Ultra-High Temperature Ceramics, light structures, transpiration cooling, sharp leading edges
C/C-SiC
sharp edge
ATLLAS II: 13 partners 2 industrial partners, 4 SME, 4 researchinstitutions, 3 universities
8 High speed airbreathing propulsion for passenger transportation
ZEHST (Zero Emission High Speed Technologies)
28-months feasibility and systems study for a high-speed civil aircraft (since feb. 2011) Based on an EADS study (2009) in the perspective of French-Japan Frame Agreement on Supersonic Technologies Sponsored by the French agency Direction Générale de l'Aviation Civile (DGAC)
Presented at Paris Airshow in June 2011
Main characteristics of the concept under study Range ≈≈≈11000km (e.g. Tokyo ↔ LA) in less than 3h 60 passengers Operated as a standard aircraft Environment-friendly
Main output from this study Refinement of requirements Definition of the vehicle Technology maturation plan Steps towards a flying unmanned demonstrator by 2020 Opening to international cooperation
9 see AIAA paper S. Defoort Passenger transportation
HIKARI - High speed Key technologies for future Air transport - Research and Innovation cooperation scheme
Project co-funded by the European Commission (FP7 Call 5) and by METI in Japan to promote an effective cooperation between Europe and Japan in the field of conceptual design of a high speed aircraft
Approach To contribute to some of the technological bricks that need to be explored To contribute to create synergies between the existing European and Japanese programs to build a common roadmap towards experimentations by 2020 Main studies Market analysis, Propulsion (single or multiple engines, rocket engines and tanks), Fuel (operations and impact on environment), innovative on-board thermal and energy management. Workshops will be held to define conceptual guidelines and common experimentation plan.
Partners 12 in EU: EADS Innovation Works (leader), ESTEC, MBDA, Astrium, ONERA, DLR, CIRA, Airbus, Oxford Economics, NLR, CNRS, EASN 4 in Japan: JADC, IHI, JAXA, Univ. of Tokyo Planning Signature of the Grant Agreement before the end of 2012 24-month duration 1010 Hypersonics: methodology for airbreathing propulsion
1 industrial partner, 1 SME, 4 research1 industrial institution partner,s 1 SME, 4 research institutions LEA flight test program Methodology for aeropropulsive balance of dual-mode ramjet Validation using a simplified experimental vehicle and performing flight tests in the range Mach 4 to 8
Flight tests schedueled in 2014 & 2015
LEA flight test sequence
LEA vehicle Combustion tests MBDA/ONERA MAI & CIAM
Variable geometry Geometric throat combustion chamber
Mobile flameholder
Fuel injection: kerosene, H 2 Mobile cowl 4.2 m
booster separation Booster dérived from RADUGA missile Autonomous flight 20/30 s at Mach 4 / 8
Aerodynamic tests TsAGI Aceleration with liquid fuel rocket booster Telemetry with second subsonic aircraft supersonic separation from LII TUPOLEV Tu 22 M3 Flight test and range operations Russian armed forces
ROSOBORONEXPORT head of russian contribution LEA crash Preparation of full scale free jet tests at Mach 6 in S4 blowdown windtunnel 11 LEA contributors Hypersonics: methodology for airbreathing propulsion
HEXAFLY (Kick-off in october 2012)
EU program, 18 months, ESA coordination Feasibility Study for Flight experiments based upon ATLLAS and LAPCAT technologies
Ground-based and air-launched concepts are evaluated: Mission requirements, trajectories, … Overall design layout, technical realization
6 major disciplines to be addressed: High-Speed Vehicle Concepts High-Speed Aerodynamics High-Speed Propulsion High-Temperature Materials and Structures High-Speed Flight Control High-Speed Environmental Impact
HEXAFLY: 6 partners 1 industrial partner, 1 SME, 4 research institutions 12 Technologies for hypersonic systems
DLR SHEFEX Flight Program Coordinated by DLR First flight performed in 2005 Second flight performed in june 2012 SHEFEX III flight expected in 2016
13 see AIAA DLR paper HYTASP 40 Technologies for hypersonic systems
CHATT (Cryogenic Hypersonic Advanced Tank Technologies) EU FP7-funded project addressing cryogenic propellant storage inside an airliner and related subsystems like heat-exchanger and insulation. Coordinated by DLR-SART and runs from 2012-2015 (42 months) Technology requirements are system driven and will be evaluated by LAPCAT and FAST20XX reference concepts. Within CHATT 4 different subscale cryogenic CFRP tanks will be build and tested with cryogenic fluids.
1414 see AIAA paper HYTASP 46 Technologies for hypersonic systems
Other R&T
Graduiertenkolleg Training Group « Aerothermic design of Scramjet propulsion system »
19 projects
SERN-Nozzle 2D / 3D-inlet with double ramp Isolator Combustion chamber with strut injector
DLR participation in UQ SCRAMSPACE I: engine tests performed in HEG
2.5 Unfueled combustor Fueled combustor without combustion 2.0 Fueled combustor with combustion
1.5
P c 1.0
0.5 CFD UQ 0.0 -300 -200 -100 0 100 200 300 400 500 600 700 800 Numerical Simulation 15 x[mm] Experiment in HEG Technologies for hypersonic systems
Other R&T
ONERA / JAXA /DLR : cross-check between HEG (DLR) / HIEST (JAXA) / F4 (ONERA)
Issues: run duration <-> air quality
HYSHOT IV already tested and computed by DLR & JAXA ONERA preparing the tests (after LAPCAT 2 tests on HYSHOT II)
ONERA Turbulence-Chemistry Interaction model development on Partially Stirred Reactor (PaSR)
Application to lifted supersonic flame jets Fundamental study on auto-ignition, compressibility effects, … LES / RANS frameworks
Application to combustors Ongoing collaboration with JAXA on unsteady reacting flows Collaboration with UQ (RESTM12)
16 Technologies for hypersonic systems
Other R&T
CIRA MHD experiment in SCIROCCO (with ALTA, Univ. Bologna, HPCC)
0,85 0,848 0,846 0,844 0,842 0,84
P5/P1 0,838 0,836 0,834 0,832 0,83 0 50 100 150 200 250 300 350 Time (s)
CIRA HYPROB Program on liquid propellant Lox/LCH4 and hybrid propulsion (LOx or LN 2O / WAX)
17 Hypersonics in Europe: general roadmap
2010 2011 2012 2013 2014 2015 EXPERT IXV SKYLON
Space access SPACE PLANE FAST 20XX
LAPCAT 1 & 2 ATLLAS 1 & 2
transport ZEHST Atmospheric HIKARI
LEA
forDMR HEXAFLY Methodology
SHEFEX 1, 2 & 3 CHATT HYPROB 18
Technologies Other R&T Combustion modelling, MHD… Conclusion
19