HIKARI Confidential

High Speed Key Technologies for future Air

Transport

Research and Innovation Cooperation Scheme

HIKARI: Paving the Way towardsHigh Speed Air Transport

Emmanuel Blanvillain, Guy Gallic, Airbus Group Innovations

Aerodays 2015

London, UK

22.10.2015

HIKARI, FP7 Call5

3

JEDI-ACE

SHEFAE

HIKARI

22.10.2015, London

HIKARI Confidential

High Speed Key Technologies for future Air

Transport

Research and Innovation Cooperation Scheme

The research leading to these results has received funding from the European

Union Seventh Framework Programme (FP7/2007-2013), METI and MEXT.

Duration: February 2013 - January 2015

4

LAPCAT MR2

JAXA HST

ZEHST

LAPCAT A2

Spaceliner

LAPCAT M8

22.10.2015, London

Build on momentum from high speedtransport projects in Europe and JapanBring together the previous concepts,exchange, benchmark and understand

Make visions converge into Joint designguidelines and roadmaps for technologydevelopment and demonstrators

Perform technology studies in key areas:environment, propulsion, thermal analysis

Project Objectives

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The Design Process

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Range: to capture 90% of the market, the required range is thefollowing– 11500 km [6200nm] with no ERF (Extended Range Factor)– 13500 km [7300nm] when including the ERF

ERF: Extended Range Factor (detour)– Not a big issue for time savings– Issue for fuel burn and vehicle sizing

Recommendation– Investigate low sonic boom option to suppress the ERF

Range and Sonic Boom Strategy

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Figure 3: Passenger distribution w/o ERF

Figure 4: Passenger distribution w/ ERF

Market capture Fuel efficiency

+

Commercial Requirements

(Market and Operations)

Speed– Mach 5 provides huge time savings against subsonic flight

No large time benefit beyond this– Mach 5 provides significant cruise phases (>40%) even for

medium range and low acceleration

Technology Impact– Propulsion options at Mach 5 are larger: ramjet / PCTJ– Materials might be simpler / cheaper– More test facilities available

Speed

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+

Mission Delta from

Subsonic to

Mach 5

Delta from

Mach 5 to

Mach 8

11 000 km 10.3 hours 0.5 hour (5%)

14 000 km 13.2 hours 0.7 hour (5%)

Time savingsDemanding Technologies

Table 1: Time Savings in hours (w/ 0.1g acceleration and deceleration, no ERF)

Water vapor produced by H2 combustion has a long residence time in the very dry layers of the stratosphere. This generates a high radiative forcing, and thus a high green house effect

This effect might decrease as altitude increases above 25km.Some routes (polar routes, single hemisphere routes) might be more favorable.If more impacting than a subsonic flight, a penalty should compensate for the extra emission impact

Contrails do not seem to represent a threat (to be verified for extreme values of zonal and seasonal atmospheric discrepancies)"

Current production process for H2 (from NG) are not sufficiently energy efficient and therefore induce high fuel prices

Climate Impact and Fuel: Key findings

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H2

Cooling

Climate ImpactPerformance

Cost

Recommendation

Investigate designs using other fuels (liquid hydrocarbon specifically, and possible LNG) with holistic evaluation method (performance, thermal, costs, climate impact, ground operations)

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Passenger Capacity: Step wise approach

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2030-2035

Business Jet size 10 passengers

to initiate the business, as “niche” market first

2040-2045

Small airliner size 100 passengers

to grow the market , with more ambitious technologies (leading to longer range and cheaper tickets)

2055+

Large airliner size 300 passengers

to capture market growth and progressively develop towards a “mass market”

Key Parameters results

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Design Parameter High is good for … Low is good for … Recommended Value

Range Market capture thus number of aircraft sold

Performance , thus lower operating costs and ticket price

13 500 km (including the ERF)11 500km (excluding the ERF)

Acceleration Cruise performance

Comfort / Engine weight and size

Nx= [0.15-0.2] g

Cruise Speed Time savings, thus passenger appeal and market share

Technology levels requiredMach 5

(or slightly below for extended range operations)

Cruise Altitude Emissions : non monotonic behavior Optimized for maximal performance and minimal climate impact

Fuel Type: H2 Range, Cooling Cost, Climate impact Hydrogen, but consider alternatives

Pax Capacity Performance , thus lower operating costs and ticket price

Flexibility to cover the market thus number of aircraft sold.Program complexity and costs

Step-wise growth

Medium (100 pax) for 2045Large (>200 pax) beyond 2055

2015 2025 2035 2045

Main HIKARI Roadmap including TD Roadmap

Environment

Propulsion

Thermal Control

Materials

Control

Aerodynamics

Structure

Safety / Operations / Social

Facilities / Tools / Capabilities

FS Prototype Production & Verification

Reduced Size A/C Demo

FS Vehicle Definition / Project Development

Phase 2 Phase 3

Mission & Conceptual Vehicle Studies

Synergies with Other Areas(Spin-Offs)

TRL 6

Phasing of Technology Development Roadmap

System Studies Feeding

Tech. Dev.

FS Vehicle Requirements

Airborne Subsystem Demonstration Roadmap

Ground Based Subsystem Demo. Roadmap

Phase 1

Milestone

Star

tin

g D

ates

of

Tech

no

logy

St

ream

s V

ary

TRL 1

Tech. Dev. Feeding FS Definition

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MS1

MS2

MS3 MS4

• 22.10.2015, London

Propulsion : PCTJ

Wind tunnel tests at Mach 4 to validatedesign aspects

Noise estimated inferior to those of Concorde

Thermal and Energy Management

Identification of cooling capacity and thermal load, identification of needs in energy and energy producers

Introduction technologies solution to generate and store electricity

Technology studies (extracts)

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JAXA

22.10.2015, London

Synergies and short-medium term benefits to other industries

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Synergetic topic Short/Mid-Term application

Mass H2 production and use, incl. tanks Ground transportation, subsonic aviation (propulsion / fuel cell), space launchers …

Thermal and energy optimization method(+ components: lightweight heat exchangers)

More electric subsonic aviation, ground transportation…

High temperature lightweight materials Subsonic aircraft engines,space re-entry vehicles, space propulsion,

Low Speed Noise modelling and mitigation measures

Subsonic aircraft

Atmospheric and climate modelling Subsonic flights : polar trajectories, business jets…

Design methods and tools for highlycomplex and integrated vehicles

Aerospace vehicle design

Design Rules evolution to allow high performance vehicles (single pilot…)

Subsonic aircraft, sub-orbital vehicles

The market is sufficiently large to allow sustainable airline operations (>200 a/c), provided that HS flights are fed by connecting network and under the conditions of affordable ticket prices ( <= twice BC price)

High performance is critical to achieve affordable tickets: very efficient design, optimized propulsion

Range : 13 500km, investigate opportunities for supersonic overland

H2 but … LHC/CH4

Mach 5 is the best compromise speed

Passenger Capacity : step-wise growth small for 2030+ larger 2050+ to accompany market growth and master risks

Conclusion

16 22.10.2015, London

Build on momentum from high speedtransport projects in Europe and JapanBring together the previous concepts,exchange, benchmark and understand

Make visions converge into Joint designguidelines and roadmaps for technologydevelopment and demonstrators

Perform technology studies in key areas:environment, propulsion, thermal analysis

Project Objectives

17 22.10.2015, London

Develop critical technologies identified in the HIKARI roadmap– Thermal and energy system management – Low noise and low sonic boom– Propulsion: PCTJ, turbo ramjet : investigate and down select

Progress towards a joint design following the HIKARI Guidelines, collaborative team + chief engineer

Progress on regulation aspects Proceed with Joint demonstrators following the HIKARI roadmap

Recommendations on the Way Forward

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Topics

Frame

H2020 Transport call 2016-2017 (draft)

– call MG1.2 : Low Sonic Boom research

– call MG1.5: Breakthrough : HIKARI 2 (joint design work)

H2020 calls beyond aviation

– Energy, materials, space: technology work

RISE (Research and Innovation Staff Exchanges)

Any question

http://www.hikari-project.eu

http://www.euronews.com/2015/03/02/hypersonic-airlines/

Thank You !

19 22.10.2015, London

This document and all information contained herein is the sole property of the HIKARIConsortium or the company referred to in the slides. It may contain information subject toIntellectual Property Rights. No Intellectual Property Rights are granted by the delivery of thisdocument or the disclosure of its content. Reproduction or circulation of this document toany third party is prohibited without the written consent of the author(s). The disseminationand confidentiality rules as defined in the Consortium agreement apply to this document.

The statements made herein do not necessarily have the consent or agreement of the HIKARIconsortium and represent the opinion and findings of the author(s).

All rights reserved.

Thank you!

The research leading to these results is being funded by the European Commission Seventh Framework

Programme (FP7/2007-2013) under Grant Agreement no 313987, the METI (Ministry of Economy, Trade

and Industry) and other concerned Japanese authorities under the 7th Framework for Research and

Technical Development.

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Constraints and Technical Requirements Flow Chart

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Passenger Capacity– Larger aircraft allow for more efficient structures (smaller fraction of dead weights, higher

volumetric efficiency), hence better fuel consumption per passenger, and more affordable ticket price.

– Smaller aircraft allow to serve more routes, and reduce program complexity and spread the smaller development cost over more units produced.

Objective– Reach a sustainable fleet size for operations : minimum 200 aircraft

Recommendation : step-wise approach (for market, risks and investments reasons)– Start with smaller vehicle, to initiate the business, as “niche” market first.

A smaller vehicle will imply a lower “entry ticket” (investment costs) and more limited risks– Later grow towards larger vehicle, once the market is more mature and the technologies have

been proven

Passenger Capacity (1/2)

23

+

Fuel consumption / passenger

Nb of aircraft produced

Pgm complexity & costs

Flexibility (network, airports)

If relying on existing turbofan engines for low speed phases, noise is expected to be comparable to today’s levels

If considering more advanced / multi-phase propulsion, the higher exhaust jet velocities induce high noise levels at all design points (Fly-over, Approach , Lateral)

Recommendation: investigate dedicated noise treatments and procedures

Low Speed Noise: Key findings

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+

Performance LS Noise

Multiphase propulsion

A320-211

737-300

A340-211777-200

787-8

747-100

747-300

A380-841

Concorde

TU-144

LAPCAT MR2.4

JAXA-HST

LAPCAT MR2.4, optimized engines

80

85

90

95

100

105

110

115

120

125

130

No

ise

ce

rtif

ica

tio

n l

eve

ls,

EP

Nd

B Lateral

Flyover

Approach

Small Large

Subsonic Supersonic Hypersonic