Prsentation PowerPoint

1
France National Report
Francois Falempin 16th AIAA/DGLR Spaceplanes
Hypersonic Systems Technologies
Conference Bremen, 19 - 22 October, 2009
2
High-Speed Airbreathing Propulsion
Two key points
aero-propulsive balance
Combustion chamber technology
Feasibility of positive balance On ground
development methodology (prediction, design
margins)
Fuel cooled structures Variable
geometry Endothermic Fuels
LEA Flight Test Program
On-ground Development and Demonstration Programs

3
Endothermic fuels
Reforming process studied at ONERA with MPP
Catalyst synthesis, deposition
activation Parametric study on catalytic
reforming
Autoclave ARTICHAUTS
combustion test MPP in LAERTE test facility
4
Endothermic fuels (MBDA DCPR)
Reforming Modeling for different LHC
Compatibility/effect of metalic and C/SiC
materials
Coupled Simulation Hydraulics-thermics-chemistry
5
Instrumentation for endothermic fuelsCOMPARER
(MBDA, Pôle capteur, PRISME(former LEES))

• goal
• on board extraction of fuel control parameters
• fuel system management
• small reactor with
• detailed characterisation of
• gaseous and liquid products
• (including GPC and FTIR)
• on line measurement device
• Test with composite material
• under progress

See AIAA-2009-7375
See AIAA-2009-7373
6
METHYLE test bench 2400 K 300s
Supplying nozzle SMR combustor
Endothermic fuel pre-heaters
CH4 supplying line
Vitiator
See AIAA-2009-7378
First operational test series in early 2009
7
Exemple of test performed1650 K CH4(80)/H2
(20) ER 0.5 and 1
50s
50s
SMR ignition

Small damage on coating
8
Next steps by end of 2009 Large PTAH-SOCAR
panel test in SMR (cooled by N2 then by
pre-heated endothermic fuel) Pre-he
ated endothermic fuel combustion test series
See AIAA-2009-7353
500 mm long PTAH-SOCAR panel
9
ATLLAS
ATLLAS Aero-Thermal Loaded Material
Investigations for High-Speed Vehicles
Paris University sonic boom computations
See AIAA-2009-7355
periodic approach / full approach
ONERA materials detailed effusion computations
MBDA cooled structures and computations
10
LEA Flight Test Program
Scientific purpose (no technology demonstration)
4 m long
non recoverable/non reusable
Gaseous CH4/H2 Fuel
4 flight tests Mach 4 to 8 (2013 - 2015)
Precise evaluation of aero-propulsive balance
On-ground development methodology
See AIAA-2009-7227
11
LEA Flight test sequence
Contribution to combustion test numerical
simulation CIAM MAI
LEA vehicle developed by MBDA/ONERA
4.2 m
booster separation
Booster derived from AS4 missile RADUGA
Autonomous flight 20/30 s at Mach 4 / 8 30 to
40 km
Aerodynamic tests TsAGI
Acceleration on Booster
Telemetry with airborne receiver
LII
Supersonic drop from TUPOLEV Tu 22 M3
ROSOBORONEXPORT
Contract responsible
Final crash
RADUGA Technical
prime subcontractor
12
LEA Aeropropulsive design
external aerodynamics
separation aerodynamics
Nose-to-Tail Computation
Nozzle afterbody
Instrumentation FADS
CLEA combustor to be tested very soon in ATD5
Combustion tests at MAI Injection struts
Forebody air inlet
13
LEA Forebody and Air Inlet
Works on forebody boundary layer transition
development of relevant transition prediction
numerical tool experimental validation
development of devices to control transition
location New test series performed on Mach
2 to mach 8 Mach number range
14
LEA Aerodynamic tests for FEC dropping from
TU22M3
Test series to be performed at TsAGI in December

15
LEA Combustor development
Testing at ONERA Preliminary experimental
study on CH4/H2 mixture fuels ignition delay
evaluation comparison with computation
results First test series in ATD 5 with
new full scale model performed in 2009 (Mach 4
to 7.5) (cooper alloy heat sink structure)
16
LEA Combustor development
Testing at MAI (metallic water-cooled panels
structure) First test series performed in the
Mach number range 2 to 7 with full scale (but
2/3 width) with H2, K and CH4/H2 fuels
Technology test of different injection strut
design New vitiator design, manufacturing,
integration and testing New test
series with new full scale (full width)
model starting right now
17
LEA On-ground testing logic
Combustor/nozzle
Combustor/nozzle
full scale
full scale
(METHYLE)
(METHYLE)
External
aerodynamics
External
aerodynamics
scale
1/4
-
S3 and
S4
scale
1/4
-
S3 and
S4
Forebody/air
inlet
Forebody/air
inlet
scale 1/3
scale 1/3
Direct
Connect
-
full scale (ATD5)
Direct
Connect
-
full scale (ATD5)
Synthesis propulsion test
Synthesis propulsion test
full scale
full scale
(METHYLE)
(METHYLE)
See AIAA-2009-7358
full
scale (ATD5)
full
scale
(MAI)
full
scale (ATD5)
full
scale
(MAI)
Forebody/inlet
Forebody/inlet
full scale

S4
full scale

S4
Free jet
Free jet
full
scale

S4
full
scale

S4
18
II
LAPCAT II Long-Term Advanced Propulsion
Concepts and Technologies II Feasibility studies
for a civilian transport
Mach 5 concept
One of the Mach 8 concepts
19
Contribution to LAPCAT 2
System studies for Mach 8 airplane engine
(DMR) and airframe design preliminary design
cross evaluation Nose-to-tail computation
Contribution to experimental works air
inlets scaling effects vitiation
effects Definition of a development
Roadmap (including mandatory flight
experiments)
See AIAA-2009-7378
See AIAA-2009-7328
See AIAA-2009-7254
See AIAA-2009-7390
See AIAA-2009-7290