Diapositiva 1

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16th AIAA/DLR/DGLR International Space Planes
and Hypersonic Systems and Technologies
Conference Bremen (Germany), 19-22 October 2009
Italy National Report G. Russo
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The Origins

• Space Activities at CIRA started quite at the
  beginning thanks to the Italian participation to
  the ESA Hermes Project (1988)
• Development of the SCIROCCO facility
• Coordination of the Italian Fluidynamic Studies
  under Dassault Aviations contract/s
• In the years ahead CIRA participated in almost
  all the ESA projects
• MSTP, FLTP, FESTIP, X-38, IRT, FLPP ITTs
• Presently CIRA participates in other ESA
  projects
• CSTS, RADFLIGHT, MHD-AFC, HI-LIFT, BLAST, SUAE,
  EXPERT, IXV ITTs

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Today Technology Roadmap
Robotic satellite servicing
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Today Capabilities

• Ground test facilities
• Scirocco (70MW Plasma Wind Tunnel)
• Ghibli (2MW Plasma Wind Tunnel)
• LISA (planetary landing and splashdown testing)
• Flying laboratory
• USV FTB_1
• Research expertise
• Aerothermodynamics Propulsion
• Materials Structures, incl. TPS HS
• Guidance Navigation Control
• Advanced Diagnostics
• Integrated capabilities for
• Advanced re-entry systems
• Hypersonic vehicles
• Space systems

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Plasma Wind Tunnel - SCIROCCO

• Goal To improve the flight safety of space
  vehicles during reentry from low Earth orbit
  or from super-orbits (return from Moon or Mars)
  
• Use Study and qualification of thermal
  protection systems and hot structures
• Operational since 2002
• Testing Fluid air
• Max Speed Mach 16
• Stagnation Temperature ? 10000 C
• Test Duration up to 25 minutes
• Nozzle max exit diameter 2.0 m
• Model Nominal Size 0.6 m
• Segmeted Arc Max Power 70 MW
• Unique in the world as dimension and power
• Partners Customers

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SCIROCCO Developments

• MRS Thermal Protection System
• Earth Reentry from Superorbit
• ExoMars Thermal Protection System
• CO2 Operating Fluid
• ExoMars Entry Descent Landing
• System
• Supersonic Parachute

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Plasma Wind Tunnel GHIBLI

• Goal Research activities and development of
  new materials and concepts for thermal
  shields for reentry space systems
• Uso Experimental tests on small samples or
  models subject to hypersonic flows
• Testing Fluid air, CO2 (future)
• Max Speed Mach 12
• Stagnation Temperature ? 10000 C
• Test duration up to 25 minuti
• Nozzle exit diameter 150 mm
• Model nominal size 80 mm
• Arc max power 2 MW
• Commissioning Tests in progress
• Starting of Operations middle 2009
• Partners Clients

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Large Dynamic Impact Facility

• Goal Improve spacecraft survivability during
  earth and planetary landing
• Use Design and validate crashworthy airbag
  space structures and crash protection devices
• Operational since 2003
• Impact trajectory from 5 to 90 deg
• Max speed 20 m/s
• Max Model weight 20 t
• World unique for testing envelope
• Application ExoMars

• ExoMars Entry Descent Landing
• System
• Vented Airbag Testing

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in the long run space access and re-entry will
be guaranteed by aviation-like vehicles

• Goal USV is a Technological Programme for
  hypersonic flight and atmospheric reentry
• USV is composed by
• USV_TECH dedicated to enabling technologies
  development
• GNC
• Aerodynamics/Aerothermodynamics
• Sharp UHTC-based Hot Structures
• CFRP Cryogenic Tank
• Air-breathing Propulsion
• IIHMS
• Adaptive Hypersonic Wing
• USV_1/2/4 to develop and use Flying Test Beds
  (FTB) launched by means of Stratospheric Balloons
  and dedicated to trans-, super- and hypersonic
  flights
• USV_3/X to develop and use a VEGA-launched
  high-lift FTB for sub-orbital and orbital flights

FTB-1/2
FTB-X
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Relation with other Programs

• USV is a national program that includes
  interactions and even integration with
  international activities as well as programs
• Collaborations were established in past years
  with
• NASDA (now JAXA, Japan) in the frame of CFRP
  cryogenic tanks development
• CIAM (Russia) for air-breathing propulsion
  studies
• ISRO (India) on USV_X aerodynamics and system
  analysis
• CIRA participation in the ESA EXPERT program is a
  fundamental part of the USV Roadmap for the
  development of re-entry capabilities, with
  specific regard to in-flight experimentation
• Synergies between USV_X and the ESA IXV program
  allowed the revision of the USV Roadmap
• A Framework Agreement in hypersonics has been
  recently signed with UQ (Australia) fostering
  synergies between USV and HIFiRE

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USV_1

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USV_4

• 2 m long hypersonic glider
• 15 s Mach 8 flight
• 3 year development to flight
• feasibility under study with UQ

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USV_3 / USV_X
CFD Analysis M20, AoA10

• REFERENCE CONCEPT
• 5 m long winged reentry glider
• high lift reentry trajectory
• 1-1.5 h reentry trajectory
• Flying while reentering

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From USV to IXV
EXPERT Launch 2010 Aerothermodynamics In Flight
Measurement P/Ls Scientific Coordinator PI of 3
P/Ls Post-flight Analysis
CIRA USV
FLPP-IXV Launch 2012 In Flight
Experimentation Aerothermodynamics TPS
Qualification in PWT Balloon System Qualif. Drop
Test Support to ASI for TAA Post-flight Analysis
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IXV TPS HS Qualification
IXV Phases (C2/D) to plan, prepare, design and
execute the IXV TPS/HS tests, at Assembly and
System level, in order to support the
Qualification Review.

• The TPSHS Subsystem consists of the following
  assemblies
• Nose Assembly
• Windward TPS Assembly it includes the C-SiC
  Shingles Assembly and the Leading Edge Assembly
• Body Flap Assembly that includes the Hinge TPS
• Leeward Base Ablative TPS Assembly

CIRA Activities (TAS-I as prime) test
feasibility, test set-up, contributions to test
article design and instrumentation, test
execution, interpretation of results, reporting.
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SHARP HOT STRUCTURES
Wing Leading Edge

• R nose 10 mm
• Stagnation heat flux gt 650 kW/m2
• Heating peak duration gt 15 s
• Maximum Operational Temperature 2100C
• Density lt 6 (g/cm3)
• Porosity lt 5
• Cataliticity low
• Emissivity high (gt0.8)

Nose Cap
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SHARP HOT STRUCTURES
Reference Vehicle FTB_2/X

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EXPERT ExperimentUHTC Winglet

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EXPERT ExperimentUHTC Winglet
EXPERT WINGLET P/L Structural aerodynamic
profile made of massive UHTC
UHTC WINGLET during an integration fit check
Ready for Qualification Test in SCIROCCO
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RoadmapIn-Flight Experimentation
7.5 km/s
5 km/s
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RoadmapIn-Flight Experimentation
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CLAE Conf. Local Aerothermod. Effects
Identification of the most interesting
regions 304 pressure sensors mounted on FTB_1
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CLAE Conf. Local Aerothermod. Effects
blunted forebody/full-scale flap model (2)
3D thermo-chemical non equilibrium flow
simulations have been carried out in order to
verify, at least from a numerical point of view,
the achievement of the requirements on the
model the (maximum possible) model width is not
sufficient to avoid finite span effects on the
SWBLI around the flap and over the entire model
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GUIDANCE NAVIGATION CONTROL

• Goal Develop and validate innovative
  autonomous GNC systems
• Use Flight dynamics modelling and simulation,
  GNC avionic systems development,
• Real Time Systems and Rapid Prototyping
• Tools Synthetic environment for autonomous GNC
  design, Iron Bird for real-time testing, Small
  Scale Flying Demonstrator
• Methods Object oriented modelling,
• Robust/adaptive control,
• FDIR/FTC, Autonomous Decision Making
• Partners and clients

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DTFT_2 GNC
On-Line Adaptive 4D Guidance
Objectives

• On-line adaptive guidance to reach final position
  and velocity conditions at a predetermined time
  instant

Description

• DTFT2 guidance algorithm continuously adapt the
  trajectory and the tracking algorithm during the
  flight to minimize distance from the final
  pre-determined (one day before launch) target in
  terms of horizontal position, altitude and Mach
  number for a mission duration of 140s.

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STRUCTURES AND MATERIALS

• Goal Develop new materials and high efficiency
  structural concepts
• Use Automated deposition technologies, Resin
  infiltration technologies,
• Oxidation resistant composite ceramic matrix,
• Improvement of the functional properties of
  nano-composites,
• Material selection for increasing comfort in
  composite fuselage
• Tools Custom simulation tools for resin
  infusion, filament winding, cure process and
  robotic winding.
• mechanical testing equipments,
• non destructive test equipments,
• optical and electron microscopy
• Partners and clients

ANISOGRID STRUCTURE BY FILAMENT WINDING
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CAST MHD test in HEAT
Sharp Model at Mach 15
Flow around the test body with MHD interaction
(ptot 500 mbar).
Flow around the test body without MHD interaction
(ptot 500 mbar).
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CAST MHD test in Scirocco

• P02 bar
• H022 MJ/kg
• Test duration 10 min
• Electromagnet switch on 10 s

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CAST TC1a Double Cone in HEAT
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UHTC Reentry Capsule on MAXUS-8
A double cone free flight Reentry experiment will
be flown on MAXUS-8 sounding rocket campaign on
March 2010. The UHTC Reentry Capsule will be
accomodated in the interstage volume of the
rocket and will be deployed during the staging
phase, at the end of the motor thrust phase
. Independent reentry flight will be executed
with data acquisition and storage on board, and
payload recovery after landing.
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LAPCAT Long-Term Advanced Propulsion Concepts
and Technologies

• Development of the thermo fluid dynamic model and
  related flow solver for two classes of propulsion
  systems
• Rocket engines LOx-HC (Liquid Oxygen
  Hydrocarbons).
• Airbreathing engines for hypersonic vehicles
  (Scramjet).

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Rocket engines LOx-HC (Liquid Oxygen
Hydrocarbons)
Development of a 3D numerical solver for the
simulation of transient chemically reactive flows
in typical LOx-HC rocket and rocket-based-combine
d-cycle engines operating conditions
Validation and testing
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Airbreathing engines for hypersonic vehicles
(Scramjet)
AIAA Paper 2009-7207

• Compressible reactive 3D solver

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Main characteristics
Class of engine 10-20 Ton
thrust Propellant
Methane (CH4) Test
Duration up to 600 s
Altitude conditions 60 mbar
HyProb Test Facility
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CFD

• CFD codes for complex geometries
• Robust and general codes for applications on
  complex geometries (complete configurations)
• Numerical schemes
• Parallelization
• CFD/Models
• Advanced state-to-state models for kinetics
• Catalysis
• Ablation
• Radiation
• Combustion
• Real gas effects on turbulence
• LES and DNS
• Simulation of rarefied flows

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BEAT Facility - Avio
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Italian (and CIRA) Role within the European
Context
RE-ENTRY TECHNOLOGY
Independent from RLV future
USV_1
IXV
?
EXPERT
lead
lead
lead