ra diation- s hapes- t hermal protection investig a tion s for high sp eed ea rth r e-entry j-m...

RaRadiation-diation-SShapes-hapes-TThermal Protection hermal Protection

InvestigInvestigaationtionss

for High for High SpSpeedeed EaEarthrth RRe-entrye-entry

May 3rd 2011 1

J-M BOUILLY, A. PISSELOUP - EADS Astrium - Saint-Médard-en-Jalles, FranceO. CHAZOT - Von Karman Institute, Rhode-St-Genese, BelgiumG. VEKINIS - Institute of Materials Science, NCSR "Demokritos", GreeceA. BOURGOING - EADS Astrium Space Transportation, Les Mureaux, FranceB. CHANETZ - ONERA, Meudon, FranceO. SLADEK - Kybertec, s.r.o., Chrudim, Czec Rep.

RASTAS SPEAR :Radiation-Shapes-Thermal Protection Investigations for High Speed Earth Re-entry

The research leading to these results has received funding from the European Union The research leading to these results has received funding from the European Union Seventh Framework Programme (FP7/2007-2013) under grant agreement n° 241992Seventh Framework Programme (FP7/2007-2013) under grant agreement n° 241992

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3rd International ARA Days - Arcachon, France2011, May 2-4 - Session TPS-3

May 3rd 2011 - 3rd International ARA Days - Arcachon 2-4 May 2011 - Se3rd International ARA Days - Arcachon 2-4 May 2011 - Session TPS-3ssion TPS-3

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RaRadiation-diation-SShapes-hapes-TThermal Protection hermal Protection InvestigInvestigaationtionss for High for High SpSpeedeed EaEarthrth RRe-entrye-entry

Overview

• Introduction• Objectives• Overview of technical activities

• Review of System Requirements• Ground Facilities Improvement• Key Technologies for High Speed Entry• Ablation – flight mechanics coupling assessment • Gas-surface interactions modeling

• Next Steps / Conclusion


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• In the frame of EC FP7 second call• Activity 9.2 – strengthening of

space foundations / research to support space science exploration

• SPA.2009.2.1.01 Space Exploration

• Duration• Sep 2010 - Sep 2012

• Status : • Team composed of 10 partners• Astrium is the coordinator

• Budget • total : 2.3 M€• including 1.6 M€ EU grant

• More on www.rastas-spear.eu

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Partner Country

ASTRIUM-ST SAS France

CIRA : Centro Italiano Ricerche Aerospaziali

Italy

CFS Engineering Switzerland

NCSR Demokritos Greece

CNRS France

IoA : Institute of Aviation Poland

KYBERTEC Czec Rep.

MSU : Lomonosov Moscow State University

Russia

Office National d’Etudes et de Recherches Aérospatiales

France

VKI : Von Karman Institute for Fluid Dynamics

Belgium

Introduction


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10 partners from 8 European countries

AST-F

ONERA

CNRS

VKI

CFS

CIRA

IoA

MSU

DEMOKRITOS

KYBERTEC

LANDING GEAR DEPARTMENTLANDING GEAR DEPARTMENT


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General Objective

• Sample Return Missions : an important step for Solar System Exploration

• After collecting samples, any return mission will end by high-speed re-entry in Earth’s atmosphere.

• This requires strong technological bases and a good understanding of the environment encountered during the Earth re-entry.

• Investment in high speed re-entry technology development is thus appropriate today

• to enable future planetary exploration missions in the coming decades.

• Mars Sample Return, Marco Polo...

Rastas Spear project• to increase Europe’s knowledge in high

speed re-entry vehicle technology

Sample Return Capsule

Other potential applications : ARV, Venus


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Objectives of the project

• OBJ1 (WP1, WP2, WP4 + WP5)To better understand phenomena during high speed re-entry enabling more precise Capsule sizing and reduced margins.

• OBJ2 (WP2) :To identify the ground facility needs for simulation

• OBJ3 (WP3) : To master heat shield manufacturing techniques and demonstrate heat shield capabilities.

• OBJ4 (WP3+WP4) : To master damping at ground impact and flight mechanics and thus ensure a safe return of the samples

WORKPACKAGES WP Participants

WP1 Review of System Requirements

AST CNRS

WP2 Ground Facilities Improvement

AST CIRACNRSVKI

WP3 Key Technologies for High Speed Entry Mastering

AST-FCIRADEMOKRITOSIOA

WP4 Ablation-Flight mechanics coupling assessment

ASTCIRACNRS

WP5 Gas-Surface interactions modelling

ASTCFSMSUONERA

WP6 Synthesis, Management & Coordination

AST + KYBERTEC+ WP leaders


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WBSWP1

Review of SystemRequirements

1.1 Atmosphere modelling

1.2 Trajectories

1.3 Aerodynamics & ATD

1.4 Vehicle Design

WP3Key Technologies for

High Speed Entry

3.1: Choice of TPS + Joints

3.2: Flow tests

3.3: Breadboard manufacturing

3.4: Crushable Structure

WP4Ablation- Flight Mechanics

Coupling assessment

4.1 Tools coupling

4.2 Ablation coupling assessment

4.3 Engineering modellingCorrection by CFD

WP5Gas-Surface Interactions

Modelling

5.1: Review of surface roughness and blowing influence

5.2: Ground Experiment Preparation

5.3: CFD Modelling

5.4: Synthesis of WP

WP2Ground Facilities

Improvement2.1: Analysis of Current Ground Facilities

2.2: Shock tube technology

2.3: Ballistic Range Technology

2.4: Plasma Generator Technology

WP

6M

an

ag

em

en

t, D

isse

min

atio

n a

nd

Exp

loita

tion

6.1

Man

agem

ent

6.2

Dis

sem

inat

ion

& E

xplo

itatio

n

2.5: Synthesis


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WP 1 results: Review of System RequirementsMain objective provide with general inputs for any others WP

WP 1.1: Atmosphere modelling- Atmosphere compositions for Earth and Venus, - Thermochemical model (kinetic model + thermal model) available, with identification of all possible species and chemical reactions.

EARTH VENUS

complete model based on N2, O2 and Ar

model based on CO2 and N2 mixture

simplified model based only on N2 and O2


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May 3rd 2011

WP 1 results: Review of System RequirementsWP 1.2: Trajectories- Identification of generic aeroshapes with respect to candidate exploration missions. We focus our investigation on Earth entry,-Trajectories have been computed including usual design criteria-Flight domain determined with constraints on :

- max heat flux, max heat load, max g-load

Time [s]

He

at

Flu

x[k

W/m

2]

Ma

ch

Ve

loci

ty[m

/s]

Alti

tud

e[k

m]

0 10 20 30 40 50 600

2000

4000

6000

8000

10000

12000

14000

16000

10

20

30

40

50

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10000

11000

12000

13000

0

20

40

60

80

100

120

ConvectiveRadiativetotalMachVelocityZ

12300m/s

32.31

45.7

V=12300m/sZ=90.08km

11600kW/m2

V=10891m/sZ=57.48kmM=33.648832kW/m2

2932kW/m2Sphere cone 45°Diameter D =1100 mm

Nose radius Rn = 275 mm


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Contributions to the radiative flux of the equilibrium and nonequilibrium zones

Contributions to the radiative flux of the equilibrium and nonequilibrium zones

-2,5 -2,0 -1,5 -1,0 -0,5 0,00

10000

20000

30000

40000

50000

-8.5°, Altitude Z = 63.2 km

Ke

lvin

Shock layer distance

T Tvib Tel

-2,5 -2,0 -1,5 -1,0 -0,5 0,010-4

10-3

10-2

10-1

100 -8.5°, Altitude Z = 63.2 km

Mo

le f

ract

ion

Distance (cm)

0 N Ar O+ N+ Ar+ e-

equilibrium

Non-equil.

• Nonequilibrium zone produces less than 19% of the radiative flux

• Less than 8% between -2.2 and -1.7 cm.

WP 1 results: Review of System RequirementsWP 1.3: Aerodynamics & Aerothermodynamics- Aerodynamics: Newton Preliminary analysis

- Aerothermodynamics (Aerothermal environment) Engineering methods for convective heating,

Shock-layer radiation computations for radiative heating (CNRS activities)

t (s)

Siz

ing

He

at

Flu

x(w

att

/2)

0 10 20 30 40 50 600

2E+06

4E+06

6E+06

8E+06

1E+07

1.2E+07

1.4E+07

1.6E+07

1.8E+07

ConvectiveRadiativeTotal

Ve= 12300 m/s - e = -12.5 °

Stagnation Point


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WP 1 results: Review of System RequirementsWP 1.4: Vehicle design

IF Carrier

Filling Foam

FS Structure

FS TPS

Lid TPS

Front Energy absorbing material

Rear Energy absorbing material

Lid structure

Internal insulation

Internal structure

Sample Canister

AFT TPS

- Preliminary design of the generic capsule, and determination of TPS thickness, in order to define the Mass Centering and Inertia (MCI) assuming a given architecture- Preliminary requirements related to TPS for other WP : surface recession, mass loss, temperature evolution, gas flow rate,…


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WP2: Ground Facilities Improvement

Objectives:

• Review High Enthalpy facilities and dedicated instrumentation• Identification of ground testing facilities to reproduce flight environment• Identification of testing facilities for TPS qualification• First design of hypervelocity facility for Super-orbital reentry simulation

Typical example: X2 facility in dual-driver expansion tunnel mode (UQ, Australia)


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Two kind of ground based facilities are involved to reproduce the typical flight environment:- Shock tube / Shock tunnels duplicate the shock layer and generate database for the radiation features- Plasma wind tunnels duplicate the boundary layer around the vehicle and allow TPS qualification WP2 will review those facilities, provide recommendations for required performances of test facilities and associated methodologies, and preliminary define the hyper-velocity facility dedicated to high speed entry

WP2: Ground testing strategy

Bow shock Reacting BL

Aerospace vehicle noseM>>1

Wall ChemistryGas Surface InteractionAblation

ThermalChemical

NEQ

Upstream flow

Plasma wind TunnelShock Tube facility

Shock wave

Shock layer

Real flight situation

Radiation studies TPS qualification

TPSBoundary layer


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WP3: Key Technologies for High Speed Entry

WP3.1. Iterative search for new joint and bonding adhesives

• Search for advanced adhesives for better performance

• Elementary characterisation

• Compare with heritage adhesives and optimise

• Develop new, efficient and lower cost manufacturing processes

WP3.2. Arc Jet validation at CIRA/SCIROCCO

• Heat flux up to 15MW/m² (tbc)

• Testing of range of joints and geometries

WP3.3. Manufacture a demo TPS shield to demonstrate the technologies developed in RASTAS SPEAR


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WP3: Key Technologies for High Speed Entry

WP3.4. Crushable Structures• Material selection for light damping

structures• Material characterisation tests

• Static

• Low speed dynamic

• Crush

• Modelling of energy absorption structures• Manufacturing of corresponding item for

techno demonstrator, and numerical validation


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RaRadiation-diation-SShapes-hapes-TThermal Protection hermal Protection InvestigInvestigaationtionss for High for High SpSpeedeed EaEarthrth RRe-entrye-entry WP4: Ablation – flight mechanics coupling

assessmentObjectives Based on WP1 results as inputs : flight environment, vehicle configuration

• 1- To assess impact of massive ablation on aerodynamic performances and stability along the entry trajectory path.

• 2- To identify recession level that could be tolerated with respect to capsule aerodynamic performances and stability requirements.

• 3- To elaborate and validate an engineering tool that couples: - Aeroshape aerodynamic, - Trajectory and stability, - Aerothermal environments, - TPS material thermal response - and then recession determination resulting in aeroshape modification.

• 4- To translate these results into criteria for maximum recession requirements in relation with usual landing accuracy, g-loads, heating and incidence profile issues.


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WP4: Ablation – flight mechanics coupling assessment

Work logic:

Synthesis

WP4.1 – Tools Coupling (AST)Coupling of following tools:

- Ablation & thermal TPS response code including Aeroshape modification

- Shock shape & - Pressure distribution & - Aerodynamic coefficients determination by CFD code, including ablation gas products injection

- 6 DoF Trajectory Tool

WP4.2 – Tools Coupling Assessment (AST)

WP4.3 – Engineering modellingCorrection by CFD (AST – CIRA - CNRS)

- Assessment of Ablations-flight mechanics effects for candidate Earth Entry capsule

- Assessment of Aeroshape modification (CIRA)

- Assessment of Radiation (CIRA-CNRS)

- Assessment of Surface mass blowing (CIRA)

- Identification of requirements for maximum TPSrecession

- Sensitivity to TPS ablative properties

- Development of engineering tool to determine radiating heating vs. recession rate (AST)

- Engineering correlation derivation from CFD computations (AST)


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Flow aerodynamics

Trajectory

Thermal response Ablation

- Ablation & thermal TPS response code including Aeroshape modification

- Shock shape & - Pressure distribution &

- Aerodynamic coefficients determination by CFD code, incl. ablation products injection

- 6 DoF Trajectory Tool

WP 4.3 – Engineering modellingCorrection by CFD (AST – CIRA - CNRS)

Coupling of tools Detailed inputs(radiation, blowing, shape change)

Assessment of coupling effectsRequirements for max TPS recession


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WP5: Gas-surface interactions modeling • WP 5.1 Review of surface roughness

• Critical analysis from real flight (Astrium/MSU)• Bibliography about roughness and blowing (Onera/MSU)• Turbulence model recommendations (MSU/Onera)

• WP 5.2 Ground experiment• Tests in Mach 5 blow down wind tunnel (Onera)• Test analyses (Euler + boundary layer)

• WP 5.3 Model implementation• Engineering model assessment (MSU/CFS)

Next slides


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May 3rd 2011

WP5: Gas-surface interactions modeling

Experiments in the blow down wind tunnel R2Ch

• Test Objective : qualification of the wall heat-flux with different roughness and blowing rate

• Wind tunnel characteristics :

• Mach 5 nozzle with an• exit diameter : 326 mm• pst : from 5 105 Pa to 50 105 Pa ; Tst = 650 K• Re (L=1 m) = 4.25 106 from 42.5 106

• Model : Flat plate with a sharp leading edge, already available from a prior test campaign

During tests :

- Heat flux measurements by infrared thermography, - Schlieren photographs


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• Three porous ceramic insert (porosity 48 %)

- without roughness

- with roughness r1 (pyramid height 100 microns)

- with roughness r2 (pyramid height 300 microns)

• Characteristics of the roughness : pyramids joined and in staggered rows

k

b

2b

l = 46,3mm

l= 46,3 mmL = 225,8mm


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• Consequence for the tests : blowing with three mass-flow rates up to 3.8 kg/m²/s :

- m1 : without blowing (reference case m1 = 0)- m2 : moderate blowing (m2 = 0.5 m3 = 1.9 kg/m²/s)- m3 : maximal blowing (m3 = 3.8 kg/m²/s)

Stagnation blowing rate

0,000

0,001

0,010

0,100

1,000

10 20 30 40 50 60temps [s]

m/(r V

)in

f

turbulent

Z(km) m/(rV)

52 0.012

46 0.005

36.2 0.0012

mass-flow rate calculated on the maximum heat-flux trajectory(from Astrium MSRO study-2000)


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Next Steps

WP 2 • Review and description of dedicated shock tube and plasma facilities• First design of hyper-velocity facility to simulate high speed Earth re-entry.

WP 3 •Bibliographic review on joints materials•Screening and testing of crushable materials•Preparation of arc jet tests in Scirocco

WP 4 •Flow computations with and without ablation products•Preparation of tools for coupling

WP 5 •Completion of bibliographic review•Preparation and performance of ground experiments


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Conclusion

• Rastas Spear is a typical R&D project• Part of European Community Framework Programme n°7 (FP7)

• Objective to increase the TRL of • Key technologies• Methodologies

• Project is now on-track• Frame of the study has been defined

• Focus on passive Earth Return Capsule

• Remaining steps until end of study will allow completion of overall project objectives• Completion Fall 2012


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Thank you for your attention

More at www.rastas-spear.eu

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ra diation- s hapes- t hermal protection investig a tion s for high sp eed ea rth r e-entry j-m...

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