Atmospheric Entry Plasmas - ULisboa · (photodissociation, photoionization, photodetachment) and...
Transcript of Atmospheric Entry Plasmas - ULisboa · (photodissociation, photoionization, photodetachment) and...
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Atmospheric Entry PlasmasFısica dos Plasmas
Mario Lino da Silva, Bruno Lopez, Vasco Guerra and JorgeLoureiro
Instituto de Plasmas e Fusao NuclearInstituto Superior Tecnico, Lisboa, Portugal
March 10, 2014
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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What are Atmospheric (Re)-Entry Plasmas
Typical Earth reentry profile Spacecraft entry in Mars Atmosphere (Artist Illustration)
Formation of a strong shockwave upstream of a spacecraft crossingthe upper atmospheric layers at hypersonic speeds.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Shockwaves as Plasma Precursors
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Comparison Between Entry and Laboratory DischargePlasmas
Reentry Plasma
1/2mv2 ' 7/2kBTtr
v = [7− 10km/s]⇒Ttr = [25, 000K− 60, 000K]
Ttr � Tvib
Gas Discharge Plasma
Tel = 1− 3eV
V–e processes dominant
Ttr � Tvib
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Plasma Radiation as a Spacecraft Design Driver
Radiative heating can be a major design driver forlarge or high-speed (≥ 10km/s) entry vehicles
For lower entry speeds, radiative heating maymandate additional thermal protections (e.g. baseheating for Martian entries)
Convective heating mostly depends on groundspecies, radiative heating depends on excited species.Larger uncertainties
Accounting for an additional spectral dimension withgrids with over 106 points. Very computationallyintensive CFRD simulations.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Main Drivers
Do we need to take radiation into account?
Optically thin or thick?
Coupling between flow and radiation?
Equilibrium or non-equilibrium radiation?
Selection of an appropriate radiative database
Other issues (precursor, photo-chemistry, photo-ionisationprocesses)
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Aerothermodynamics of Entry Vehicles
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Aerothermodynamics of Entry Vehicles
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
Engineering Correlations for Radiation
Engineering Correlations useful when exploring different EDLscenarios
Exploratory parameters: Spacecraft sizing, atmosphericprofiles and composition, entry path and angle, aerodymamiccoefficients, etc...
Correlations then complemented with detailed CFRDcalculations for pre-selected Flight paths, at specificrepresentative entry points (∼5)
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
Blackbody radiation limit
spectral emissivity of a gas has atheoretical limit given by Planck’slaw
Bν(T ) =2hν3
c2
[exp
(hν
kBT
)− 1
]−1
The spectral integration yields theStefan–Boltzmann Law:∫
ν
Bν(T ) = σT 4The Sun’s emissivity is close to a blackbody
Engineering correlations are based on this upper theoretical limit for theemitted radiation
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
Stagnation Streamline flux dependence on cone radius
Convective fluxesSutton and Graves, Fay and Riddel correlations:
qwconv = f[√(
dudx
)s
]from Newtonian theory:
[(dudx
)s
]= 1
R
√2p−p∞ρ
qwconv ∝ 1√R
Radiative FluxesOptically Thin shock layer: qwrad =
(Eδ2
)a with δ w R
ρs/ρ∞
qwrad ∝ R
Requirements for minimizing convective and radiativeheat fluxes are mutually exclusive
aE: radiated power, half goes upstream, half to the wall. δ is the shock standoff. s: shock
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Stagnation Streamline flux dependence on entry speed
Convective fluxes
qwconv ≈ 1/2ρ∞u3∞Sta
qwconv ∝ u3∞
Radiative Fluxes
Ts =u2∞
2Cps;
qwrad = σT 4s =
u8∞
(2Cps )4
qwrad ∝ u8∞
Radiation dominates above10km/s
aSt: Stanton number
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Boltzmann and Goulard Numbers
Boltzmann number B−1o , Radiation/Convection ratio:
B−1o =
qradqconv
=σT 4
ρuCpT
Infinite slab approximationa. We also have CpT w u∞/2.
Goulard Number Γ, Radiative cooling parameter
Γ =2qwradqwconv
=2qwrad
1/2ρ∞u3∞
σ: Stefan-Boltzmann constanta
half the radiated power goes upstream, half to the wall
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Optically Thin and Optically Thick Limiting Cases
Optically Thin: Γn =4σT 4
s αδρ∞u∞hs
Optically Thicka: Γk =16σT 4
s α3ρ∞u∞hs
Γ < 10−3: radiation is not important
10−3 < Γ < 10−2: radiation is important but coupling isnot necessary
Γ > 10−2: coupling of the radiation to the flowfield isnecessary
The absorption coefficient is related to the opticaltransmissivity such that T = exp(−αδ). Transmissivitygoes from 100% (optically thin) to 0% (optically thick).
aknown as the Rosseland limit
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Radiative Transfer Regimes
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
Computational Fluid Radiative Dynamics Simulations
Development of radiative databasesproviding the spectral-dependent emissionεν and absorption α(ν) coefficients forany arbitrary state of the plasma
Accounting for bound, bound–free(photodissociation, photoionization,photodetachment) and free-free(Bremstrahlung) transitions
bound-bound transitions include atomic,diatomic and polyatomic transitions
Radiative transfer equation is then solvedover the computational domain
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Development of Spectral Databases
atomic and polyatomic transitionstypically simulated from externalradiative databases (NIST, TopBase,HITRAN)
diatomic transitions databases areexplicitely obtained using appropriatequantum-mechanics models
continuum radiation calculated frompublished absorption cross-sections(e.g. TopBase for atomicphotoionization), or fromsemi-empirical to exact cross-sectionsfor molecular continuum cross-sections
Absorption Coefficient for a 97%CO2–3%N2 Plasma inThermochemical Equilibrium at 5000K and 1bar
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
Line-by-Line Models
“Collection” of lines which correspond to the overall quantum-allowedradiative transitions between the internal levels of an atom/molecule.
Selection rules define the quantum-allowed transitions, which must respectangular and spin momentum conservation for atoms and molecules.
Three key parameters:1) Line position considering Planck’s Law: ν = Eu − El/hc ;2) Line intensity: Iν = NuAul∆Eul ;3) Line profile: F (ν − nu0), Voigt (sum of a Lorentz & Gaussian profile).
Radiative spectra obtained through the superposition of these overall lines.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Line-by-Line Models
“Collection” of lines which correspond to the overall quantum-allowedradiative transitions between the internal levels of an atom/molecule.
Selection rules define the quantum-allowed transitions, which must respectangular and spin momentum conservation for atoms and molecules.
Three key parameters:1) Line position considering Planck’s Law: ν = Eu − El/hc ;2) Line intensity: Iν = NuAul∆Eul ;3) Line profile: F (ν − nu0), Voigt (sum of a Lorentz & Gaussian profile).
Radiative spectra obtained through the superposition of these overall lines.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Line-by-Line Models
“Collection” of lines which correspond to the overall quantum-allowedradiative transitions between the internal levels of an atom/molecule.
Selection rules define the quantum-allowed transitions, which must respectangular and spin momentum conservation for atoms and molecules.
Three key parameters:1) Line position considering Planck’s Law: ν = Eu − El/hc ;2) Line intensity: Iν = NuAul∆Eul ;3) Line profile: F (ν − nu0), Voigt (sum of a Lorentz & Gaussian profile).
Radiative spectra obtained through the superposition of these overall lines.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Line-by-Line Models
“Collection” of lines which correspond to the overall quantum-allowedradiative transitions between the internal levels of an atom/molecule.
Selection rules define the quantum-allowed transitions, which must respectangular and spin momentum conservation for atoms and molecules.
Three key parameters:1) Line position considering Planck’s Law: ν = Eu − El/hc ;2) Line intensity: Iν = NuAul∆Eul ;3) Line profile: F (ν − nu0), Voigt (sum of a Lorentz & Gaussian profile).
Radiative spectra obtained through the superposition of these overall lines.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Key Parameters
The fundamental equation for intensity
Iν = NuAul∆EulF (ν − ν0)
can be decoupled in the following variables :
Nu : Level populations :Either a Boltzmann equilibrium distribution, either through Collisional-Radiativenonequilibrium models
Aul : Transition probabilities (Einstein Coefficients):From ”ab-initio” or measured transition moments
∆Eul : Level energies:Fitting and extrapolation of experimentally determined data
F (ν − ν0) : Line profile:Voigt profiles accounting for Doppler and Collisional broadening (depends on the localconditions of the plasma)
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Key Parameters
The fundamental equation for intensity
Iν = NuAul∆EulF (ν − ν0)
can be decoupled in the following variables :
Nu : Level populations :Either a Boltzmann equilibrium distribution, either through Collisional-Radiativenonequilibrium models
Aul : Transition probabilities (Einstein Coefficients):From ”ab-initio” or measured transition moments
∆Eul : Level energies:Fitting and extrapolation of experimentally determined data
F (ν − ν0) : Line profile:Voigt profiles accounting for Doppler and Collisional broadening (depends on the localconditions of the plasma)
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Engineering CorrelationsLarge-Scale CFRD Simulations
The SPARTAN Code
SPARTAN: Simulation of PlasmA Radiation inThermodynAmic Nonequilibrium
Simulation of Earth, Mars and Titan plasma radiation
63 atomic and molecular bound-bond, bound-free(Photodissociation, Photoionization, Photodetachment),and free-free transitions
Simulated species: C, C+, C−, N, N+, N−, O, O+, O−,Ar, Ar+, C2, H2, N2, N+
2 , O2, CN, CH, CO, CO+, NH,NO, OH, CO2
Code freely distributed under a Gnu Public License, seehttp://esther.ist.utl.pt/
SPARTAN Code Logo
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Elementary Radiative Processes
El
Eu
? ?
6
hν- hν-
hν-
hν-
hν-
spontaneous emission induced emission absorption
∂Nu
∂t= −NuAul
∂Nu
∂t= −NuBuluν
∂Nl
∂t= −NuBuluν
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Derivation of the Radiative Transfer Equation (RTE) (1/2)
Summing the three processes we have
∂Nu
∂t= −NuAul + [NuBul − NuBul ]uν
In Radiative equilibrium the net variation is 0, and radiation is given bythe Planck Blackbody Law
uoν(T ) =8πhν3
c3
[exp
(− hν
kBT
)− 1
]−1
we have
glBlu = guBul
Aul
Bul=
8πhν3
c3
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Derivation of the Radiative Transfer Equation (RTE) (2/2)
Integrating the expressions of the previous slide in volume from we obtainthe classical RTE equation:
cos θdLνdz
= εν − ανLν
with
εν =nuAulhν
4π
α(ν) =
(nu −
guglnl
)Bul
hν
c
which becomes the Beer-Lambert Law in 1D coordinates:
dIνdl
= ε− α(ν)Iν
and after integration:
Iν =ε
α(ν)[1− exp(−α(ν)l)]
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Ray-Tracing Methods for Space-Related Heat TransferAnalysis
Ray-Tracing: An exactmethod for determining thequantities of photons whichirradiate a surface.
qν =
∫ π/2
−π/2
∫ π
0Iν(θ, φ)cosθ sin θdθdφ
Iν =ε
α′[1 − exp(−αl(θ))]
Ray-tracing considers full 3D geometries, with the possibility of simpler2D/1D slab geometries.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Ray-Tracing Methods for Space-Related Heat TransferAnalysis
Ray-Tracing: An exactmethod for determining thequantities of photons whichirradiate a surface.
qν =
∫ π/2
−π/2
∫ π
0Iν(θ, φ)cosθ sin θdθdφ
Iν =ε
α′[1 − exp(−αl(θ))]
Ray-tracing considers full 3D geometries, with the possibility of simpler2D/1D slab geometries.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Ray-Tracing Methods for Space-Related Heat TransferAnalysis
Ray-Tracing: An exactmethod for determining thequantities of photons whichirradiate a surface.
qν =
∫ π/2
−π/2
∫ π
0Iν(θ, φ)cosθ sin θdθdφ
Iν =ε
α′[1 − exp(−αl(θ))]
Ray-tracing considers full 3D geometries, with the possibility of simpler2D/1D slab geometries.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Engineering CorrelationsLarge-Scale CFRD Simulations
Ray-Tracing Methods for Space-Related Heat TransferAnalysis
0 5 10 150
1
2
3
4
5
6
7
8
X(m)
Y(m
)
T (K)
500
1000
1500
2000
2500
3000
3500
4000
4500
Complex flow geometries with millions of molecular spectral lines
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Case Studies
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
IST-IPFN Participation is Space Exploration Programmes
Since 2004, IPFN has supported all the major Europeanplanetary exploration Missions
Support to the Huygens Titan entry mission in 2004
Support to the Mars EXPRESS Observation of the PHOENIXentry in 2008
Support to the upcoming Mars robotic exploration MissionEXOMARS in 2016 and 2018
IPFN is developing a new generation European shock-tube(ESTHER) for the support of planetary exploration missionson a total funding of 2M Euros
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Huygens Titan Entry (2005)
60 half angle blunted cone
Base diameter: 2.7 m
Nose radius: 1.25 m
Entry module mass: 318.62 kg
Aerodynamic databasesdeveloped by EADS between1991 and 1995.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Huygens Heat Fluxes: Nominal Yelle Atmospheric Profile
Titan Composition: 95% N2–5% CH4
Important Radiator species CN produced in the shock layer.correlations do not work anymore.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Validation of Aerothermodynamic Databases: Shock-TubesExperiments
TCM2 Shock-Tube at Marseilles, France, was utilized for validatingthe CFRD models used for Huygen’s Entry
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Acquisition Results: CN spectral time-resolved picture
Shot conditions :
Shock TubeClassical mixturepshock=200 Pa
Shock velocityvshock=5680 m/s
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
40 Pa test rebuilding, Boltzmann
Non-equilibrium zone, 1s integration Temporal evolution
Validation of Aerothermal databases against simpler (1D,
time-dependent) representative flow conditions
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Coupled CFD-Radiative Simulations of Huygens Entry
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Influence of Radiation and Radiation Coupling
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Mars EXPRESS Observation of the PHOENIX Entry
ESA Mars EXPRESS Orbiterprovided support for PHOENIX2008 Mars Entry
Mars EXPRESS TrackedPHOENIX Entry with his onboardinstrumentation (First Attempt attracking an Entry from anOnboard Satellite).
CFRD simulations prior to entry predicted the IR trail to be the mostemissive.
SPICAM VUV Camera and HRSC Visible Camera tracked the Entry.IR Fourier Spectrometer could not be turned on due to power budgetconstraints.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
CFRD Simulations of PHOENIX Entry
PHOENIX Temperature Profiles, t=203s Sample spectrum of the PHOENIX Plume
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
HRSC Observation in # 5647 during Phoenix EDL : Nadir Context of Limb
° ° SC /
SOWG 38, ESAC, Villafranca: HRSC Future Planning Hoffmann and Hauber 04 June 2008
195° E, 81.5° N: HRSC ND, spatial resolution 12.5 m/pixel, image width 18 km
HRSC Observation in # 5647 during Phoenix EDL : Pointing during 144 SRC Frames
f f f
SOWG 38, ESAC, Villafranca: HRSC Future Planning Hoffmann and Hauber 04 June 2008
Phoenix always in center of frame based on latest available Kernel from 25 May
HRSC in # 5647 during Phoenix EDL : SRC 076
Uppermost limb haze layers (detached haze y (layer) enter FOV
SOWG 38, ESAC, Villafranca: HRSC Future Planning Hoffmann and Hauber 04 June 2008
HRSC in # 5647 during Phoenix EDL : SRC 096
Upper limb within FOV
SOWG 38, ESAC, Villafranca: HRSC Future Planning Hoffmann and Hauber 04 June 2008
HRSC in # 5647 during Phoenix EDL : SRC 116
Optically thick limb at edge of FOVg
•No hints for flash or brightening
•Pointing and timing seem to be correct
Phoenix not detected:•Upper limit for energy releaserelease
•Consistent with continuous telemetry link
SOWG 38, ESAC, Villafranca: HRSC Future Planning Hoffmann and Hauber 04 June 2008
ESA UNCLASSIFIED – For Official Use
ExoMars Programme: two missions launched in 2016 and 2018.• The 2016 mission consists of the Trace Gas Orbiter (TGO) and the EDL Demonstrator Module (EDM)• The 2018 mission consists of the Rover, accommodated inside a Descent Module (DM) and carried
to Mars by a Carrier Module (CM)• Large international cooperation with Roscosmos and some contributions from NASA
Proton
Trace Gas Orbiter (TGO)
ExoMars Programme Mission Architecture
2016 Mission 2018 Mission
Carrier Module & Descent Module
Rover + Landed PlatformEDL Demonstrator Module (EDM)
+
Proton
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Radiative Transfer Towards Mars EXPRESS
Optical path Transmissivity Raddiation collected by one pixel of the Mars EXPRESSinstrumentation
Radiation in the VUV-Visible region was not detected, IR radiation was
predicted to be detected if the instrument had been switched on
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Spectral Database for CO2–N2 Mixtures
CO2 Infrared
CO Infrared
CO 4+
CO 3+
CO Angstrom
CO Triplet
CN Violet
CN Red
C2 Swan
C2 Phillips
C2 Mulliken
C2 Deslandres–D’Azambuja
C2 Ballik–Ramsay
O2 Sch.–Runge
O2 Sch.–Runge Cont.
N2 1+
N2 2+
NO Gamma
NO Beta
NO Delta
NO Epsilon
NO Beta
C Atomic
C Photoionization
N Atomic
N Photoionization
O Atomic
O Photoionization
C− Photodetachment
N− Photodetachment
O− Photodetachment
CO2 Photoionization
N2 Photoionization
O2 Photoionization
CN Photoionization
CO Photoionization
NO Photoionization
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Radiative Power for CO2–N2 Mixtures: Comparison WithOther Spectral Databases
1000 2000 3000 4000 5000 6000 7000 8000 9000 1000010
0
102
104
106
108
1010
1012
Temperature (K)
Rad
iativ
e P
ower
(W
/m3 ) CO
2 IR Other Systems
Comparison of the overall temperature dependent radiative power of CO2 IR radiation (red) and for the other
radiative systems (black) for an atmospheric pressure, Martian-type CO2–N2 plasma. Comparison is carried for the
SPARTAN code database (full lines) and the EM2C database (dotted lines).
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Example of a Ray Departing from the Afterbody Plume;PH (1/2)
103
104
105
10−15
10−10
10−5
100
Wavelength (A)
Inte
nsity
(W
/m2 /c
m−
1 )
Intensity at ray departureIntensity at ray arrival
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
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Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Example of a Ray Departing from the Afterbody Plume;PH (2/2)
4.17 4.1705 4.171 4.1715 4.172 4.1725
x 104
10−1
100
101
Wavelength (A)
Inte
nsity
(W
/m2 /c
m−
1 )
Intensity at ray departureIntensity at ray arrival
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Comparison of Stagnation Streamline and BackcoverShoulder Spectra; PH
VUV-Visible radiation higher for the stagnation streamlinepoints
For both points, CO2 radiation spectral intensity is severalorders of magnitude above Visible-VUV radiation
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Contribution of Radiative Fluxes above 1µm to the OverallRadiative Power; Large Spacecraft Configuration
0 5 10 15 20 25 30 35 40 45 5099.8
99.82
99.84
99.86
99.88
99.9
99.92
99.94
99.96
99.98
100
Wall Point
IR R
adia
tion
Con
trib
utio
n (%
)
PHPPP28P23SHA
Values for the smaller spacecraft configuration are similar. Other studies in the scope
of the ESA TC3 testcase confirm such findings for CO2–N2 mixtures (CN and C2
radiation less than 3% overall in the stagnation streamline point.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
The ESTHER Shock-Tube Project
European Shock Tube for High Enthalpy Research
European Space Agency project
International consortium, led by Instituto Superior Tecnico, for thedevelopment and comissioning of a shock-tube facility for planetaryexploration research in the high speed regime
Consortium partners include:
Fluid Gravity Eng. (Ermsworth, UK),Universite de Provence (Marseille, France),Ingenieurie Systemes Avances (Bordeaux, France),Moscow Institute for Physics and Technology (Moscow, Russia),Instituto de Soldadura e Qualidade (Lisboa, Portugal),Shock-Waves Laboratory (Aachen, Germany),University of Manchester (Manchester, UK),Universite Blaise Pascal (Clermont–Ferrand, France),Universite Paris VI (Paris, France)
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Shock-Tube Characteristics
Facility capable of reproducing shock waves for gas mixtures simulatingthe atmosphere of Earth, Mars and Venus (CO2–N2), Titan (N2–CH4).
High pressure reached in the driver section through the deflagration of ahigh-pressure H2–O2 mixture. This allows a quick-rise in pressure,enabling 3–4 shots per day, but needs special precautions related to thepresence of explosive gases.
Shock velocities of v '4–12km/s, allowing the simulation of orbital (slowspeed) and interplanetary superorbital entry plasma flows.
High-speed automated diagnostics (MHz) for control, acquisition, andcollecting light emitted by the plasma.
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Shock-Tube Design (1/4)
High Pressure Driver Section
600 bar maxium working pressure
900 bar design limit
Internal diameter 200mm
Outer diameter 360mm
Internal length 1.5m
Nominal mixture70%He,20%H2,10%O2
Initial pressure 10 to 50 bar
High pressure ignition and safetysystem
Combustion gas preparation systemand induction system includingmixing, storage, valves, probes andgauges
Gasket system with rupture pressures60 to 600 bar
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Shock-Tube Design (2/4)
Compression Tube (or second stage)
Internal diameter 130mm
Outer diameter 150mm, length 6.5m
Initial pressure 0.1-0.5 bar (optimized for each run)
Gasket system with rupture pressures 5 to 25 bar
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Shock-Tube Design (3/4)
Working Section
Internal diameter: 80mm
outer diameter: 150mm
length from diaphragm to window:4m
total internal length to the dumptank: 5.4m
Initial pressure 10 to 1000Pa
Pumping system: minimum pressureof 10-8 mbar during cleaningprocedures, ensure known initial testgas composition.
Working gas preparation andinduction system including probesand gauges.
Windows (UV/VUV transparent)and window mounting system.
Shock speed / pressure measurementsystem.
Diaphragm to dump tankM. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
IntroductionCorrelations & High-Fidelity Sims.
Case Studies
Titan Entry: HuygensMars Entry: PHOENIX and EXOMARSThe ESTHER Shock Tube
Shock-Tube Design (4/4)
Dump Tank
Post window section lead in tube to dump tank
Pressure range, vacuum to 2bar pressure post shot.
Diameter: 1 m
Length: 3 m
M. Lino da Silva, B. Lopez, V. Guerra and J. Loureiro, IPFN Reentry Plasmas
Outside view of the laboratory and view of the experimental hall
ESTHER shock-tube
Hypersonic Plasmas LaboratoryEuropean Shock-Tube for High Enthalphy Research
Facility Specifications
Length: 16m Test-section diameter: 80mm Shock Velocities: 4-12+ km/s Pre-shock pressures: 0.1-100+ mbar Planetary compositions: Air (Earth), CO2-N2 (Venus, Mars), N2-CH4 (Titan)
Shock-Tube: A facility for reproducing the conditions of an atmospheric entry Support to planetary exploration missions and meteoroids planetary protection research 2M€ total funding, 1,75M€ funding from the European Space Agency First facility of its class to be built in the last 30 years in Europe, located at IST-IPFN World class facility capable of reaching superorbital shock-speeds in excess of 10km/s
Example of a shock-induced plasma