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I. Şakraker, C.O. Asma, R. Torras-Nadal, O. Chazot20.06.2013
IPPW-10
San Jose, CA, USA
Ground Testing of In-Flight Experiments of Re-Entry CubeSat QARMAN
2
QARMAN: Real Flight TestbedQubeSat for Aerothermodynamic Research and
Measurements on AblatioN • Platform: Triple CubeSat with Ablative TPS• Mission: Atmospheric Entry Technology Demonstrator, Starting Altitude of 350 km• Launch: 2015 with QB50 Network
Why a Re-Entry “CubeSat”?→ Standardized small platform eliminates the only drawback: High Costs
→ Standard launch adaptors leading to highly flexible launch opportunities
→ If successful, it will be an affordable test platform for ablators, ceramics, sensors, trajectories, in-flight demonstrations, de-orbiting systems etc.
3
Free Stream Measurements•Cold Wall Heat Flux•Static&Total Pressure•Spectrometer
Ablation Measurements•Pyrometer : Temperature •Radiometer : Temperature as f(ε)•Spectrometer : Species Detection•High Speed Camera•Infrared Camera•Thermocouples
VKI PlasmatronMeasurement Techniques
Courtesy: Helber
4
VKI PlasmatronStagnation Point Heating by Fay&Riddell, 1958
weee
ww
edge
eeew hh
ds
dUq
1.02/12/16.0Pr763.0
Local Heat Transfer Simulation Thermo-chemical equilibrium at stagnation point:
→ Subsonic plasmaFull simulation of stagnation region
te
fe HH t
efe pp t
efe
5
Velocity Gradient, β, Duplication• β Definition differs in Subsonic and Hypersonic due to BL model• Unique to Trajectory and Vehicle Geometry
QARMAN Stagnation Line at 50 kmStagnation Line at Plasmatron
6
Velocity Gradient, β, DuplicationConventional Method: Effective Radius
Modified Newtonian Theory
Spherical Bodies Blunt Bodies… ?
Ref: Lees1957
e
e
eff
flight pp
R
3
81
7
Velocity Gradient of Blunt BodiesBoison & Curtiss 1958
Geometries having bluntness parameter x*/r* less than 0.25 no longer obey MNT!
x*/r*
Velocity Gradient, β, Duplication
8
Iterative Approach for Test Model Geometry Determination1- Pick a β
2- Determine the Reff Hypersonic (i.e MNT)3- Pass from Reff Hypersonic to Subsonic by matching the heat flux equation
ground
se
flights
SeffHeffPP
PRR
,,
1- Take the ICP Computation and calculate NDPs
2- Momentum equation provides the Reff Subsonic for ground facility
2
mod,
25.3
12NDP
NDPNDPNDP
RR el
Seff
Extract Rmodel
Velocity Gradient, β, Duplication
@ 66 km Rm=5.8 mm@ 60 km Rm=94 mm
9
QARMAN Flight Challenges
Flight Aerothermodynamic Database CFD++
10
QARMAN: Sensor Accommodation
11
Experimental PayloadsOverview
Payload Objective Sensor
XPL01 TPS Efficiency Temperature
XPL02 TPS & Environment Pressure
XPL03 Stability Pressure
XPL04 Shear Force, Transition Pressure, Skin Friction
XPL05 Off-Stagnation Temperature
Temperature
XPL06 Aerothermodynamic Environment and Radiation
Spectrometer
12
Aerothermodynamic Instrumentation
Investigated Challenge Parameter to measure Sensor Phase
TPS Efficiency Temperature Distribution 12 x TC 3
TPS & Environment Pressure 2 x Pressure Sensor 3
Stability Pressure 2 x Pressure Sensor 2b
Rarified Flow Conditions Low Pressure / Vacuum 1 x Vacuum Sensor 2a2b
Shear Force, Laminar to Turbulence Transition Skin Friction 4 x Preston Tube
2b
3
Off-Stagnation Temperature Evolution Temperature 10 x TC
2b
3
ATD Environment Species 1 x Spectrometer 3Intensity 1 x Photodiode 3
Phase 3 BudgetsTotal Mass: 319 gTotal Energy Consumption: 0.556 W hTotal Data Size: 21.57 KB
13Q1 Q2 Q3 Q4
29.00
31.00
33.00
35.00
37.00
39.00
41.00
Cork - PeakCork - IntegralASTERM - PeakASTERM - Integral
QARMAN TPS Selection Campaign - Enthalpy measured by REDES [MJ/kg]
Samples: QARMAN 1/2 ScaleMaterials: Cork P50 and ASTERMObjectives: 1- Monitor insulation properties
2- Monitor corner behaviorConditions:Constant Pressure 100 mbarTarget Heat Fluxes: 708; 1250; 1500; 1640 kW/m2
Total duration 80 s (20 s at each heat flux)
QARMAN TPS Selection Campaign
14Q1 Q2 Q3 Q4
29.00
31.00
33.00
35.00
37.00
39.00
41.00
Cork - PeakCork - IntegralASTERM - PeakASTERM - Integral
QARMAN TPS Selection Campaign - Enthalpy measured by REDES [MJ/kg]
Campaign Completed – 16 May 2013
Measurement Techniques:Free Stream Measurements- Water cooled calorimeter- Pitot Probe and Static Pressure Sensor- SpectrometerSample Measurements- Radiometer- Pyrometer- High Speed Camera- Thermocouples, 3 Type E + 1 Type K- 3 Spectrometers aligned from wall stagnation outward
QARMAN TPS Selection Campaign
15
High Speed Camera → Recession & SwellingASTERMCork P50
Stag. Point: +1mmCorner: -7.4 mm
Stag. Point: -3.2mmCorner: -6.6 mm
QARMAN TPS Selection Campaign
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QARMAN TPS Selection CampaignASTERMCork P50
PyrometerRadiometer
Thermocouples
ASTERM
Cork
Tsurface = 2400 K Tsurface = 2500 K
Spectroscopic Characterization,Talk by B. Helber this afternoon
17
Payloads: XPL01TPS Efficiency & Heating2 Thermal Plugs
Measurement Chain
Summary
18
Thermal Plugs
60°
14mm
50mm
• 6 Thermocouples at 2.5, 5, 10, 20, 30, 40 mm• At 60° apart• 2 thermocouple per side trail• TC Type K or R inserted in U-shape
Payloads: XPL01TPS Efficiency & Heating
19
XPL02: Stagnation Region & TPS PressureExoMars Concept
Diagonally 2 pressure taps
CFD: QARMAN @ 66km
Courtesy: G. Pinaud
20
Stability determination (max. angles and rates) in-flight with• Pressure sensors• Accelerometers• Gyroscopes• Strain gauges
AeroSDS -> XPL03
Wall temperature T [K]
6-DoF simulations for osciallation frequency
CFD simulations for surface pressure, temperature and force determination
21
Payloads: XPL06Radiation Study: Spectrometer
Spectrometer
Spectrometer support
structure
TPS bonding structure
TPS
Photometer
Light splitterOptical
path sleeve
Staged optical path
Measurement Setup
Presented by Bailet earlier today
22
Questions?
isil.sakraker@vki.ac.be
QARMAN project is partially supported by the European Community Framework Programme 7, Grant Agreement no. 284427 in the framework of QB50 Project.
QARMAN Team: Thorsten Scholz, Gilles Bailet, Isil Sakraker, Cem O. Asma
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