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Ground Testing of In-Flight Experiments of Re-Entry CubeSat QARMAN. I. Şakraker , C.O. Asma, R. Torras-Nadal , O. Chazot 20.06.2013 IPPW-10 San Jose, CA, USA. QARMAN: Real Flight Testbed. Q ubeSat for A erothermodynamic R esearch and M easurements on A blatio N - PowerPoint PPT Presentation
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I. Şakraker, C.O. Asma, R. Torras-Nadal, O. Chazot20.06.2013
IPPW-10San 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
dsdUq
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 ppR
381
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,
25.312
NDPNDPNDPNDP
RR elSeff
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 3Stability 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
16
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?
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