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Ground Testing of In-Flight Experiments of Re-Entry CubeSat QARMAN

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

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Ground Testing of In-Flight Experiments of Re-Entry CubeSat QARMAN

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  1. 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

  2. QARMAN: Real Flight Testbed QubeSat 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. VKI Plasmatron Measurement Techniques Courtesy: Helber • Ablation Measurements • Pyrometer : Temperature • Radiometer : Temperature as f(ε) • Spectrometer : Species Detection • High Speed Camera • Infrared Camera • Thermocouples • Free Stream Measurements • Cold Wall Heat Flux • Static&Total Pressure • Spectrometer

  4. VKI Plasmatron Stagnation Point Heating by Fay&Riddell, 1958 Local Heat Transfer Simulation Thermo-chemical equilibrium at stagnation point: → Subsonic plasma Full simulation of stagnation region

  5. Velocity Gradient, β, Duplication • β Definition differs in Subsonic and Hypersonic due to BL model • Unique to Trajectory and Vehicle Geometry Stagnation Line at Plasmatron QARMAN Stagnation Line at 50 km

  6. Velocity Gradient, β, Duplication Conventional Method: Effective Radius Modified Newtonian Theory Spherical Bodies Blunt Bodies… ? Ref: Lees1957

  7. Velocity Gradient, β, Duplication Velocity Gradient of Blunt Bodies Boison & Curtiss 1958 • Geometries having bluntness parameter x*/r* less than 0.25 no longer obey MNT! x*/r*

  8. Velocity Gradient, β, Duplication Iterative Approach for Test Model Geometry Determination 1- Pick a β 1- Take the ICP Computation and calculate NDPs 2- Determine the Reff Hypersonic (i.e MNT) 3- Pass from Reff Hypersonic to Subsonic by matching the heat flux equation 2- Momentum equation provides the Reff Subsonic for ground facility Extract Rmodel @ 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 Payloads Overview

  12. Aerothermodynamic Instrumentation Phase 3 Budgets Total Mass: 319 g Total Energy Consumption: 0.556 W h Total Data Size: 21.57 KB

  13. QARMAN TPS Selection Campaign Samples: QARMAN 1/2 Scale Materials: Cork P50 and ASTERM Objectives: 1- Monitor insulation properties 2- Monitor corner behavior Conditions: Constant Pressure 100 mbar Target Heat Fluxes: 708; 1250; 1500; 1640 kW/m2 Total duration 80 s (20 s at each heat flux) QARMAN TPS Selection Campaign - Enthalpy measured by REDES [MJ/kg]

  14. QARMAN TPS Selection Campaign • Campaign Completed – 16 May 2013 • Measurement Techniques: • Free Stream Measurements • Water cooled calorimeter • Pitot Probe and Static Pressure Sensor • Spectrometer • Sample Measurements • Radiometer • Pyrometer • High Speed Camera • Thermocouples, 3 Type E + 1 Type K • 3 Spectrometers aligned from wall stagnation outward QARMAN TPS Selection Campaign - Enthalpy measured by REDES [MJ/kg]

  15. QARMAN TPS Selection Campaign High Speed Camera → Recession & Swelling Cork P50 ASTERM Stag. Point: +1mm Corner: -7.4 mm Stag. Point: -3.2mm Corner: -6.6 mm

  16. QARMAN TPS Selection Campaign Cork P50 ASTERM Tsurface = 2500 K Tsurface = 2400 K Pyrometer Radiometer ASTERM Thermocouples Cork Spectroscopic Characterization, Talk by B. Helber this afternoon

  17. Payloads: XPL01 Summary TPS Efficiency & Heating 2 Thermal Plugs Measurement Chain

  18. Payloads: XPL01 TPS Efficiency & Heating Thermal Plugs • 6 Thermocouples at 2.5, 5, 10, 20, 30, 40 mm • At 60° apart • 2 thermocouple per sidetrail • TC Type K or R inserted in U-shape 60° 14mm 50mm

  19. XPL02: Stagnation Region & TPS Pressure ExoMars Concept Diagonally 2 pressure taps CFD: QARMAN @ 66km Courtesy: G. Pinaud

  20. AeroSDS -> XPL03 • Stability determination (max. angles and rates) in-flight with • Pressure sensors • Accelerometers • Gyroscopes • Strain gauges 6-DoF simulations for osciallation frequency CFD simulations for surface pressure, temperature and force determination Wall temperature T [K]

  21. Payloads: XPL06 Presented by Bailet earlier today Spectrometer support structure Radiation Study: Spectrometer Light splitter Optical path sleeve TPS Spectrometer TPS bonding structure Photometer Staged optical path Measurement Setup

  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, IsilSakraker, Cem O. Asma

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