Measurement of critical aerothermodynamic phenomena during the hypersonic flight of an atmospheric reentry vehicle, for comparison with computer analytical and wind/plasma tunnel test predictions.
Reference payloads
Flush Air Data System
Pyrometric Instrumentation for Nose Heating
Laminar to Turbulent Transition Characterisation (natural transition and roughness induced transition)
Shock Wave Boundary Layer Interaction on a body flap and in the area surrounding the body flap.
Shock Layer Chemistry measurements via emission spectroscopy.
Sharp Hot Structure experiment
Skin Friction measurement
Base Flow characterisation
Spacecraft
Total mass
Payload mass Thermal Protection System
Landing system
Data volume
Stabilisation
436 kg
41 kg
Non-ablative materials (C-SiC on nose and flaps, PM1000 on the conical parts) – Hot structure concept
Parachute system (with supersonic stabiliser)
100 Mb (stored in redundant crash resistant memory units) Passive (based on natural aerodynamic stability)
Mission
Entry velocity
Maximum Heat Flux
Maximum g-loads Maximum Mach number
5 km/s
1.7 MW/m²
16 g Mach 20
Ballistic trajectory
Launch vehicle
Volna (decommissioned Russian ICBM)
Launch mass
436 kg into suborbital trajectory
Launch site
Pacific Ocean (off the Kamchatka coast)
Launch windows
April-October 2011
Flight duration
10 minutes
Landing site
Kura Range (Kamchatka, Russia)
Gound Station
Russian ground station in the Kura range
Programmatics
Spacecraft design and manufacturing funded within Interim Technology Phase for Reusable Transportation and Atmospheric Reentry
Payload funded through TRP, GSTP, and provided as national contributions of European research entities
Launch and recovery operations costs paid proportionally by the countries participating in the vehicle development
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