Facts and figures

14 PRO. 2009 1507

Expert Mission Summary
Mission objectives	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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