Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Table 7

Characteristics of facilities for TPS testing at high heat-fluxes.

Name	Heat-flux (MW/m^2)	Stagnation pressure (bar)	Running time	Model size (mm)	Measurements	Remarks
JP200	5–25	1.5–9	60 s	Flat plate: 200 ∗ 40 mm Thickness: 10–25 mm	Recession rate, heat flux, pressure and surface temperature	Turbulent flow. Test of tiles, gaps, and steps. Dynamic and static
SCIROCCO	0.26–3 Throat: Up to 21	0.005–0.11 Throat: up to 1.5	1800 s; 20 s	800 For 20 mm; MW: 25 For 100 mm:  8 MW	static pressure, stagnation pressure, temperature, heat-flux	TPS assembly
PWK1-2-4	Up to 15	20–5000 Pa	Max 3 h	320	Heat flux, pressure, oxygen partial pressure, dissociation degree, Mach number	Material characterization, high-enthalpy entry simulations, heat shield testing
GLADIS	4–45	Near vacuum conditions	Pulse of 1 ms, to 45 s pulses per hour	70	Heat-flux, temperature	Test of large components. Testing of full-scale ITER divertor targets. Hydrogen beam facility
LBK	10	Up to ~1 bar with short nozzle	<1800 s	?	Pressure, temperature, heat flux, dissociation, emission	Aerodynamic heating studies, TPS qualification