INFERNITYFLAME IN FREEFALL

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Attribute
Hardware groupSPICE duct group
Pillars
PreventionSuppression
Fuel phaseSolid
MaterialSIBAL cotton-fiberglass fabric, Nomex, Ultem, PMMA, wax-saturated fiberglass, paraffin and Japan wax candles
ShapeThin and thick flat samples, solid spheres, and candles inside thin ceramic tubes
SizeThin flats 120 x 10-20 mm; thick flats 50 x 10 x 1-2 mm; PMMA spheres 10-20 mm diameter; candles 6 mm diameter x 25 mm
O2 concentration21%
Pressure14.7 psi
Airflow50 cm/s
FacilityMicrogravity Science Glovebox (MSG) with the SPICE flow duct
Module / vehicleInternational Space Station
Sensors
  • Video and still cameras with telemetry overlay
  • Radiometer for flame output
  • Anemometer for duct airflow
  • Nitrogen mass flow controller
Variables tested
  • Fuel material, geometry and thickness across 41 samples
  • Duct airflow from 5 to 50 cm/s
  • Nitrogen suppressant flow from 0 to 500 cc/min ramp to extinction
  • Front versus back ignition on PMMA spheres
ObjectivesTest whether solid materials burn as well in microgravity as in normal gravity when ventilation is adequate, and identify how suppressant application and fuel geometry change extinction behavior in a crewed spacecraft.
Key findings
  • Burned 41 fuel samples across 89 test points inside the sealed MSG work volume.
  • Nitrogen suppressant was ramped from 0 to 500 cc/min until extinction, linking the experiment directly to spacecraft extinguisher practice.
  • Flame shape, spread rate, pulsation and time to extinction were recorded against airflow, fuel geometry and suppressant flow.
  • The data feed flame-spread and suppression models used to design spacecraft fire detection and suppression systems.
Relevant environments
Spacecraft cabinSpace stationLunar baseMars basePressurized rover
SourceNASA PSI