FIELD: transport.
SUBSTANCE: invention relates to fire protection of inhabited pressure compartments of spacecrafts. Additional container with gas working medium is placed adjacent to sample combustion chamber made in the form of cylinder. The combustion chamber at its both ends is connected with additional container by openings for working gas medium passage when closed loop of its motion is created. The combustion chamber and additional container are equipped with plate-type heat exchangers one of which is located in combustion chamber between the axis of centrifuge rotation and sample of material being tested, and the other one - in additional container between the axis of centrifuge rotation and working gas medium outlet from combustion chamber. Opening at the side of working gas medium inlet into combustion chamber is closed by grid made of incombustible material with low hydraulic resistance. Openings between combustion chamber and additional container at each end of combustion chamber are made with port areas not less than combustion chamber cross-sectional area in the region of tested material sample location.
EFFECT: determination of material combustion limits from gravity acceleration depending on oxygen concentration in spacecraft pressure compartment atmosphere.
8 dwg, 1 tbl
