FIELD: fire-prevention facilities.
SUBSTANCE: invention relates to devices for determining the data required for development of fire-fighting systems in habitable pressurised compartments of the spacecrafts (hereinafter - SC) in orbital flight. The device for determining the process parameters of extinguishing fire under the conditions of habitable pressurised compartments of the spacecrafts in orbital flight, is located in the habitable pressurised compartment of the spacecraft and comprises a combustion chamber blown with flow of gaseous atmosphere of the pressurised compartment. In the combustion chamber the test material samples are installed. The combustible flat samples of materials are placed in parallel to each other. The distance between the samples and between the samples and elements of the combustion chamber are set not less than the value determined from the relation: dmin=4,64×(Lmod×νen/Vlim)0,5, where Lmod is the length of the sample in the direction of gas medium flow, cm, νen is the kinematic coefficient of viscosity of the gas medium in the combustion zone, cm2/s; Vlim is the limit speed of the gas medium for combustion of test material, cm/s. The geometric center of the combustion chamber of the device during experiments with this material is placed at a distance from the center of mass of the spacecraft, not exceeding a value determined from the relation: Rmax=0.1·glim/ω2 cc.max, where glim is limit acceleration of force of gravity for combustion of the test material, cm2/s, ωcc.max is maximum possible angular velocity of rotation of the spacecraft in normal orbital flight, l/s.
EFFECT: increased efficiency of extinguishing fire.
5 dwg
