PLANT FOR DETERMINATION OF RATE OF BURNING OF SOLID ROCKET PROPELLANT Russian patent published in 2001 - IPC

FIELD: rocketry. SUBSTANCE: proposed plant includes combustion chamber, solid propellant specimen, pressure sensor, cover with matching cone and radiator at whose input transceiving SHF sensor is coupled. Radiator is connected with solid propellant specimen holder at outlet which is made in form of sleeve whose inner diameter exceeds diameter of matching cone. Cavity of chamber located opposite radiator is filled with filler. Besides that, combustion chamber is connected with Vacuum reservoir through pipe line with actuating mechanism which opens valve by command from time relay. Water is used as filler filling lower portion of chamber. Combustion chamber is so positioned that radiator with specimen is located at the top. EFFECT: increased capacity of plant. 2 cl, 2 dwg