| 摘要 |
FIELD: rocketry. ^ SUBSTANCE: proposed solid-propellant rocket engine consists of combustion chamber accommodating solid-propellant charge secured by support grids, nozzle assembly and igniter. Charge is made form of all-round-burning grain consisting of concentrically arranged rings interconnected by radial bridges whose thickness is equal to thickness of rings. Relationships between summary area of critical section of nozzle assembly, summary initial area of charge burning surface, initial areas of burning surface of inner channel, channels between rings and outer surface, respectively, initial through areas of inner channel, channels between rings and between outer surface of charge and wall of combustion chamber, respectively, and experimental value of tolerable relative consumption for propellant used in charge, all protected by claim, are provided. ^ EFFECT: provision of maximum tolerable volumetric loading ratio of combustion chamber of any shape with possibility of obtaining either progressive or neutral thrust law. ^ 5 dwg
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