FIELD: rocketry.
SUBSTANCE: proposed solid-propellant charge has open front and nozzle end faces and through inner channel with progressive cylindrical and compensating burning surfaces. Heat protective bushing with sunk section between housing and propellant surface is made on nozzle end face of charge. Compensating conical burning surface is made on front and nozzle end faces at minimum possible and angle to axis of charge, said angle should be not less than 90°. Sunk section of heat protective bushing is 0.08-0.17 of length of housing in place of location of propellant. Thickness of wall of heat protective bushing is 0.06-0.25 of thickness of charge arch.
EFFECT: provision of maximum possible performance characteristics of impulse engine.
6 dwg
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