FIELD: rocketry.
SUBSTANCE: proposed solid-propellant rocket engine contains nozzle unit, igniter and solid-propellant charge with star-shaped section central channel and overhung nonrestricted rear end face rigidly connected with body. Channel of charge is provided with local conical widening from side of rear end face whose base coincides with plane limiting the charge. Length of conical section is 1.5-2.2 of length of charge overhung part. Diameter of base of conical section is 1.8-2.2 of channel diameter. Clearance equal to 0.1-0.2 of length of overhung part of charge from side of rear end face is provided between end face of charge and nozzle bottom.
EFFECT: increased reliability of solid propellant rocket engine by reduction and thrust peaks at high rate of filling owing to choice of optimum relation of main design parameters.
4 dwg
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Authors
Dates
2008-02-20—Published
2006-06-29—Filed