FIELD: rocketry.
SUBSTANCE: invention relates to thrust control valve with reduced gain designed for use in rocket engine. Proposed valve has body with intake fluid medium channel and piston-cylinder unit to control release of fluid medium from valve. Fluid medium intake channel has at least one flow regulator made in said channel. At least one flow regulator has rectangular part to provide improved stability of control, T-shaped and slotted part to control thrust at transient starting conditions and turbine fixed bypass part designed for mating with lock. Lock contains at least one fluid medium channel and provides reproduced control of preset fixed bypass flow rate.
EFFECT: provision of thrust control at reduced gain, elimination of fluctuations of control action.
9 cl, 5 dwg
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