FIELD: rocketry.
SUBSTANCE: control of solid fuel rocket engines. A method for controlling a solid-fuel adjustable propulsion system, which consists in changing the critical cross-sectional area of the nozzles by applying to the nozzle drive a control signal from a pressure stabilization system, generated depending on the measured pressure in the engine, according to the invention, the required quality of engine operation under conditions of parametric uncertainty is achieved by introducing into the stabilization systems pressure (SSP) of functional correction of the setpoint signal based on the measured pressure in the combustion chamber of a solid rocket propulsion system (SRPS).
EFFECT: ensuring the use of SRPS at fuel charge temperatures different from the calculated ones.
1 cl, 8 dwg
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