FIELD: rocketry.
SUBSTANCE: proposed method of controlling fuel consumption of a rocket propulsion system can be used in rocket engineering and is intended to control the ratio of fuel components when controlling consumption of two-component liquid fuel components during bench tests of liquid-propellant engines (LPE), as well as during flight of carrier rockets and boosters, including with multiple switching on of sustainer liquid-propellant rocket engine. Control method consists in maintaining a given ratio of fuel components second consumption based on processing of continuous information from vibration acceleration sensors located on rocket engine chambers at standard places intended for vibration sensors arrangement, allowing to estimate current values of frequency of high-frequency self-oscillations in rocket engine chamber. Analytical dependence of the value of the ratio of fuel components on the frequency of high-frequency self-oscillations in the chamber is formed based on the results of the first fire bench tests of the liquid-propellant engine.
EFFECT: reduced weight of the system for controlling the ratio of fuel components, which improves the design perfection of the stages of carrier rockets and boosters and, as a result, increases the weight of the output payload.
1 cl, 3 dwg
