METHOD OF ADJUSTING AND CONTROL OF PARAMETERS OF LIQUID-PROPELLANT ROCKET ENGINE Russian patent published in 2006 - IPC F02K9/56 

FIELD: rocketry.

SUBSTANCE: invention is designed to control thrust and ratio of propellant components of liquid propellant rocket engine. Tests are carried out at least at three modes with different thrust levels. At each mode control devices are set in positions found from mathematical model of engine by calculation and then they are re-adjusted in turn being set in preselected positions and mass flow rates of propellant components are measured. Coefficients of transmission of control devices and their correcting actions are found and then engine is adjusted to preset value of thrust level and to one and the same value of coefficient K_m of components for all modes. Value of components for each mode is determined and is set, depending on thrust level in form of polynomials whose approximating coefficients are considered temperature constants for engines of this type. Adjustment of engine parameters at standard operating conditions is done by simultaneous re-adjustment of control devices in positions found by equations of their polynomial relations from thrust level with due account of corrections for deviation of current value of coefficient K_m from nominal value, constant coefficients of said relations being individual constants of engine, and current values of thrust level and coefficient K_m included into said polynominal relations are corrected by value of temperature corrections.

EFFECT: provision of high degree of thrust control and ratio of components with engine operating within wide range of mode changes with due account of actual temperature of propellant components.

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