METHOD OF DETERMINING MANEUVER TERMINATION INTERVAL AND SHUTTING DOWN OF ACCELERATION UNIT SUSTAINER ENGINE Russian patent published in 2012 - IPC B64G1/24 

FIELD: transport.

SUBSTANCE: invention relates to termination control of rocket acceleration unit uncontrolled-thrust sustainer engines. Proposed method comprises forecasting sustainer engine shutdown in changing over to termination control before spaceship separation when functional reaches preset power. For this, during said transition determined is conditional time of rocket propellant combustion (propellant consumption) and difference between said conditional time and preset time specified in flight mission. Said difference describes sustainer engine operation available time to be compared with calculated on the basis of flight mission. Is calculated time exceeds preset time then maneuver termination moment (engine shutdown) is defined as the sum of the interval of changing to termination control available time of engine operation. Said summed time is memorised to forecast acceleration unit motion at every interval of termination control with constant integration step. Said step equals relation of period to termination of maneuver to preset number of integration steps in acceleration unit motion model. Acceleration fuel propellant and final maneuver may terminate at shortage of power functional. In this case, knowledge of the moment of maneuver termination allows setting the spaceship orbit required inclination.

EFFECT: higher accuracy.

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