METHOD FOR STARTING LIQUID PROPELLANT ENGINES OF SECTIONAL ROCKET AND DEVICE FOR IMPLEMENTING THE SAME Russian patent published in 1997 - IPC

FIELD: rocket engineering. SUBSTANCE: method for starting liquid propellant engines provides operation of the engines until any propellant component complete comes spent, when appropriate booster pump of the engine is started to be filled with gaseous impurities, this engine hydraulic turbine loading lowers, impeller angular frequency increases, and outlet pressure decreases due to cavitation initiation and development. The engines come turned off on achieving permissible value by one of these parameters. As this takes place, permitting value of angular frequency and pressure are specified so as the first instruction to turn off the engines were implemented before the pressure comes low at outlets of the main pumps of the engine. This allows one to minimize afterpulse spread and provide "standard" gradient of flight thrust decrease. The device for turning off the engine on spending one propellant component has a sensor connected to information input of frequency converter 22, set point device 23 for specifying permissible value of the monitored parameter, comparator 24, switch 27, controller 25 and control instruction generator 26. Sensor output is connected to the input of drive 14 of controller 13 of engine 1 thrust. As this takes place pulse sensor 15 of angular frequency of the booster pump 8 or frequency pressure sensor at this pump outlet may be used. EFFECT: higher efficiency. 5 cl, 7 dwg