METHOD FOR CONTROL OF THRUST VECTOR OF LIQUID-PROPELLANT ROCKET ENGINE AND LIQUID-PROPELLANT ROCKET ENGINE WITH USE OF THAT ONE

摘要

The invention relates to rocket-space engineering and can be used for control of high voltage current of liquid-propellant sustainer with turbo-pump system of supply of two fuel components to combustion chamber for stages of rockets and upper stages of rocket-carriers and spacecrafts. The method includes gas-dynamical control of thrust vector of fluid jet propulsion with turbo-pump system of supply of two fuel components without afterburning of exhaust gas of the turbine. In the process of control one applies in sequence first a controlled non-symmetrical injection of exhaust turbine gas to supersonic flow of the nozzle till complete use of gas, and for following increase of side steering efforts one injects an oxidation fuel component to supersonic flow downstream of the units for injection of exhaust turbine gas. Different methods of distribution of exhaust gas and different methods of injection of oxidation fuel component to supersonic flow are used. The device is a liquid-propellant rocket engine that includes a combustion chamber with supersonic nozzle, a turbo-pump system for fuel supply to the combustion chamber with turbine that includes exhaust collector of generator gas connected with a system of gas ducts and gas distributors to collectors of units for injection of exhaust gas to supersonic section of the nozzle. Downstream of the gas injection units in each quarter of the nozzle symmetrically in planes of thrust vector control installed are units for injection of oxidation fuel component, those are connected to the drives of the system for control of oxidizer injection and injection of exhaust gas. Advantage of the method is in increase of mass-dimensions and operation parameters of the system for control of engine thrust vector and propulsion installation as a whole.