| 摘要 |
FIELD: rocketry. ^ SUBSTANCE: proposed reheat liquid-propellant rocket engine has engine chamber with regenerative cooling duct and injector assembly, turbopump set, gas generator, starting system, propellant components igniting means and propellant main lines. Outlet of oxidizer pump is connected with inlet of gas generator. Outlet of first stage of propellant pump is connected with channels of chamber regenerative cooling channels and with injector assembly. Outlet of second stage of propellant pump is connected with flow regulator provided with electric drive. Other inlet of regulator is connected with starting tank containing standard propellant. Outlet of regulator is connected with gas generator. Outlet of gas generator is connected with inlet of turbine of turbopump set whose outlet is connected with injector assembly. Flow regulator is provided with preliminarily stage hydraulic drive which is connected with starting tank containing standard propellant through cavitation jet and hydraulic relay. Said hydraulic relay is connected with second stage of propellant pump. Throttle installed at outlet of first stage of propellant pump is made integral with preliminary stage controlled valve. ^ EFFECT: simplified pneumohydraulic system of engine, reduced overall dimensions and mass and cost of engine, provision of reliable operation under any operating conditions. ^ 3 cl, 2 dwg |
