LIQUID PROPELLANT ROCKET ENGINE

摘要

A liquid propellant rocket engine is provided to improve the reliability of the rocket engine by maintaining a stable combustion temperature of a gas generating unit. In a liquid propellant rocket engine(100), a fuel supplying pump(120) supplied fuel to a combustion chamber(110). An oxidizer supplying pump(130) supplies an oxidizer to the combustion chamber. A gas generating unit(140) generates gas by receiving a part of the fuel and the oxidizer supplied from the fuel supplying pump and the oxidizer supplying pump. A turbine(150) is rotated by the gas supplied from the gas generating unit and drives the fuel supplying pump and the oxidizer supplying pump. A thrust controlling valve(160) controls the quantity of oxidizer supplied to the gas generating unit. An oxidizer bypass tube(170) is diverged from the gas generating unit of the thrust controlling valve. A mixing ratio stabilizer controls the fuel supplied from the gas generating unit according to the pressure of the oxidizer supplied to the oxidizer bypass tube.