FIELD: rocket and space technology.
SUBSTANCE: invention relates to the field of rocket and space technology, namely to propulsion systems (PS) of spacecraft. The control unit contains fuel tanks of fuel and oxidizer containing self-igniting fuel components, a gas generator made with the possibility of burning a mixture of fuel and oxidizer to form an oxidizing gas, a main combustion chamber made with the possibility of burning a mixture of fuel and oxidizer, a turbopump unit including a turbine rotated by a stream of oxidizing gas coming from a gas generator, oxidizer pumps and fuel driven by the rotation of the turbine. Fuel and oxidizer pumps are designed with the possibility of the supply of components to the gas generator and the main combustion chamber. The control unit contains an additional combustion chamber designed to burn a mixture of fuel and oxidizing gas, and the fuel is supplied to the additional combustion chamber by a fuel pump, and the oxidizing gas is supplied to the additional combustion chamber from the gas generator after the turbine is rotated.
EFFECT: increase in the specific impulse of the engine is achieved due to a more complete use of fuel energy, ensuring the possibility of multiple engine starts, as well as ensuring the possibility of functioning in a wide range of energy intensities.
5 cl, 1 dwg
