The invention discloses a self-pressurization double-component pulse working
rocket engine, and belongs to the technical field of
aerospace propulsion. A double-cylinder pneumatic
plunger pump and a
thrust chamber are organically combined into a whole, gas in a
combustion chamber is used for driving the double-cylinder
plunger pump, the sum of the action areas of the pressure, borne by an annularpiston of the
plunger pump, of a
propellant is smaller than the action area of the pressure of the gas of the
combustion chamber, and therefore the
pressure difference is generated. After an oxidizingagent pressurized by the
plunger pump is catalytically decomposed, hot gas is generated to enter the
combustion chamber to be combusted with fuel, the pressure of the
combustion chamber is increased,a
positive feedback effect is formed, the
combustion chamber works at high-
voltage pulses at low
inlet pressure, the performance of the engine can be greatly improved, the size, the structure weightand the manufacturing cost of the engine can be reduced, meanwhile, as it is required that the
inlet pressure of the
propellant is low, the amount of gas pressurized by a
propellant storage box is small, the pressure of the storage box is low, the structure weights of the storage box and a pressurization
system can be effectively reduced, and therefore the loading capacity and the use performanceof a
spacecraft are effectively improved.