This invention discloses a self-feeding
piston pump for rockets, relating to the field of
aerospace liquid
rocket engine technology; it includes an integrated rotor
assembly, a
stator upper cover, a
stator housing, and a
stator lower cover; the rotor
assembly integrates the rotor housing, differential
piston, guide pin, output shaft, upper and lower bearings, and upper and lower
rotary valve cores, which are locked together with fastening screws; the number of cylinders is 2-12, preferably 4 in this embodiment; the stator
assembly is sealed and fixed to form a stationary housing, and a sealing valve sleeve is provided corresponding to the
rotary valve core, with a crescent-shaped gas distribution groove inside the sealing valve sleeve; the
rotary valve core achieves gas distribution through a venting channel that cooperates with the rotor venting hole; the output shaft is inserted into the upper rotary valve core. The rotor assembly is fixed in a
blind hole, with upper and lower bearings installed at the upper and lower ends. The stator bearing housings are respectively located on the side of the upper stator cover near the output shaft through hole and on the side of the lower stator cover near the end face. The
piston is driven by the high-pressure gas in the
combustion chamber to reciprocate and deliver
propellant. The motor assists in starting and generating
electricity in a
steady state. There is no upper limit to the pressure on the
supply side of the
combustion chamber. The upper pressure limit is determined only by the material strength of the
combustion chamber and the pump body. It is preferentially adapted to 450bar~1000bar and
detonation combustion conditions. It has the advantages of simple structure, high rotational accuracy, no upper limit to supply pressure, and high reliability. It is suitable for high-pressure
propellant supply for liquid
rocket engines.