Abstract: According to one embodiment, there is provided a propulsion apparatus of liquid propellant rocket engine. The propulsion apparatus of liquid propellant rocket engine, the propulsion apparatus including: a body in which liquid propellant flows; an injector core located inside the body; at least one outlet connected to the injector core to discharge combustion gas; and an injector for discharging the liquid propellant flowing into the body, wherein the injector is located in an area adjacent to the outlet, wherein the liquid propellant moves between a frame of the body and a frame of the injector core.

Abstract: The invention relates to the field of automatic equipment and, in particular, to devices for chemical ignition of liquid rocket engine propellant components. The ampoule comprises a body, diaphragm units mounted at the body inlet and outlet, each of which is made as a piston made as a single part with a diaphragm. The peripheral part of the diaphragm is fixed in an air-tight manner to the body under a guide element in which the body is mounted. The piston has a stem extending into a guide bush. Furthermore, a device for filling the ampoule with fuel is located in a partition of the body inside the ampoule. A guaranteed cutting of the diaphragm along the entire perimeter and reproduction of hydraulic characteristics for the flow part of the ampoule are achieved in this ampoule design.