SOLID-PROPELLANT ROCKET ENGINE START SYSTEM AND PRESSURE INTAKE OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2013 - IPC F02K9/95 F02K9/96 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine start system includes pyro cartridges installed in the housing cover plate, augmentor tube, igniter and its attachment assembly. The igniter attachment assembly includes a shell, a ring and longitudinal screws passing through the ring and shell walls and screwed into the threaded seats on the cover plate. Open end face of the shell contacts the igniter, and the ring presses the igniter flange to the open shell end face. The augmenter tube passes through the axial hole at the shell bottom, which is equal to its diameter. Pressure intake of solid-propellant rocket engine is made around the augmenter tube of the start system and includes seats of the telemetric measurement system, which are made in the cover plate of the rocket engine housing and have the channels gas-connected to inner cavity of solid-propellant rocket engine housing, and the screen covering these channels and forming the bottom of the start system shell. On the side of outer surface of the shell bottom there are annular perforated projections dividing the volume between the shell and the heat-insulating coating into several coaxial headers. Slots are made in the heat insulating coating between the igniter attachment screws.

EFFECT: inventions allow reducing the weight and dimensions of the start system and pressure intake, improving reliability and simplifying the manufacturing procedure.

8 cl, 5 dwg