SOLID-PROPELLANT ROCKET ENGINE START SYSTEM AND PRESSURE INTAKE OF SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2011 - IPC F02K9/95 F02K9/96 

FIELD: engines and pumps.

SUBSTANCE: solid-propellant rocket engine start system includes pyro cartridges installed in rocket engine housing, igniter and augmentor tube with igniter attachment thread. Igniter is installed on thread of augmentor tube by means of the head having a connection pipe which joins the above thread. The sleeve some part of inner channel of which has the diameter exceeding outer diameter of connection pipe is installed outside augmentor tube. The other invention of the group refers to pressure intake of solid-propellant rocket engine, which includes holes for telemetric measurement system, which are made in the housing of rocket engine and have the channels gas-connected to inner cavity of rocket engine housing, and the screen covering these channels. Rocket engine housing and sleeve edge are equipped with a step providing the gap between rocket engine housing and sleeve. Screen is made in the form of hollow cylinder installed coaxially to sleeve and covering the gap. Gap together with screen forms the annular header to which channels of telemetric measurement system are led.

EFFECT: inventions allow improving the reliability of start system and pressure intake of solid-propellant rocket engine, simplifying their manufacturing technique and reducing weight and overall dimensions.

9 cl, 5 dwg