ROCKET ENGINE OF ROCKET-ASSISTED PROJECTILE Russian patent published in 2017 - IPC F02K9/97 F02K9/95 

FIELD: engines and pumps.

SUBSTANCE: rocket engine of rocket-assisted projectile comprises a combustion chamber with a charge of solid fuel nozzle, and the nozzle cap initiator. In the critical section of the nozzle is set breakthrough membrane. The plug includes a base and a cover fixed on the basis of a hollow cylindrical cup with perforated bottom by a membrane installed at the throat of the nozzle. At the base of the plug and the bottom of the glass made coaxial holes in which the rod is installed with the possibility of longitudinal movement. The stock has a sharpened tip from the membrane, a conical thickening of the part of the base cap, combined with the conical recess in the base and cut the flange sandwiched between the base and the plug cover. On the inside the glass rod mounted console, and between the glass and the bottom bracket mounted coil spring, covering the stem. Pyrotechnic initiator primary linkage includes an igniter placed between the cup bottom and the membrane, and at least two igniters kaplyuley-established on the basis of plugs and associated with strikers fixed to the console. Cover nozzle stub located at the outlet section of the nozzle and fastened by means of rolling with the outer side and the central portion of the lid is a hole with a diameter equal to the diameter of the tapered stem thickening. The magnitude of free volume combustion chamber defined by an algebraic expression to be protected by the present invention.

EFFECT: invention allows for reliable autonomous ignition charge of solid fuel, which is independent from the influence of powder gases and propellant pressure relief at the departure of the nozzle cap.

4 dwg, 1 tbl