DOUBLE-DUTY SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/92 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises housing 1, sustained mode central nozzle 2, second mode nozzle unit 3 aligned with the former and arranged to axially move inside housing 1 and fixed by locking device 5. Note here said unit 3 represents cylindrical gas duct 6 with OD equal to critical cross section of sustained mode nozzle 2, face of gas duct 6 accommodates bottom 7 furnished with bar 8 crossing aforesaid critical cross section of nozzle 2, while bottom 7 and gas duct 6 have several rows of radial 9 and/or inclined (10) orifices. Nozzle unit 3 is arranged on front bottom of housing 1 with the help of guide device 4. Cross section area of rod 8 equals that of the wall of gas duct 6. Total flow passage area of radial 9 and inclined 10 orifices of said nozzle unit 3 equals the area of critical cross section of sustained mode nozzle 2. Bottom 7 of nozzle unit 3 features elongated conical or stepped-cylindrical shape, while bottom OD and, thence, ID feature variable length to allow the area of inner flow passage section of said section of bottom 7 to equal total flow passage area of radial 9 and inclined 10 orifices arranged further streamwise. Guide device 4 represents telescopically arranged cylinders 11. One or several cylinders 11 (PA, PB) of said guide device 4 make hydraulic brake. Note that the space above said cylinders is filled with fluid 14, while din channels 15 are arranged in said cylinders 11. Nozzle unit 3 is furnished with restricting ledge 16 arranged on outer cylindrical surface of gas duct 6 nearby its inlet part 17.

EFFECT: reduced weight and overall dimensions.

7 cl, 4 dwg