| US 7,478,778 B2 | ||
| Rocket engine having guide vanes in the nozzle of the engine | ||
| Erland Ørbekk, Gjøvik (Norway) | ||
| Assigned to Nammo Raufoss AS, Raufoss (Norway) | ||
| Appl. No. 10/572,862 PCT Filed Sep. 14, 2004, PCT No. PCT/NO2004/000272 § 371(c)(1), (2), (4) Date Sep. 05, 2006, PCT Pub. No. WO2005/028844, PCT Pub. Date Mar. 31, 2005. |
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| Claims priority of application No. 20034266 (NO), filed on Sep. 24, 2003. | ||
| Prior Publication US 2007/0152096 A1, Jul. 05, 2007 | ||
| Int. Cl. F42B 15/01 (2006.01); F42B 10/00 (2006.01); F42B 10/66 (2006.01); F02K 9/80 (2006.01); F41G 9/00 (2006.01); F02K 9/97 (2006.01) | ||
| U.S. Cl. 244—3.21 [244/3.1; 244/3.15] | 4 Claims |
| 1. A rocket engine having a plurality of guide vanes, a plurality of fixed vanes, and an engine nozzle,
wherein each of the plurality of guide vanes is mounted for turning proximate a rearmost end of one of the plurality of fixed
vanes,
wherein each of the plurality of fixed vanes is parallel to an axis of the engine nozzle and protrudes into a combustion chamber
of the engine.
|