Patent ID: 7631486
Filing Date: 2009-12-15
Classification: F02K

Abstract:
1. A thrust orienting nozzle for an aerospace vehicle, comprising: a channel configured to guide a principal propulsion gas flow downstream from at least one gas generator; a first symmetric channel configured to guide a first portion of the principal propulsion gas flow from the channel to a first half-nozzle; a second symmetric channel configured to guide a second portion of the principal propulsion gas flow from the channel to a second half-nozzle; the first half-nozzle configured to eject the first portion of the principal propulsion gas flow, the first half-nozzle including a first throat and first divergent walls downstream of the first throat, the first divergent walls including a first internal side and a first external side; the second half-nozzle configured to eject the second portion of the principal propulsion gas flow, the second half-nozzle including a second throat and second divergent walls downstream of the second throat, the second divergent walls including a second internal side and a second external side; and at least one of the following two piloting means, including a) a means of dividing the principal propulsion gas flow into each of the half-nozzles, and b) a means of orienting the thrust vector produced by each of the two half-nozzles, wherein the at least one of the two piloting means being fluid injection means downstream of the first symmetric channel and the second symmetric channel and within the first half-nozzle and the second half-nozzle.