Thrust orienting nozzle
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United States of America Patent
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Dec 15, 2009
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N/A
app pub date -
Jun 29, 2006
filing date -
Jun 30, 2005
priority date (Note) -
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Abstract
The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles.The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.
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