System for controlling speed transition and thrust vectorisation in a multiple-shaped nozzle by secondary injection

Number of patents in Portfolio can not be more than 2000

United States of America Patent

PATENT NO 11661910
APP PUB NO 20210164418A1
SERIAL NO

17048243

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Abstract

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A mixing tube with multiple shapes is provided, allowing additional injection of gas in order to keep the flow detached from the second shape in an ascent phase and to bring about, in a descent phase, a controlled detachment as a result of the change of slope between the two shapes. A propulsion nozzle for an engine of a spacecraft or aircraft is provided including such a mixing tube and a method for controlling the speed transition of the propulsion gases in such a nozzle in accordance with the altitude. Also, a method is provided for vectorising the thrust in such a nozzle by radial and asymmetrical injection of gas and a control method which prevents re-attachment of the jet to the second shape of such a propulsion nozzle for an engine of a spacecraft when it is in the take-off or landing phase.

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Patent Owner(s)

Patent OwnerAddress
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUEPARIS FRA
UNIVERSITE D'ORLEANSCHATEAU DE LA SOURCE 6 AVENUE DU PARC FLORAL ORLEANS 45100
UNIVERSITE D'EVRY-VAL D'ESSONNE23 BOULEVARD FRANÇOIS MITTERRAND EVRY 91000

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Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Chpoun, Amer Saint-Fargeau-Ponthierry, FR 1 0
Leger, Luc Saint-Pryve-Saint-Mesmin, FR 1 0
Sellam, Mohamed Paris, FR 1 0
Zmijanovic, Vladeta Orleans, FR 1 0

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