SYSTEM FOR CONTROLLING SPEED TRANSITION AND THRUST VECTORISATION IN A MULTIPLE-SHAPED NOZZLE BY SECONDARY INJECTION

摘要

The invention relates to a mixing tube (1) with multiple shapes 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. The invention also relates to a propulsion nozzle (4) for an engine of a spacecraft or aircraft comprising such a mixing tube (1) and a method for controlling the speed transition of the propulsion gases in such a nozzle (4) in accordance with the altitude. Finally, the invention also relates to a method 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.