Patent ID: 6418710
Filing Date: 2002-07-16
Classification: F02K

Abstract:
A nozzle for a thruster, comprising:a first fixed nozzle portion; at least a second nozzle portion in the form of a diverging ring displaceable between a retracted position in which said diverging ring surrounds the first nozzle portion and a deployed position in which said diverging ring is connected to a downstream end of the first nozzle portion; a deployment mechanism capable of causing said diverging ring to pass from said retracted position to said deployed position; actuation means for actuating the deployment mechanism; an insert disposed inside the diverging ring so as to transform a diverging section of said diverging ring into a non-diverging section, at least over the major fraction of the length of the diverging ring; mechanical link means connecting said insert to the diverging ring; and releasing means for releasing said mechanical link means when or after the diverging ring reaches said deployed position, in order to enable said insert to be expelled.