Deployable diverging part for a thruster
AssigneeSociete Nationale d'Etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."
InventorsBruno Perrier, Jean-Luc Sans, Laurent Collignon
Life of this patent
Estimating the term…
Abstract
A diverging ring is displaceable between a retracted position in which it surrounds a first portion of a diverging part and a deployed position in which it is connected to a downstream end of the first portion. A deployment mechanism causes the diverging ring to move from its retracted position to its deployed position under drive from an actuator. A temporary structure, or “insert”, is placed inside the diverging ring so as to transform the diverging section thereof into a non-diverging section, at least over the major portion of the length of the diverging ring, the insert being eliminatable on or after the diverging ring coming into its deployed position.
Claims21
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.
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 said first nozzle portion and a deployed position in which said first diverging ring is connected to a downstream end of said 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 said deployment mechanism;
- an insert disposed inside of said 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 said diverging ring;
- and
- link means for connecting said insert to said diverging ring, said link means being made at least in part out of a material strength that is ephemeral in the combustion gas flowing through said diverging ring, so as to be eliminated after said diverging ring has come into said deployed position.
A nozzle according to claim. 12, wherein said actuation means comprises energy storage means that is not connected to an external energy source.
A nozzle for a thruster, comprising:
- a 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 said first nozzle portion and a deployed position in which said diverging ring is connected to a downstream end of said 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 said deployment mechanism;
- an insert disposed inside of said 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 said diverging means;
- and
- a protective cover provided on an inside surface and an end surface of said insert, said protective cover being made out of a material that is ephemeral to the combustion gas flowing through said diverging ring, and said insert being made at least in part of a material of strength that is ephemeral in the combustion gas flowing through said diverging ring, so as to be eliminated after said diverging ring has come into said deployed position.
Dependencies are inferred from the claim text.