Jet noise suppression means and thrust reverser

Claim 2

A COMBINED NOISE SUPPRESSION AND THRUST REVERSAL NOZZLE FOR AN AIRCRAFT JET PROPULSION ENGINE LOCATED IN THE REGION OF THE EXIT OF THE PROPULSIVE STREAM, THE NOZZLE HAVING A LONGITUDINAL AXIS AND THE PERIPHERY OF THE NOZZLE INCLUDING A NUMBER OF ELEMENTS, EACH OF THE ELEMENTS HAVING AN UPSTREAM AND A DOWNSTREAM END, MOUNTINGS FOR SAID ELEMENTS AT BOTH OF SAID ENDS AND A MECHANISM FOR ADJUSTING THE ELEMENTS INTO A FIRST POSITION IN WHICH THE DOWNSTREAM ENDS OF EACH OF A PAIR OF ADJACENT ELEMENTS ARE SPACED APART FROM ONE ANOTHER RELATIVE TO THE LONGITUDINAL AXIS, A SECOND POSITION IN WHICH THE DOWNSTREAM ENDS OF THE ELEMENTS ARE EQUIDISTANT FROM THE LONGITUDINAL AXIS AND A THIRD POSITION IN WHICH THE UPSTREAM ENDS OF THE ELEMENTS ARE MOVED OUTWARDLY AWAY FROM AND THE DOWNSTREAM ENDS MOVED TOWARDS THE LONGITUDINAL AXIS.

Claim 3

A NOISE SUPPRESSION NOZZLE THROUGH WHICH THE PROPULSIVE GAS STREAM OF A JET PROPULSION ENGINE IS TO BE ISSUED, THE NOZZLE HAVING A LONGITUDINAL AXIS AND INCLUDING A NUMBER OF PIVOTALLY MOUNTED ELEMENTS FORMING A PART OF THE PERIPHERY OF THE NOZZLE, EACH ELEMENT HAVING A LONGITUDINAL AXIS AND MEANS TO ADJUST THE INCLINATION OF THE LONGITUDINAL AXES OF CERTAIN OF THESE ELEMENTS IN ONE DIRECTION AND OF OTHER ELEMENTS IN THE OPPOSITE DIRECTION WITH RESPECT TO THE LONGITUDINAL AXIS OF THE NOZZLE, WITHOUT RESULTANT CHANGE OF NOZZLE OUTLET AREA, FROM A NOISE SUPPRESSION POSITION, IN WHICH THE LONGITUDINAL AXES OF THE ELEMENTS ARE INCLINED TO THE LONGITUDINAL AXIS OF THE NOZZLE IN SUCH A MANNER THAT THE CROSS-SECTIONAL SHAPE OF THE PROPULSIVE GAS STREAM LEAVING THE NOZZLE EXIT IS DEEPLY INDENTED TO FROM CORRUGATIONS, TO A RELATIVELY LESS EFFECTIVE NOISE SUPPRESSION POSITION IN WHICH THE ELEMENTS CO-OPERATE WITH THE REMAINDER OF THE PERIPHERY OF THE NOZZLE TO FORM A BOUNDARY FOR THE PROPULSIVE GAS STREAM BEFORE IT LEAVES THE DOWNSTREAM END OF THE NOZZLE AND IN WHICH POSITION, THE LONGITUDINAL AXES OF THE ELEMENTS ARE INCLINED TO THE LONGITUDINAL AXIS OF THE NOZZLE IN SUCH A MANNER THAT THE CROSS-SECTIONAL SHAPE OF THE PROPULSIVE GAS STREAM LEAVING THE NOZZLE EXIT IS INDENTED TO A REDUCED EXTENT AS COMPARED WITH THE NOISE SUPPRESSION NOZZLE POSITION.

Claim 4

A NOISE SUPPRESSION NOZZLE THROUGH WHICH THE PROPULSIVE GAS STREAM OF A JET PROPULSION ENGINE IS TO BE ISSUED, THE NOZZLE HAVING A LONGITUDINAL AXIS AND INCLUDING A NUMBER OF PIVOTALLY MOUNTED ELEMENTS FORMING A PART OF THE PERIPHERY OF THE NOZZLE, EACH ELEMENT HAVING A LONGITUDINAL AXIS AND MEANS TO ADJUST THE INCLINATION OF THE LONGITUDINAL AXES OF CERTAIN OF THESE ELEMENTS IN ONE DIRECTION AND OF OTHER ELEMENTS IN THE OPPOSITE DIRECTION WITH RESPECT TO THE LONGITUDINAL AXIS OF THE NOZZLE, WITHOUT RESULTANT CHANGE OF NOZZLE OUTLET AREA, FROM A NOISE SUPPRESSION POSITION, IN WHICH THE LONGITUDINAL AXES OF THE ELEMENTS ARE INCLINED TO THE LONGITUDINAL AXIS OF THE NOZZLE IN SUCH A MANNER THAT THE CROSS-SECTIONAL SHAPE OF THE PROPULSIVE GAS STREAM LEAVING THE NOZZLE EXIT IS DEEPLY INDENTED TO FROM CORRUGATIONS, TO A RELATIVELY LESS EFFECTIVE NOISE SUPPRESSION POSITION IN WHICH THE ELEMENTS CO-OPERATE WITH THE REMAINDER OF THE PERIPHERY OF THE NOZZLE TO FORM A BOUNDARY FOR THE PROPULSIVE GAS STREAM BEFORE IT LEAVES THE DOWNSTREAM END OF THE NOZZLE AND IN WHICH POSITION, THE LONGITUDINAL AXES OF THE ELEMENTS ARE INCLINED TO THE LONGITUDINAL AXIS OF THE NOZZLE IN SUCH A MANNER THAT THE CROSS-SECTIONAL SHAPE OF THE PROPULSIVE GAS STREAM LEAVING THE NOZZLE EXIT IS INDENTED TO A REDUCED EXTENT AS COMPARED WITH THE NOISE SUPPRESSION NOZZLE POSITION.