Patent ID: 7571610
Filing Date: 2009-08-11
Classification: F02K

Abstract:
1. An extendible exhaust nozzle bell for a rocket engine of an aircraft or spacecraft, comprising: a first part and a second part, wherein said first part, which has a smaller diameter than said second part, is fixedly arranged on a motor of the rocket engine and said second part is arranged to be movable with respect to the first part, such that said second part, in a front stowed position, is located to surround said first part and, in a rear operating position, is located to continue the first part; a closed volume, formed at least in part by a deformable rolling bellows arrangement, such that, when the closed volume is acted on by a gaseous fluid to enlarge the volume, said second part is structured and arranged to extend from said front stowed position into said rear operating position; and a portion of the deformable rolling bellows arrangement is connected to an external surface of said second part and to a fixed part of one of the rocket engine, the aircraft, or the spacecraft.