Patent ID: 9102395
Filing Date: 2015-08-11
Classification: B64C,B64D,F02K,Y02T

Abstract:
1. A propulsive system for an airplane having a jet engine and a nacelle surrounding said jet engine, wherein said nacelle has a front section between an air inlet in the front in the direction of motion of flight and a rear extremity of the front section at the rear with said nacelle having a rear section behind the rear extremity forming an extension of the front section of the nacelle, wherein said rear section is formed by first and second petals hinged relative to the front section with interior and exterior surfaces of said petals in a zero setting position each being in geometric continuity with the interior and exterior surfaces determining the aerodynamic forms of the front section; wherein the first and second petals are each hinged around an axis essentially in a plane perpendicular to a longitudinal axis of the propulsive system and of the jet engine, and are located behind the rear extremity of the front section of the nacelle so that the position of the axis relative to each of the first and second petals determines an anterior section, located in front of the axis of rotation, and determines a posterior section, located behind the axis of rotation; and wherein the system further comprises a means of controlling and driving configured to drive the first and second petals to at least one stationary operational intermediate position between a fully open position and a fully closed position and to maintain the first and second petals in the at least one stationary operational intermediate position, wherein the posterior sections of the first and second petals are spaced from the axis of the propulsive system such that a part of a jet from the jet engine is ejected between the posterior sections and another part of the jet from the jet engine is ejected by the anterior sections of the first and second petals to first and second sides and toward the front of the propulsive system.