CPC B64C 21/06 (2013.01) [B64C 1/16 (2013.01); B64D 27/20 (2013.01); B64D 29/04 (2013.01); B64D 2033/0206 (2013.01); B64D 2033/0286 (2013.01)] | 11 Claims |
1. A propulsion assembly for an aircraft, comprising:
a fuselage extending along a longitudinal axis and enclosing an inner enclosure,
at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure,
at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, and configured to homogenize and reduce the speed of the flow entering the at least one ducted engine,
at least one air intake formed on an outer wall of the fuselage, an inlet of the air intake being partly delimited by said outer wall of the fuselage, the at least one air intake being configured to ingest external air and deflect the external air towards the at least one plenum chamber,
wherein the fuselage has a substantially elliptical section comprising a major axis and a minor axis, the ratio between the major axis and the minor axis being comprised between 1 and 2.5,
wherein the plenum chamber has a parallelepiped shape comprising a width extending along the major axis, a length extending along the longitudinal axis and a height extending along the minor axis, wherein the width is comprised between 2.1E and 2.8E, the length is comprised between 1.1E and 2.5E and the height is comprised between 1.3E and 2.0E, where E is a diameter of the air inlet section of the at least one ducted engine.
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