| 摘要 |
<p>The invention concerns an aircraft comprising a fuselage (30) extending along a main longitudinal axis (AA), two wings (10, 20) positioned on either side of the fuselage, two propulsion units (11, 21), each fixed respectively to one wing, each propulsion unit being configured to produce thrust in a plane substantially parallel to the longitudinal axis, and a static balancing unit (31) fixed in the vicinity of one end of the fuselage and configured to produce thrust in a direction substantially orthogonal to the longitudinal axis, said aircraft being characterised in that each wing (11, 21) is rotatably mounted about a transverse axis (BB) between an aerodynamic flight position in which the wing extends in a plane substantially parallel to the longitudinal axis and a static flight position in which the wing extends in a plane substantially perpendicular to the longitudinal axis. Application to the production of unmanned aircraft.</p> |
