Patent ID: 8647062

Claim:
A method for improving performance of an aircraft comprising at least one engine provided at least with one propeller without fairing ( 1 ), the propeller ( 1 ) comprising a plurality of blades (B) evenly distributed around a rotation axis (Ox) and able to rotate in a plane of rotation orthogonal to the rotation axis (Ox), with each one of the blades (B) being associated a blade setting angle (β) formed by the chord (E) of a section (S) of the blade (B) corresponding to a determined distance (R) from the rotation axis and the plane of rotation, each one of the blades (B) being submitted to a torsion aerodynamic moment (M), the method comprising: preliminarily determining for a desired thrust value of the propeller ( 1 ), a constant reference control torsion moment (Mc), intended to be applied on each one of the blades (B); and automatically and independently slaving, the blade setting angles (β) respectively associated with the blades (B), to the determined reference control moment (Mc), such that the torsion aerodynamic moments (M) applied on the blades (B) stay substantially equal to the reference control moment (Mc) whatever the angular position (θ) of the latter in the plane of rotation.