| CPC B64C 5/02 (2013.01) [B64C 27/04 (2013.01); B64C 27/82 (2013.01); B64C 2027/8281 (2013.01)] | 15 Claims |
|
1. A helicopter comprising:
a fuselage elongated along a first longitudinal axis (X) of said helicopter and extending between a nose and a tail boom of the helicopter from which a fin projects;
a tailplane arranged at said tail boom and transversal to the tail boom;
said tailplane defining a pair of first aerodynamic surfaces generating, in use, respective first aerodynamic forces and elongated along a second axis (Y) transversal to said first axis (X);
said first and second axes (X, Y) defining a first plane (Q);
a pair of first elements transversal to said first respective aerodynamic surfaces; and
a pair of second aerodynamic surfaces generating, in use, respective second aerodynamic forces, connected to said respective first elements, and facing and spaced from said respective first aerodynamic surfaces;
each of said second aerodynamic surface comprising, in turn:
a first root end connected to said respective first element;
a first leading edge;
a first trailing edge opposite to the said first leading edge;
a first chord (C2) joining said first leading edge and said first trailing edge at said first root end parallel to said first axis (X); and
a second chord (C1) joining said first leading edge and said first trailing edge at a second free end parallel to said first axis (X);
said first and second chord (C2, C1) defining a second plane (R) tilted with respect to said first plane (Q); characterized in that each of said aerodynamic surface comprises said second free end being spaced from said tail boom and opposite to said first root end;
said second chord (C1) being defined at said second free end;
wherein each second aerodynamic surface of said pair of second aerodynamic surfaces has respective fifth chords (C) with lengths gradually decreasing proceeding from the said respective first element and towards said respective second free end and proceeding from said first chord (C2) to said second chord (C1);
wherein each said second aerodynamic surface is tapered proceeding from said first root end towards said second free end;
wherein each of said first element comprises:
a third end connected to said respective first aerodynamic surface;
a fourth end connected to said respective second aerodynamic surface and opposite to said third end;
a second leading edge;
a second trailing edge;
a third chord (D1) joining said second leading edge and second trailing edge at said third end parallel to said first axis (X);
a fourth chord (D2) joining said second leading edge and second trailing edge at said fourth end parallel to said first axis (X);
said third and fourth chord (D1, D2) defining a third plane (S);
said third plane (S) being tilted with respect to said first plane (Q) at a second non-zero angle (γ) between −15 and 15 degrees and/or being tilted with respect to a third axis (Z) orthogonal to said first plane (Q) at a third non-zero angle (β) between −30 and 30 degrees,
and also comprising:
a pair of second elements, each said second element being connected to a respective first aerodynamic surface and to said respective first element at a respective third root end, and extending on the opposite side of said respective first element with respect to said respective first aerodynamic surface, and each said second element including a fourth free end opposite to said respective third root end, a curved third leading edge, and a third trailing edge opposite to said curved third leading edge,
wherein a length of the second elements along the first axis (X) decreases from the third root end toward the fourth free end, and
wherein at least one of the second leading edge and the second trailing edge are oriented towards the nose of the helicopter in relation to the second axis (Y).
|