| 主权项 |
1. A rotorcraft comprising a vertical mid-plane, a fuselage, a tailboom, a fin and a pitch stabilizer, wherein the pitch stabilizer has box configuration suitable for providing stability to the rotorcraft;
the pitch stabilizer comprising one or two pitch stabilizing assemblies, with no more than one pitch stabilizing assembly on each side of the vertical mid-plane, wherein each pitch stabilizing assembly comprises:
one anhedral upper pitch stabilizing means extending transversally in span from an upper inner airfoil to an upper outer airfoil; and extending longitudinally in chord from an upper leading edge to an upper trailing edge; a chord variation in span being, between an upper longest airfoil and the upper outer airfoil, a tapered variation, with the chord decreasing from the upper longest airfoil to the upper outer airfoil,one dihedral lower pitch stabilizing means extending transversally in span from a lower inner airfoil to a lower outer airfoil, and extending longitudinally in chord from a lower leading edge to a lower trailing edge; a chord variation in span being, between a lower longest airfoil and the lower outer airfoil, a tapered variation with the chord decreasing from the lower longest airfoil to the lower outer airfoil,one wing tip element extending in elevation between a corresponding upper outer airfoil and a corresponding lower outer airfoil, wherein, for each pitch stabilizing assembly:
the upper pitch stabilizing means are forwardly offset in a longitudinal direction from the lower pitch stabilizing means by a longitudinal distance of between 0.5 and 3 times a mean chord of the upper pitch stabilizing means,the upper pitch stabilizing means are upwardly offset in an elevation direction from the lower pitch stabilizing means by a vertical distance of between 0.5 and 3 times the mean chord of the upper pitch stabilizing means,the distance between the vertical mid-plane and a point of the pitch stabilizer furthest from the vertical mid-plane is comprised between 0.5 times and once a width of the fuselage, wherein each upper pitch stabilizing means comprise:
an upper inner structural frame,an upper surface rigidly joined to the upper inner structural frame and located around said upper inner structural frame,and upper connecting means in turn comprising:an upper bracket in each upper pitch stabilizing means, rigidly mounted on the upper inner structural frame, and,a rotational shaft, rigidly attached to the upper bracket and suitable for rotating around a top mount rigidly connected to the tailboom, and in that each lower pitch stabilizing means comprise:
a lower inner structural frame,a lower surface rigidly joined to the lower inner structural frame and located around said upper inner structural frame, and lower connecting means in turn comprising:
a lower bracket in each lower pitch stabilizing means, rigidly mounted on the lower inner structural frame, each lower bracket comprising a screw, and,a lower mount comprising, at each side of the vertical mid-plane, at least two inserts, so that the screw of each lower bracket can alternatively be inserted in one of the at least two inserts of the corresponding side of the vertical mid-plane, thus allowing the rotation of the pitch stabilizer around the rotational shaft. |
