A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; 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,
A pitch stabilizer with box configuration suitable for providing stability to a rotorcraft comprising a vertical mid-plane and a fuselage; 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 upper pitch stabilizing means, lower pitch stabilizing means and a wing tip element.
대표청구항▼
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
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. 2. The rotorcraft according to claim 1, wherein the pitch stabilizer further comprises: a first horizontal plane which passes through an intersection of the upper longest airfoil and the upper leading edge,a first projection of a segment of the upper leading edge extending from the upper longest airfoil to the upper outer airfoil over the first horizontal plane,a first vertical plane, perpendicular to the vertical mid-plane, which passes through the intersection of the upper longest airfoil and the upper leading edge,wherein an upper leading acute angle α1, ranging between 2 degrees and 45 degrees, is formed between the first projection and the first vertical plane. 3. The rotorcraft according to claim 2, wherein the pitch stabilizer further comprises: a second horizontal plane which passes through an intersection of the upper longest airfoil and the upper trailing edge,a second projection of a segment of the upper trailing edge extending from the upper longest airfoil to the upper outer airfoil over the second horizontal plane,a second vertical plane, perpendicular to the vertical mid-plane, which passes through the intersection of the upper longest airfoil and the upper trailing edge,wherein an upper trailing acute angle α3, ranging between 2 degrees and 45 degrees, is formed between the second projection and the second vertical plane. 4. The rotorcraft according to claim 3, wherein the pitch stabilizer further comprises: a third horizontal plane which passes through an intersection of the lower longest airfoil and the lower leading edge,a third projection of the segment of the lower leading edge extending from the lower longest airfoil to the lower outer airfoil over the third horizontal plane,a third vertical plane, perpendicular to the vertical mid-plane, which passes through the intersection of the lower longest airfoil and the lower leading edge,wherein a lower leading acute angle α2, ranging between 2 degrees and 45 degrees, is formed between the third projection and the third vertical plane. 5. The rotorcraft according to claim 4, wherein the pitch stabilizer further comprises: a fourth horizontal plane which passes through an intersection of the lower longest airfoil and the lower trailing edge,a fourth projection of the segment of the lower trailing edge extending from the lower longest airfoil to the lower outer airfoil over the fourth horizontal plane,a fourth vertical plane, perpendicular to the vertical mid-plane, which passes through the intersection of the lower longest airfoil and the lower trailing edge,wherein a lower trailing acute angle α4, ranging between 2 degrees and 45 degrees, is formed between the fourth projection and the fourth vertical plane. 6. The rotorcraft according to claim 5, wherein the pitch stabilizer further comprises: a fifth vertical plane, perpendicular to the vertical mid-plane, which passes through an intersection of an upper quarter chord line of the upper pitch stabilizing means and the upper inner airfoil,a fifth projection of the upper quarter chord line of the upper pitch stabilizing means over the fifth vertical plane,a fifth horizontal plane perpendicular to the vertical mid-plane, extending in a longitudinal direction and which passes through the intersection of the upper inner airfoil and the upper quarter chord line of the upper pitch stabilizing means,wherein a superior acute angle β1, ranging between 2 degrees and 45 degrees, is formed between the fifth projection and the fifth horizontal plane. 7. The rotorcraft according to claim 6, wherein the pitch stabilizer further comprises: a sixth vertical plane, perpendicular to the vertical mid-plane, which passes through an intersection of the lower quarter chord line of the lower pitch stabilizing means and the lower inner airfoil,a sixth projection of the lower quarter chord line of the lower pitch stabilizing means over the sixth vertical plane,a sixth horizontal plane perpendicular to the vertical mid-plane, extending in a longitudinal direction and which passes through the intersection of the lower inner airfoil and the lower quarter chord line of the lower pitch stabilizing means,wherein an inferior acute angle β2, ranging between 2 degrees and 45 degrees, is formed between the sixth projection and the sixth horizontal plane. 8. The rotorcraft according to claim 1, wherein each wing tip element comprises at least three sections, a first section, directly connected to an upper edge airfoil, whose quarter chord line is formed by one or more circular arcs; a second section, directly connected to the lower outer airfoil, whose quarter chord line is also formed by one or more circular arcs; and a third section whose quarter chord line is a straight line tangent to the quarter chord lines of the first and the second sections, said third section having a chord whose length is equal to or smaller than a predetermined reference chord of the one or two upper pitch stabilizing means. 9. The rotorcraft of claim 8, wherein the quarter chord line of the first section and the quarter chord line of the second section are each made by two circular arcs tangent to one another, the radii of said arcs being comprised between 0.01 and 4 times the predetermined reference chord of the one or two upper pitch stabilizing means. 10. The rotorcraft according to claim 1, wherein the upper longest airfoil is the upper inner airfoil and the lower longest airfoil is the lower inner airfoil. 11. The rotorcraft according to claim 1, wherein the top mount comprises active means suitable for remotely controlling the rotation of the rotational shaft.
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