US 12,735,177 B2Granted

Helicopter

AssigneeTusas- Turk Havacilik Ve Uzay Sanayii Anonim Sirketi

InventorsHulusi Ali Kasap, Ahmet Alper Ezertas, Baris Can, Mehmet Cemil Kazanbas, Ahmet Alperen Gundogan

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Abstract

A helicopter has a body exposed to air flow, at least one wing provided on the body, extending outward from the body and enabling ammunition and similar payloads to be placed thereto, a rotor generating the aerodynamic lift and/or thrust required for the body to take off, a tail provided on the body, extending outward from the body and providing balance during the movement of the body.

Claims8

Dependent claims

A helicopter (1) comprising:

a body (2) exposed to air flow,
at least one wing (3) provided on the body (2), extending outward from the body (2),
a rotor (R) generating the aerodynamic lift and/or thrust required for the body (2) to take off,
a tail (4) provided on the body (2), extending outward from the body (2) and providing balance during the movement of the body (2),
a root region (301) on the wing (3) extending from the body (2) so as to form a dihedral angle,
a tip region (302) on the wing (3) extending from the root region (301) so as to form an anhedral angle with the body (2),
a bending region (303) between the root region (301) and the tip region (302) on the wing (3), connecting the root region (301) and the tip region (302) to each other, the bending region (303) having an angularly upside-down V-shape and being positioned at about 42% of a wingspan measured from the root region (301),
wherein the wing (3) is configured to support external payloads thereon and is produced so as to have a different profile cross-section for each of the root region (301), tip region (302) and the bending region (303);
wherein the wing (3) has a profile cross-section along a hump line (K), which is the line connecting all midpoints between the upper and lower non-symmetrical surfaces along the chord of the wing profile, on the wing (3) with a hump ratio, which is the ratio between the hump line's (K) maximum vertical deviation to the chord line and the chord length, of the root region (301) being greater than the hump ratio of the bending region (303) and a hump ratio of the tip region (302) being greater than the hump ratio of the bending region (303);
and
wherein the upside-down V-shaped wing configuration improves aerodynamic interaction of the wing (3) with rotor (R) wake flow to provide enhanced hovering performance, and provides control and enhanced stability in aerodynamic interaction of ammunition with a horizontal tail (6) by narrowing a low-pressure wake flow region created behind the wing (3).

8 more elements

Dependencies are inferred from the claim text.

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Abstract

A helicopter (1) comprising:

a body (2) exposed to air flow,
at least one wing (3) provided on the body (2), extending outward from the body (2),
a rotor (R) generating the aerodynamic lift and/or thrust required for the body (2) to take off,
a tail (4) provided on the body (2), extending outward from the body (2) and providing balance during the movement of the body (2),
a root region (301) on the wing (3) extending from the body (2) so as to form a dihedral angle,
a tip region (302) on the wing (3) extending from the root region (301) so as to form an anhedral angle with the body (2),
a bending region (303) between the root region (301) and the tip region (302) on the wing (3), connecting the root region (301) and the tip region (302) to each other, the bending region (303) having an angularly upside-down V-shape and being positioned at about 42% of a wingspan measured from the root region (301),
wherein the wing (3) is configured to support external payloads thereon and is produced so as to have a different profile cross-section for each of the root region (301), tip region (302) and the bending region (303);
wherein the wing (3) has a profile cross-section along a hump line (K), which is the line connecting all midpoints between the upper and lower non-symmetrical surfaces along the chord of the wing profile, on the wing (3) with a hump ratio, which is the ratio between the hump line's (K) maximum vertical deviation to the chord line and the chord length, of the root region (301) being greater than the hump ratio of the bending region (303) and a hump ratio of the tip region (302) being greater than the hump ratio of the bending region (303);
and
wherein the upside-down V-shaped wing configuration improves aerodynamic interaction of the wing (3) with rotor (R) wake flow to provide enhanced hovering performance, and provides control and enhanced stability in aerodynamic interaction of ammunition with a horizontal tail (6) by narrowing a low-pressure wake flow region created behind the wing (3).

8 more elements