Helicopter
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.
1 . 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 ).
2 . The helicopter ( 1 ) as claimed in claim 1 , wherein the wing ( 3 ) in which the length of a chord line (V) between the leading edge and the trailing edge of the wing ( 3 ) profile narrows from the root region ( 301 ) toward the tip region ( 302 ).
3 . The helicopter ( 1 ) as claimed in claim 1 , wherein the wing ( 3 ) is located on the body ( 2 ) below the rotor (R) so as to be aligned with an axis (E) of the rotor (R).
4 . The helicopter ( 1 ) as claimed in claim 1 , comprising at least one air intake ( 5 ) on the body ( 2 ) taking the air required for the rotor (R) to operate,
wherein a surface of the root region ( 301 ) positioned below and facing a lower surface of the air intake ( 5 ) extends parallel to the lower surface of the air intake ( 5 ), such that the wing ( 3 ) extends almost in parallel to the air intake ( 5 ) to provide enhanced aerodynamic performance.
5 . The helicopter ( 1 ) as claimed in claim 1 , comprising at least one horizontal tail ( 6 ) on the tail ( 4 ), providing balance during movement, wherein the wing ( 3 ) on the body ( 2 ) is aligned with the horizontal tail ( 6 ).
6 . The helicopter ( 1 ) as claimed in claim 1 , wherein the root region ( 301 ) has a dihedral angle between 20°-45°, and the tip region ( 302 ) has an anhedral angle between 25°-29.
7 . The helicopter ( 1 ) as claimed in claim 1 , wherein the root region ( 301 ) of the wing ( 3 ) is shorter than the tip region ( 302 ) thereof.
8 . The helicopter ( 1 ) as claimed in claim 1 , wherein the wing ( 3 ) has a tip region ( 302 ) configured for placement of payloads.