Rotary wing aircraft with an asymmetrical front section
A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region and that comprises a fuselage with a front section and a rear section, wherein the rear section extends between the front section and the aft region, the rotary wing aircraft comprising: a propeller that is rotatably mounted at the rear section in the aft region, a main rotor that is rotatably mounted at the front section, and a source of asymmetry that is connected to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in direction of the associated roll axis, wherein the source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash.
1. A rotary wing aircraft that extends along an associated roll axis from a nose region to an aft region, the rotary wing aircraft comprising:
a fuselage with a front section and a rear section, wherein the front section forms a cabin for passengers and/or cargo and comprises a port side wall and a starboard side wall, the front section extending from the nose region to a transition area and the rear section extending from the transition area to the aft region,
a pusher propeller that is rotatably mounted to the rear section,
a main rotor that is rotatably mounted at the front section, and
at least one source of asymmetry that is connected in the direction of the associated roll axis between the nose region and the main rotor to the front section such that the front section comprises at least in sections an asymmetrical cross-sectional profile in the direction of the associated roll axis, wherein the at least one source of asymmetry is configured to generate sideward thrust for main rotor anti-torque from main rotor downwash, wherein the at least one source of asymmetry comprises an asymmetrically shaped upper deck of the rotary wing aircraft, wherein the asymmetrically shaped upper deck comprises an asymmetrically shaped upper starboard side wall extension, if the main rotor rotates in counterclockwise direction, for deviating main rotor downwash from the starboard side wall side toward the port side wall side of the fuselage, and wherein the asymmetrically shaped upper deck comprises an asymmetrically shaped upper port side wall extension, if the main rotor rotates in clockwise direction, for deviating main rotor downwash from the port side wall side toward the starboard side wall side of the fuselage.
2. The rotary wing aircraft of claim 1 ,
wherein the at least one source of asymmetry comprises a plate-shaped protrusion of the fuselage.
3. The rotary wing aircraft of claim 2 ,
wherein the plate-shaped protrusion forms an accessible step.
4. The rotary wing aircraft of claim 2 ,
wherein the plate-shaped protrusion is integrally formed with the fuselage.
5. The rotary wing aircraft of claim 1 ,
wherein the at least one source of asymmetry comprises an asymmetrically shaped upper deck cowling of the rotary wing aircraft.
6. The rotary wing aircraft of claim 1 ,
wherein the at least one source of asymmetry comprises a deflectable flap.
7. The rotary wing aircraft of claim 1 , further comprising an uncovered propeller drive shaft configured to create a Magnus effect upon rotation in main rotor downwash.
8. The rotary wing aircraft of claim 7 ,
wherein the uncovered propeller drive shaft extends coupling- and bearing-free between the front section and the push propeller.
9. The rotary wing aircraft of claim 7 ,
wherein the uncovered propeller drive shaft is a cylinder shaft or a conical shaft.
10. The rotary wing aircraft of claim 1 , which is embodied as a compound helicopter, wherein the main rotor forms a single rotor plane.