Aircraft

Abstract

The invention relates to an aircraft designed as a compound helicopter with an aircraft fuselage, a main rotor arranged on the aircraft fuselage, and cyclogyro rotors which protrude laterally from the aircraft fuselage and which comprise an outer end surface. An improved torque compensation is achieved in that the cyclogyro rotors are connected to the aircraft fuselage by means of a suspension device which holds the cyclogyro rotors at the outer border of the rotors, and each cyclogyro rotor can be controlled individually and independently of the other. A torque compensation function of the main rotor can be carried out by the cyclogyro rotors.

Claims

1. An aircraft comprising: a compound helicopter with an aircraft fuselage; a main helicopter rotor arranged on the aircraft fuselage; and cyclogyro rotors which protrude transversely to an axis of the main helicopter rotor from the aircraft fuselage and which comprise an outer end surface wherein the cyclogyro rotors are connected to the aircraft fuselage by a suspension device that holds the cyclogyro rotors at an outer border of the cyclogyro rotors; each cyclogyro rotor are configured to be controlled individually and independently; and the cyclogyro rotors are configured to carry out a torque compensation function of the main helicopter rotor.

2. The aircraft according to claim 1, wherein the suspension device comprises wings configured to generate lift in forward flight.

3. The aircraft according to claim 1, wherein the suspension device is arranged above the cyclogyro rotors.

4. The aircraft according to claim 1, wherein the suspension device has a recess directly above the cyclogyro rotors.

5. The aircraft according to claim 1, wherein the cyclogyro rotors each have at least one offset adjustment device that is arranged in an outer border region of the cyclogyro rotors.

6. The aircraft according to claim 1, wherein the cyclogyro rotors smoothly transition into the aircraft fuselage.

7. The aircraft according to claim 1, wherein the cyclogyro rotors are connected to a drive of the main helicopter rotor by a gear.

8. The aircraft according to claim 1, wherein the cyclogyro rotors have a drive that is independent of the main helicopter rotor, wherein said drive is electrical, hydraulic, or is implemented as an individual drive unit.

9. The aircraft according to claim 1, further comprising a horizontal stabilizer and a vertical stabilizer each configured to stabilize the aircraft.

10. The aircraft according to claim 1, wherein the cyclogyro rotors are arranged below the main helicopter rotor.

11. The aircraft according to claim 1, wherein the cyclogyro rotors can are configured to be adjusted between a first position in which thrust is generated downwards and a second position in which the thrust is generated backwards.

12. The aircraft according to claim 1, wherein the cyclogyro rotors each have a length in an axial direction that substantially corresponds to a diameter of the cyclogyro rotors and wherein the length preferably lies between 80% and 120% of the diameter.

13. The aircraft according to claim 1, wherein the aircraft does not have any tail rotor.

Description

BRIEF DESCRIPTION OF THE FIGURES

(1) The invention will now be described in detail by means of FIGS. 1 to 8, wherein:

(2) FIG. 1 shows a compound helicopter according to the invention in a diagonal view from above;

(3) FIG. 2 shows the helicopter of FIG. 1 in a view from the front;

(4) FIG. 3 shows the helicopter of FIG. 1 in a lateral view;

(5) FIG. 4 shows the helicopter of FIG. 1 in a plan view;

(6) FIG. 5 shows a cyclogyro rotor in a diagonal view;

(7) FIG. 6 shows the cyclogyro rotor in a lateral view;

(8) FIG. 7 shows the cyclogyro rotor in a view from the front; and

(9) FIG. 8 shows an offset adjustment device in detail.

DETAILED DESCRIPTION OF THE INVENTION

(10) FIG. 1 shows an aircraft according to the invention, namely a compound helicopter, in a diagonal view from above, consisting of the aircraft fuselage 1, the main rotor 2, the laterally arranged cyclogyro rotors 3 and 3, the suspension 4 and 4 of the cyclogyro rotors, the outer mounting or bearing 5, and the outer offset adjustment device 11, and the horizontal and vertical stabilizer 6, 6, 7, 7, and the recess 20 in the suspension 4 and 4.

(11) FIG. 2 shows the compound helicopter according to the invention in a front view, with the two laterally arranged cyclogyro rotors 3 and 3, their suspension 4 and 4, wherein the suspension 4 and 4 is also designed as a wing or airfoil or as a component having the function of a wing or airfoil. In the central region there is provided a recess 20 which facilitates a passage of air downwards. The suspension 4, 4 is fixed on the one hand at the aircraft fuselage 1 and on the other hand at the outside of the cyclogyro rotors 3, 3 and holds them.

(12) An offset adjustment device 11 and 11 for the adjustment of the rotor blades 9 is arranged at the outside of the cyclogyro rotors 3, 3, wherein the two offset adjustment devices facing the aircraft fuselage 1 of the helicopter are not visible. Thereby it is possible to perform the cyclic adjustment of the rotor blades 9 from two sides and to provide the drive of the rotor 3, 3 from the side facing the aircraft fuselage 1 of the helicopter. It is provided that the cyclogyro rotors 3, 3 have a length in the axial direction (e.g., a distance from the aircraft fuselage 1 to the outer border) which corresponds approximately to the diameter of the cyclogyro rotors 3, 3 and preferably lies between 80% and 120% of the diameter.

(13) FIG. 3 shows the compound helicopter according to the invention in a lateral view, with the laterally arranged cyclogyro rotor 3, its suspension 4, wherein the suspension can also be implemented as a wing or as a component having the function of a wing, the outer rotor mounting or bearing 5, and the outer offset adjustment device 11, and the vertical stabilizer 6.

(14) From FIG. 4 there becomes evident in particular the horizontal and vertical stabilizer 6, 6, 7, 7.

(15) FIG. 5 shows the right-hand side cyclogyro rotor 3 of FIG. 2 in a diagonal view, consisting substantially of the rotor shaft 10, the rotor blades 9 (preferably three to six), the two rotor disks 8 and 8 with integrated rotor blade bearing or mounting, the lateral offset adjustment device 11 facing away from the helicopter aircraft fuselage, for influencing the cyclic pitch angle of the rotor blades and the direction of the thrust vector 12 which can be controlled in a plane 15 perpendicular to the axis of rotation 10 of the rotor into any direction and any size, if the cyclogyro rotor 3 is kept in rotation with a corresponding speed according to the rotational direction 14.

(16) FIG. 6 shows the cyclogyro rotor 3 in a lateral view, wherein by the angle the direction 13 of the thrust vector 12 is indicated and by the direction of rotation 14 of the cyclogyro rotor is indicated.

(17) FIG. 7 shows the right-hand side cyclogyro rotor 3 of FIG. 2 in a lateral view, consisting substantially of the two rotor disks 8 and 8, the rotor shaft 10, the rotor blades 9 (preferably 3 to 6), the lateral offset adjustment device 11 facing away from the aircraft fuselage 1 of the helicopter, and the offset unit 19 facing the aircraft fuselage 1 of the helicopter, for influencing the cyclic pitch angle of the rotor blades and the direction of the thrust vector.

(18) FIG. 8 shows the cyclic rotor blade setting devices 16 which are connected in the rotor disks 8 to the offset adjustment device 11. By displacing the central offset point 17 within a circular area 18, in accordance with the distance and the direction of the offset point 17 from the axis of rotation 10 of the rotor the size of the thrust vector and the direction of the thrust vector will be defined.