An aircraft includes at least three drive units, each of which has a first rotor and a first, rotary speed-controlled electrical motor, suitable for driving the first rotor during operation of the aircraft. Each of the drive units has at least a second rotor and at least one second, rotary speed-controlled electrical motor, suitable for driving the second rotor during operation of the aircraft in a rotational direction that is opposite to the rotational direction of the first rotor of each drive unit. Autonomous means for controlling the location and position of the aircraft are also provided.
1. An aircraft, comprising:
autonomous attitude and position control provided by at least three drive units, each of said drive units having:
a first rotor;
a first rotary speed-controlled electric motor configured for driving said first rotor in a rotation direction during operation of the aircraft;
at least one second rotor;
at least one second rotary speed-controlled electric motor configured for driving said at least one second rotor during operation of the aircraft in a rotation direction opposite to said rotation of said first rotor of said respective drive unit;
said first rotary speed-controlled electric motor and said at least one second rotary speed-controlled electric motor having rotary speeds being variable on an individual basis; and
a support for said drive units, said support including a number of supporting arms extending radially outward from and secured only to a central base body without the drive units beingsecured to each other, at least one of said drive units being fitted to each respective one of said supporting arms.
2. The aircraft according to claim 1 , wherein said first rotors of at least two of said drive units have a common rotation plane.
3. The aircraft according to claim 1 , wherein said first rotors of all of said drive units have a common rotation plane.
4. The aircraft according to claim 1 , wherein said second rotors of at least two of said drive units have a common rotation plane.
5. The aircraft according to claim 1 , wherein said second rotators of all of said drive units have a common rotation plane.
6. The aircraft according to claim 1 , wherein:
said first rotors of at least two of said drive units have a common rotation plane;
said second rotors of at least two of said drive units have a common rotation plane;
said rotation planes of said first and second rotors are oriented substantially parallel to one another.
7. The aircraft according to claim 1 , wherein said first and second rotors of at least one of said drive units are separated from one another in axial direction.
8. The aircraft according to claim 1 , wherein said first and second rotors of each of said at least three drive units are separated from one another in axial direction.
9. The aircraft according to claim 1 , wherein said first and second rotors of at least one of said drive units are disposed coaxially.
10. The aircraft according to claim 1 , wherein said first and second rotors of each of said drive units are disposed coaxially.
11. The aircraft according to claim 1 , wherein said supporting arms are detachably fitted to said base body or are fitted to said base body by quick-release fasteners.
12. The aircraft according to claim 1 , which further comprises a collision protection device for said rotors.
13. The aircraft according to claim 1 , which further comprises a collision protection device for said rotors, said collision protection device being detachably fitted to said support or to said supporting arms.
14. The aircraft according to claim 12 , wherein said collision protection device includes at least one rotor protection ring extending along an outer circumference of the aircraft.
15. The aircraft according to claim 12 , wherein said collision protection device includes a first rotor protection ring and a second rotor protection ring extending along an outer circumference of the aircraft.
16. The aircraft according to claim 15 , wherein said rotor protection rings are oriented substantially parallel to one another.
17. The aircraft according to claim 15 , which further comprises a number of holding crossmembers interconnecting said rotor protection rings.
18. The aircraft according to claim 17 , wherein said holding crossmembers are detachably fitted to said supporting arms.
19. The aircraft according to claim 1 , which further comprises an aircraft landing frame.
20. The aircraft according to claim 1 , which further comprises an interchangeable payload module.