Tilted propellers for enhanced distributed propulsion control authority

1. An aircraft having a distributed propulsion system, the aircraft comprising:

a fuselage;

one or more support structures connected to the fuselage, the one or more support structures comprising a closed or ring wing and one or more spokes;

one or more engines or motors disposed within or attached to the one or more support structures or the fuselage;

the distributed propulsion system comprising two or more propellers symmetrically distributed along the one or more support structures and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation; and

the two or more propellers are configured in pairs, each pair of propellers comprising a first propeller creating a first thrust having a first horizontal force vector and a second propeller creating a second thrust having a second horizontal force vector, wherein a summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, and a first rotational axis of the first propeller and a second rotational axis of the second propeller are substantially coplanar with a vertical axis disposed between the respective pair of propellers;

wherein a movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.

2. The aircraft of claim 1 , wherein:

the first propeller and the second propeller are proximate to one another;

the first propeller and the second propeller rotate in the same direction; and

the first rotational axis has a negative tilt angle with respect to the vertical axis, the second rotational axis has a positive tilt angle with respect to the vertical axis, and the positive tilt angle and the negative tilt angle have a substantially equal magnitude.

3. The aircraft of claim 1 , wherein the first propeller has the first rotational axis within a first tangential plane, and the second propeller has the second rotational axis within a second tangential plane, wherein the first tangential plane and the second tangential plane are substantially parallel, the first propeller creates a clockwise thrust, and the second propeller creates a counterclockwise thrust.

4. The aircraft of claim 1 , wherein the first rotational axis has a negative tilt angle with respect to the vertical axis, the second rotational axis has a positive tilt angle with respect to the vertical axis, and the positive tilt angle and the negative tilt angle have a substantially equal magnitude.

5. The aircraft of claim 1 , wherein the rotation direction is clockwise for 50% of the two or more propellers and the rotation direction is counterclockwise for 50% of the two or more propellers.

6. The aircraft of claim 1 , wherein the tilted plane of rotation is tilted towards a center of gravity of the aircraft for all of the two or more propellers.

7. The aircraft of claim 6 , wherein the tilted plane of rotation is tilted towards the center of gravity of the aircraft for 50% of the two or more propellers and the tilted plane of rotation is tilted away from the center of gravity of the aircraft for 50% of the two or more propellers.

8. The aircraft of claim 6 , wherein the tilted plane of rotation is titled tangentially with respect to the center of gravity of the aircraft such that 50% of the two or more propellers create a clockwise thrust with respect to the center of gravity and 50% of the two or more propellers create a counterclockwise thrust with respect to the center of gravity.

9. The aircraft of claim 1 , wherein the two or more propellers are fixed pitch propellers.

10. The aircraft of claim 1 , wherein a summation of horizontal torque vectors created by the rotation direction of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust.

11. An aircraft having a distributed propulsion system, the aircraft comprising:

a closed wing;

a fuselage at least partially disposed within a perimeter of the closed wing;

three or more spokes connecting the fuselage to the closed wing;

one or more motors disposed within or attached to the one or more spokes or the fuselage;

the distributed propulsion system comprising two or more propellers distributed along the three or more spokes and operably connected to the one or more motors, wherein each propeller has a rotation direction within a tilted plane of rotation; and

to the two or more propellers are configured in pairs, each pair of propellers comprising a first propeller creating a first thrust having a first horizontal force vector and a second propeller creating a second thrust having a second horizontal force vector, wherein a summation of the first and second horizontal force vectors is substantially zero when the first thrust is substantially equal to the second thrust, and a first rotational axis of the first propeller and a second rotational axis of the second propeller are substantially coplanar with a vertical axis disposed between the respective pair of propellers;

wherein a movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.

12. The aircraft of claim 11 , wherein:

the first propeller and the second propeller are proximate to one another;

the first propeller and the second propeller rotate in the same direction; and

the first rotational axis has a negative tilt angle with respect to the vertical axis, the second rotational axis has a positive tilt angle with respect to the vertical axis, and the positive tilt angle and the negative tilt angle have a substantially equal magnitude.

13. The aircraft of claim 11 , wherein the first propeller has the first rotational axis within a first tangential plane, and the second propeller has the second rotational axis within a second tangential plane, wherein the first tangential plane and the second tangential plane are substantially parallel, the first propeller creates a clockwise thrust, and the second propeller creates a counterclockwise thrust.

14. The aircraft of claim 11 , the first rotational axis has a negative tilt angle with respect to the vertical axis, the second rotational axis has a positive tilt angle with respect to the vertical axis, and the positive tilt angle and the negative tilt angle have a substantially equal magnitude.

15. The aircraft of claim 11 , wherein the rotation direction is clockwise for 50% of the two or more propellers and the rotation direction is counterclockwise for 50% of the two or more propellers.

16. The aircraft of claim 11 , wherein the tilted plane of rotation is tilted towards a center of gravity of the aircraft for all of the two or more propellers.

17. The aircraft of claim 16 , wherein the tilted plane of rotation is tilted towards the center of gravity of the aircraft for 50% of the two or more propellers and the tilted plane of rotation is tilted away from the center of gravity of the aircraft for 50% of the two or more propellers.

18. The aircraft of claim 16 , wherein the tilted plane of rotation is titled tangentially with respect to the center of gravity of the aircraft such that 50% of the two or more propellers create a clockwise thrust with respect to the center of gravity and 50% of the two or more propellers create a counterclockwise thrust with respect to the center of gravity.

19. The aircraft of claim 11 , wherein the two or more propellers are fixed pitch propellers.

20. The aircraft of claim 11 , wherein a summation of horizontal torque vectors created by the rotation direction of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust.