Aircraft having rotor assemblies rotating in parallel planes

1. An aircraft configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode, the aircraft comprising:

an airframe including at least one straight wing;

a pod assembly coupled to the airframe;

a distributed propulsion system attached to the airframe including a first plurality of propulsion assemblies each including a nacelle and a second plurality of propulsion assemblies each including a nacelle, each of the propulsion assemblies including a rotor assembly having a plurality of rotor blades, at least one of the propulsion assemblies coupled to the straight wing, the nacelles of the first plurality of propulsion assemblies longer than the nacelles of the second plurality of propulsion assemblies; and

a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies;

wherein, in the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first horizontal plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second horizontal plane parallel to the first horizontal plane;

wherein, in the forward flight mode, each of the propulsion assemblies is configured to generate forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second vertical plane parallel to the first vertical plane; and

wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, the pod assembly remains in a generally horizontal attitude.

2. The aircraft as recited in claim 1 wherein, the airframe further comprises first and second pylons coupled to the at least one wing, the first and second pylons substantially parallel with one another and each having a middle and two ends.

3. The aircraft as recited in claim 2 wherein, the first and second pylons are positioned outboard of the pod assembly.

4. The aircraft as recited in claim 2 wherein, the pod assembly is coupled between the first and second pylons at locations proximate the middle of the first and second pylons.

5. The aircraft as recited in claim 2 wherein, each of the propulsion assemblies of the first plurality of propulsion assemblies is coupled to one of the ends of the first and second pylons.

6. The aircraft as recited in claim 1 wherein, each of the propulsion assemblies of the first plurality of propulsion assemblies is positioned at least partially outboard of the pod assembly and each of the propulsion assemblies of the second plurality of propulsion assemblies is positioned at least partially outboard of the propulsion assemblies of the first plurality of propulsion assemblies.

7. The aircraft as recited in claim 1 wherein, each of the propulsion assemblies of the second plurality of propulsion assemblies includes a landing gear having a wheel.

8. The aircraft as recited in claim 7 wherein, each of the landing gear further comprises a telescoping landing strut.

9. The aircraft as recited in claim 1 wherein, the first plurality of propulsion assemblies includes a different number of propulsion assemblies than the second plurality of propulsion assemblies.

10. The aircraft as recited in claim 1 wherein, the pod assembly is a releasable pod assembly that is configured to be coupled to and decoupled from the airframe when the airframe and the releasable pod assembly are on the ground.

11. The aircraft as recited in claim 10 wherein, the releasable pod assembly further comprises wheels configured to engage the ground.

12. The aircraft as recited in claim 1 wherein, the pod assembly is a passenger pod assembly.

13. The aircraft as recited in claim 1 wherein, the pod assembly is a cargo pod assembly.

14. The aircraft as recited in claim 1 wherein, the pod assembly is a manned pod assembly.

15. The aircraft as recited in claim 1 wherein, the pod assembly is an unmanned pod assembly.

16. The aircraft as recited in claim 1 wherein, the flight control system is operated responsive to onboard pilot flight control.

17. The aircraft as recited in claim 1 wherein, the flight control system is operated responsive to remote flight control.

18. The aircraft as recited in claim 1 wherein, the flight control system is operated responsive to autonomous flight control.

19. An aircraft configured for thrust-borne lift in a vertical takeoff and landing flight mode and wing-borne lift in a forward flight mode, the aircraft comprising:

an airframe including at least one straight wing;

a pod assembly rotatably coupled to the airframe;

a distributed propulsion system attached to the airframe including a first plurality of propulsion assemblies each including a nacelle and a second plurality of propulsion assemblies each including a nacelle, each of the propulsion assemblies including a rotor assembly having a plurality of rotor blades, at least one of the propulsion assemblies coupled to the straight wing, the nacelles of the first plurality of propulsion assemblies longer than the nacelles of the second plurality of propulsion assemblies; and

a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies;

wherein, in the vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first horizontal plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second horizontal plane parallel to the first horizontal plane;

wherein, in the forward flight mode, each of the propulsion assemblies is configured to generate forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second vertical plane parallel to the first vertical plane; and

wherein, the airframe is rotatable relative to the pod assembly such that in both the vertical takeoff and landing flight mode and the forward flight mode, the pod assembly remains in a generally horizontal attitude.

20. An aircraft comprising:

an airframe including at least one wing;

a pod assembly coupled to the airframe;

a distributed propulsion system attached to the airframe including a first plurality of propulsion assemblies each including a nacelle and a second plurality of propulsion assemblies each including a nacelle, each of the propulsion assemblies including a rotor assembly having a plurality of rotor blades, the nacelles of the first plurality of propulsion assemblies longer than the nacelles of the second plurality of propulsion assemblies; and

a flight control system operably associated with the distributed propulsion system and operable to independently control each of the propulsion assemblies;

wherein, the first plurality of propulsion assemblies includes at least four propulsion assemblies positioned at least partially outboard of the pod assembly, the first plurality of propulsion assemblies including a plurality of left propulsion assemblies interconnected by at least one left pylon substantially perpendicular to the wing and a plurality of right propulsion assemblies interconnected by at least one right pylon substantially perpendicular to the wing;

wherein, the propulsion assemblies of the second plurality of propulsion assemblies are positioned at least partiallyoutboard of the propulsion assemblies of the first plurality of propulsion assemblies;

wherein, in a vertical takeoff and landing flight mode, each of the propulsion assemblies is configured to generate vertical thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first horizontal plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second horizontal plane parallel to the first horizontal plane;

wherein, in a forward flight mode, each of the propulsion assemblies is configured to generate forward thrust with the rotor assemblies of the first plurality of propulsion assemblies rotating in a first vertical plane and the rotor assemblies of the second plurality of propulsion assemblies rotating in a second vertical plane parallel to the first vertical plane; and

wherein, in both the vertical takeoff and landing flight mode and the forward flight mode, the pod assembly remains in a generally horizontal attitude.