M-wing aircraft having VTOL and biplane orientations

1. An aircraft having a vertical takeoff and landing fight mode and a forward flight mode, the aircraft comprising:

an airframe including first and second M-wings with first and second pylons extending therebetween, each M-wing having a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle;

a propulsion system including a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes, the propulsion assemblies each having a rotor assembly with a tilting degree of freedom; and

a flight control system operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors;

wherein, in the vertical takeoff and landing fight mode, the aircraft operates responsive to thrust-borne lift from the propulsion system; and

wherein, in the forward flight mode, the aircraft operates responsive to wing-borne lift in a biplane orientation.

2. The aircraft as recited in claim 1 wherein, the swept angles of the swept forward portions of the M-wings are generally congruent with the swept angles of the swept back portions of the M-wings.

3. The aircraft as recited in claim 1 wherein, the propulsion system further comprises a versatile propulsion system.

4. The aircraft as recited in claim 1 wherein, the propulsion assemblies are interchangeably attachable to the airframe.

5. The aircraft as recited in claim 4 wherein, the propulsion assemblies are mechanically coupled to the airframe.

6. The aircraft as recited in claim 4 wherein, the propulsion assemblies are electrically coupled to the airframe.

7. The aircraft as recited in claim 4 wherein, the propulsion assemblies are fluidically coupled to the airframe.

8. The aircraft as recited in claim 4 wherein, the propulsion assemblies are communicably coupled to the airframe.

9. The aircraft as recited in claim 1 wherein, the airframe includes a plurality of stanchions each positioned proximate one of the leading apexes;

wherein, each of the propulsion assemblies is attached to one of the stanchions; and

wherein, the stanchions provide standoff between the propulsion assemblies and the M-wings.

10. The aircraft as recited in claim 1 wherein, each of the propulsion assemblies further comprises a line replaceable unit.

11. The aircraft as recited in claim 1 wherein, the flight control system is operable to independently control each of the propulsion assemblies.

12. The aircraft as recited in claim 1 wherein, a maximum angle of the thrust vectors is between about ten degrees and about thirty degrees.

13. The aircraft as recited in claim 1 wherein, a maximum angle of the thrust vectors is between about fifteen degrees and about twenty-five degrees.

14. The aircraft as recited in claim 1 wherein, a maximum angle of the thrust vectors is about twenty degrees.

15. The aircraft as recited in claim 1 further comprising a pod assembly selectively attachable to the airframe; and

wherein, the airframe is rotatable about the pod assembly such that the pod assembly remains in a generally horizontal attitude in the vertical takeoff and landing fight mode, the forward flight mode and transitions therebetween.

16. The aircraft as recited in claim 1 further comprising a pod assembly selectively attachable to the airframe; and

wherein, in the vertical takeoff and landing flight mode, the first wing is forward of the pod assembly and the second wing is aft of the pod assembly; and

wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly in the biplane orientation.

17. An aircraft having a vertical takeoff and landing fight mode and a forward flight mode, the aircraft comprising:

an airframe including first and second M-wings with first and second pylons extending therebetween, each M-wing having a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle;

a propulsion system including a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes;

a flight control system operable to control the propulsion assemblies; and

a pod assembly selectively attachable to the airframe;

wherein, in the vertical takeoff and landing fight mode, the first wing is forward of the pod assembly, the second wing is aft of the pod assembly and the aircraft operates responsive to thrust-borne lift from the propulsion system; and

wherein, in the forward flight mode, the first wing is below the pod assembly, the second wing is above the pod assembly and the aircraft operates responsive to wing-borne lift in a biplane orientation.

18. The aircraft as recited in claim 17 wherein, the airframe includes a plurality of stanchions each positioned proximate one of the leading apexes;

wherein, each of the propulsion assemblies is attached to one of the stanchions; and

wherein, the stanchions provide standoff between the propulsion assemblies and the M-wings.

19. The aircraft as recited in claim 18 wherein, in the biplane orientation, the first wing has a high wing configuration and the second wing has a low wing configuration.

20. The aircraft as recited in claim 17 wherein, the propulsion system further comprises a versatile propulsion system and wherein, the propulsion assemblies are interchangeably attachable to the airframe as line replaceable units.