Logistics support aircraft having a minimal drag configuration
An aircraft is operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween forming a central region. A two-dimensional distributed thrust array and a flight control system are coupled to the airframe. A nose cone and an afterbody are each selectively coupled to the airframe. In a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe such that the nose cone and the afterbody each extend between the first and second wings and between first and second pylons to form a cargo enclosure with an aerodynamic outer shape. In a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during flight.
1. An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation, the aircraft comprising:
an airframe having first and second wings with first and second pylons extending therebetween forming a central region;
a two-dimensional distributed thrust array attached to the airframe, the thrust array including a plurality of propulsion assemblies coupled to the first wing and a plurality of propulsion assemblies coupled to the second wing;
a flight control system coupled to the airframe and operable to independently control each of the propulsion assemblies;
a nose cone selectively coupled to the airframe such that the nose cone extends between the first and second wings and between first and second pylons; and
an afterbody selectively coupled to the airframe such that the afterbody extends between the first and second wings and between first and second pylons;
wherein, in a cargo delivery flight configuration, the nose cone and the afterbody are coupled to the airframe to form a cargo enclosure with an aerodynamic outer shape; and
wherein, in a minimal drag flight configuration, the nose cone and the afterbody are not coupled to the airframe such that air passes through the central region during flight.
2. The aircraft as recited in claim 1 wherein, in the biplane orientation, the first wing is an upper wing having a dihedral configuration and the second wing is a lower wing having an anhedral configuration.
3. The aircraft as recited in claim 1 wherein the central region forms a rectangle having a major dimension extending between the first and second wings and a minor dimension extending between first and second pylons and wherein the major dimension is greater than the minor dimension.
4. The aircraft as recited in claim 3 wherein the major dimension is between about two times and about four times greater than the minor dimension.
5. The aircraft as recited in claim 1 wherein each of the propulsion assemblies is outboard of the central region.
6. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a variable speed electric motor and a rotor assembly.
7. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a thrust vectoring propulsion assembly.
8. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a longitudinal thrust vectoring propulsion assembly.
9. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises an omnidirectional thrust vectoring propulsion assembly.
10. The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a tail assembly with at least one aerosurface.
11. The aircraft as recited in claim 1 wherein the plurality of propulsion assemblies coupled to the first wing further comprises two propulsion assemblies and the plurality of propulsion assemblies coupled to the second wing further comprises two propulsion assemblies.
12. The aircraft as recited in claim 1 wherein the nose cone further comprises a leading edge fairing that is slidably receivable on the airframe.
13. The aircraft as recited in claim 1 wherein the afterbody further comprises a trailing edge fairing that is slidably receivable on the airframe.
14. The aircraft as recited in claim 13 wherein the trailing edge fairing further comprises first and second trailing edge members that are rotatable relative to the first and second pylons, respectively, such that the first and second trailing edge members have open and closed positions.
15. A method of operating an aircraft comprising:
providing an airframe having first and second wings with first and second pylons extending therebetween forming a central region, a plurality of propulsion assemblies coupled to the first wing, a plurality of propulsion assemblies coupled to the second wing and a flight control system operable to independently control each of the propulsion assemblies;
forming a cargo enclosure having an aerodynamic outer shape by attaching a nose cone to the airframe such that the nose cone extends between the first and second wings and between first and second pylons and by attaching an afterbody to the airframe such that the afterbody extends between the first and second wings and between first and second pylons;
disposing cargo within the cargo enclosure;
transporting the cargo by air from a first location to a second location including transitioning the aircraft between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation;
removing the cargo from the cargo enclosure at the second location;
detaching the nose cone and the afterbody from the airframe forming a minimal drag flight configuration in which air passes through the central region during flight; and
returning the aircraft by air from the second location to the first location in the minimal drag flight configuration including transitioning the aircraft between thrust-borne lift in the VTOL orientation and wing-borne lift in the biplane orientation.
16. The method as recited in claim 15 wherein transporting the cargo by air from the first location to the second location further comprises transitioning the aircraft between the VTOL orientation wherein the first wing is forward of the cargo enclosure and the second wing is aft of the cargo enclosure and the biplane orientation wherein the first wing is below the cargo enclosure and the second wing is above the cargo enclosure.
17. The method as recited in claim 15 further comprising operating the aircraft responsive to autonomous flight control.
18. The method as recited in claim 15 further comprising operating the aircraft responsive to remote flight control.
19. The method as recited in claim 15 further comprising operating the aircraft responsive to a combination of remote flight control and autonomous flight control.
20. The method as recited in claim 15 wherein attaching the nose cone to the airframe further comprises slidably receiving a leading edge fairing on the airframe;
wherein attaching the afterbody to the airframe further comprises slidably receiving a trailing edge fairing on the airframe;
wherein detaching the nose cone from the airframe further comprises slidably removing the leading edge fairing from the airframe; and
wherein detaching the afterbody from the airframe further comprises slidably removing the trailing edge fairing from the airframe.