초록 ▼

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred em

A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.

대표청구항 ▼

1. A flight-operable, modular aircraft comprising: a center section having a physical upper component below which resides a cargo bay, and horizontally curved fore and aft spars positioned fore and aft of the cargo bay, respectively; andleft and right wings that are structurally coupled together at

1. A flight-operable, modular aircraft comprising: a center section having a physical upper component below which resides a cargo bay, and horizontally curved fore and aft spars positioned fore and aft of the cargo bay, respectively; andleft and right wings that are structurally coupled together at least predominantly through the fore and aft spars. 2. The aircraft of claim 1, wherein the wings are coupled to the center section in a mid-wing configuration. 3. The aircraft of claim 1, wherein the wings are coupled to the fore and aft spars using reusable attachment hardware comprising at least one of pins and bolts. 4. The aircraft of claim 3, wherein the wings are folding wings. 5. The aircraft of claim 1, wherein the fore spar has hard points for connecting a nose section, and the aft spar has hard points for connecting a tail section, and each of the hard points uses at least one of pins and bolts. 6. The aircraft of claim 1, further comprising left and right ribs structurally coupled to the fore and aft spars, and wherein the cargo bay is bounded by the fore and aft spars, and the left and right ribs. 7. The aircraft of claim 5, wherein bending loads resulting from the nose and tail section are structurally carried by left and right ribs. 8. The aircraft of claim 1, wherein the fore spar extends across an entire first width of the center section. 9. The aircraft of claim 8, wherein the fore spar is curved across the entire first width, and comprises a composite material. 10. The aircraft of claim 8, wherein the aft spar extends across an entire second width of the center section. 11. The aircraft of claim 1, further comprising right and left inboard ribs, and wherein the center section has a trapezoidal shape defined by the right and left inboard ribs and the fore and aft spars. 12. The aircraft of claim 1, wherein the center section provides a least 25% of the lift of the aircraft during at least some portion of cruise flight. 13. The aircraft of claim 1, wherein the aircraft is shaped as a flying wing, having substantially no empennage, no horizontal tail, and no vertical tail. 14. The aircraft of claim 1, wherein the center section includes an engine that provides a propulsive force for the aircraft, and wherein the engine does not extend above or below the center section. 15. The aircraft of claim 1, wherein center section includes avionics capable of operating the aircraft through both ground control and on-board pilot control, and fault-tolerant flight control computers and redundant sensors that communicate via an aircraft network bus. 16. The aircraft of claim 1, further comprising first, second, and third landing gear that retract into the center section. 17. The aircraft of claim 1, further comprising a cockpit, and a targeting system operable by each of a pilot in the cockpit and a ground controller. 18. The aircraft of claim 1, further comprising a supply of fuel, wherein the center section is an interchangeable mission module that houses at least 80% of onboard fuel. 19. The aircraft of claim 1, further comprising a wing span of at least 80 ft, with left and right outer wing members having sufficient stiffness to produce a natural frequency of no less than 6 Hz. 20. The aircraft of claim 1, wherein the left and right wings have sufficient stiffness to produce a natural frequency of no less than 6 Hz.