Multi-Role Aircraft With Interchangeable Mission Modules

Abstract

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.

What is claimed is: 
     
         1 . A flight-operable, modular aircraft comprising:
 a center section having a cargo bay, fore and aft spars positioned fore and aft of the cargo bay, respectively, a left wing hardpoint coupling; a right wing hardpoint coupling, and a module hardpoint coupling;   a first left wing that structurally couples to the center section;   a first right wing that structurally couples to the center section; and   a first mission module that structurally and removably couples to the center section via the module hardpoint coupling.   
     
     
         2 . The aircraft of  claim 1 , wherein the center section further comprises a plurality of removable panels. 
     
     
         3 . The aircraft of  claim 1 , wherein the center section has a left wing hardpoint and a right wing hardpoint for removably connecting the first left wing and right left wing, respectively. 
     
     
         4 . The aircraft of  claim 2 , further comprising a second left wing and a second right wing that structurally couple to the left wing hardpoint and right wing hardpoint, respectively. 
     
     
         5 . The aircraft of  claim 4 , wherein the first left and right wings have a different dimension that the second left and right wings, respectively. 
     
     
         6 . The aircraft of  claim 1 , further comprising a plurality of interchangeable le mission modules that structurally couple to the center section via the module hardpoint coupling. 
     
     
         7 . The aircraft of  claim 1 , wherein the first mission module is selected from the group consisting of an aerial mapping module, a maritime patrol module, a police surveillance module, an air ambulance module, an air interdiction module, a close air support module, communications relay module, and a radio frequency signal jamming or interception module. 
     
     
         8 . The aircraft of  claim 1 , wherein the first mission module is selected from the group consisting of an aerial spraying module, a ground strike module, a missile launch module, and a light water bomber module. 
     
     
         9 . The aircraft of  claim 1 , wherein the first mission module is selected from the group consisting of a fuselage module, a refrigerated cargo module, a cargo container module having a roller floor and tie downs, a combination cargo and passenger transport module, and an air drop cargo module. 
     
     
         10 . The aircraft of  claim 1 , wherein the first mission module is selected from the group consisting of a standard passenger transport module, a luxury passenger transport module, a and a small vehicle launch module. 
     
     
         11 . The aircraft of  claim 1 , wherein the wings are coupled to the center section in a mid-wing configuration. 
     
     
         12 . 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. 
     
     
         13 . The aircraft of  claim 1 , further comprising a nose section hardpoint on the fore spar for removably connecting a nose section. 
     
     
         14 . The aircraft of  claim 13 , further comprising a tail hardpoint on the aft spar for removably connecting a tail section. 
     
     
         15 . The aircraft of  claim 14 , 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. 
     
     
         16 . 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. 
     
     
         17 . The aircraft of  claim 1 , wherein the center portion is shaped as a flying wing, having substantially no empennage, no horizontal tail, and no vertical tail. 
     
     
         18 . 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.