Vertical take-off and landing (vtol) aircraft with aerodynamically lifting protective structure system and method

Abstract

A method that includes takeoff of an aircraft assembly in a vertical orientation with a central axis X of the aircraft assembly perpendicular to the ground; rotating the aircraft assembly from the vertical orientation to a horizontal orientation where the central axis X is between −5° and 20° from true horizontal; and flying the aircraft assembly from a first location to a second location in the horizontal orientation with an aircraft of the aircraft assembly generating forward propulsion for forward flight and a wing body of the aircraft assembly generating aerodynamic lift for the aircraft assembly based on the forward flight in the horizontal orientation, the aerodynamic lift generated by the wing body supporting equal to or greater than 70% of the weight of the aircraft assembly.

What is claimed is: 
     
         1 . A method of operating an aircraft assembly, the method comprising:
 takeoff of an aircraft assembly in a vertical orientation with a central axis X of the aircraft assembly perpendicular to the ground, the aircraft assembly comprising:
 a cage assembly shaped as a hollow octagonal prism with the central axis X, the cage assembly including:
 a top ring, 
 a bottom ring, 
 a plurality of sidebars extending in parallel to each other between and coupling the top ring and the bottom ring, and 
 a plurality of truss bars coupled to the top ring that extend diagonally to a peak that is coincident with the central axis X, 
 
 a wing body coupled to and surrounding the sidebars between the top ring and bottom ring, the wing body defining a cage cavity having an open top cavity end and an open bottom cavity end, and 
 an aircraft disposed within the cage cavity between the top ring and the bottom ring, the aircraft coupled to a set of the sidebars of the cage assembly via a plurality of struts, the aircraft comprising an aircraft body with a plurality of arms extending from the aircraft body with rotors at terminal ends of the arms, the aircraft further comprising a plurality of sensors and a computing device having a processor and memory storing executable instructions, the rotors generating upward lift for the aircraft assembly during takeoff of the aircraft assembly in the vertical orientation; 
   after the takeoff of the aircraft assembly in the vertical orientation, rotating the aircraft assembly from the vertical orientation to a horizontal flight orientation where the central axis X is between 5° and 10° from true horizontal;   flying the aircraft assembly from a first location to a second location in the horizontal flight orientation with the truss bars and top ring oriented forward and being a leading edge during forward flight and with the bottom ring being a trailing edge during forward flight, the rotors of the aircraft generating forward propulsion for the forward flight and the wing body generating aerodynamic lift for the aircraft assembly based on forward flight in the horizontal flight orientation, the aerodynamic lift generated by the wing body supporting equal to or greater than 90% of the weight of the aircraft assembly and reducing power required to fly in the horizontal flight orientation compared to forward flight of the aircraft assembly in the vertical orientation;   at the second location, rotating the aircraft assembly from the horizontal flight orientation to the vertical orientation; and   landing the aircraft assembly on the ground in the vertical orientation at the second location.   
     
     
         2 . The method of  claim 1 , wherein the top ring and the bottom ring are defined by a plurality of rods of the same length that are coupled by respective fittings to define respective regular octagonal rings. 
     
     
         3 . The method of  claim 1 , wherein the wing body has an airfoil profile, with a leading edge of the airfoil profile at the top ring and with a trailing edge of the airfoil profile at the bottom ring, wherein the airfoil profile generates the aerodynamic lift of the wing body to cause the wing body supporting equal to or greater than 90% of the weight of the aircraft assembly. 
     
     
         4 . The method of  claim 1 , wherein the plurality of sensors includes a camera, with a view of the camera directed at an internal face of the wing body, and wherein the wing body is transparent so that the camera is able to observe through the wing body and outside of the cage cavity. 
     
     
         5 . A method of operating an aircraft assembly, the method comprising:
 takeoff of an aircraft assembly in a vertical orientation with a central axis X of the aircraft assembly perpendicular to the ground, the aircraft assembly comprising:
 a cage assembly including:
 a top ring, 
 a bottom ring, and 
 a plurality of sidebars extending in parallel to each other between and coupling the top ring and the bottom ring, 
 
 a wing body coupled to and surrounding the sidebars between the top ring and bottom ring, the wing body defining a cage cavity having an open top cavity end and an open bottom cavity end, and 
 an aircraft disposed within the cage cavity between the top ring and the bottom ring, the aircraft coupled to a set of the sidebars of the cage assembly via a plurality of struts, the aircraft generating upward lift for the aircraft assembly during takeoff of the aircraft assembly in the vertical orientation; 
   after the takeoff of the aircraft assembly in the vertical orientation, rotating the aircraft assembly from the vertical orientation to a horizontal flight orientation where the central axis X is between 0° and 15° from true horizontal;   flying the aircraft assembly from a first location to a second location in the horizontal flight orientation with the top ring oriented forward and being a leading edge during forward flight and with the bottom ring being a trailing edge during forward flight, the aircraft generating forward propulsion for the forward flight and the wing body generating aerodynamic lift for the aircraft assembly based on forward flight in the horizontal flight orientation, the aerodynamic lift generated by the wing body supporting equal to or greater than 80% of the weight of the aircraft assembly;   at the second location, rotating the aircraft assembly from the horizontal flight orientation to the vertical orientation; and   landing the aircraft assembly on the ground in the vertical orientation at the second location.   
     
     
         6 . The method of  claim 5 , wherein the cage assembly shaped as a hollow octagonal prism with the central axis X being a central axis for the hollow octagonal prism. 
     
     
         7 . The method of  claim 5 , wherein the cage assembly further comprises a plurality of truss bars coupled to the top ring that extend diagonally to a peak that is coincident with the central axis X. 
     
     
         8 . The method of  claim 5 , wherein aircraft comprises:
 an aircraft body,   a plurality of rotors that generate upward lift for the aircraft assembly during takeoff of the aircraft assembly in the vertical orientation and that generate forward propulsion of the aircraft assembly in the horizontal flight orientation,   a plurality of sensors, and   a computing device having a processor and memory storing executable instructions.   
     
     
         9 . The method of  claim 5 , wherein the aerodynamic lift generated by the wing body reduces power required to fly in the horizontal flight orientation compared to forward flight of the aircraft assembly in the vertical orientation. 
     
     
         10 . A method of operating an aircraft assembly, the method comprising:
 takeoff of an aircraft assembly in a vertical orientation with a central axis X of the aircraft assembly perpendicular to the ground, the aircraft assembly comprising:
 a wing body defining a cavity having an open top cavity end and an open bottom cavity end, and 
 an aircraft disposed within the cavity between the open top cavity end and the open bottom cavity end, the aircraft generating upward lift for the aircraft assembly during takeoff of the aircraft assembly in the vertical orientation; 
   after the takeoff of the aircraft assembly in the vertical orientation, rotating the aircraft assembly from the vertical orientation to a horizontal orientation where the central axis X is between −5° and 20° from true horizontal; and   flying the aircraft assembly from a first location to a second location in the horizontal orientation, the aircraft generating forward propulsion for forward flight and the wing body generating aerodynamic lift for the aircraft assembly based on the forward flight in the horizontal orientation, the aerodynamic lift generated by the wing body supporting equal to or greater than 70% of the weight of the aircraft assembly.   
     
     
         11 . The method of  claim 10 , wherein the aircraft assembly further comprises a cage assembly that includes:
 a top ring, and   a bottom ring.   
     
     
         12 . The method of  claim 11 , wherein the cage assembly further comprises a plurality of sidebars between and coupling the top ring and the bottom ring. 
     
     
         13 . The method of  claim 11 , wherein the aircraft is coupled to the cage assembly via a plurality of struts. 
     
     
         14 . The method of  claim 11 , wherein the top ring is oriented forward and is a leading edge during forward flight in the horizontal orientation and with the bottom ring being a trailing edge during forward flight in the horizontal orientation. 
     
     
         15 . The method of  claim 11 , wherein the cage assembly further comprises a plurality of truss bars that extend diagonally to a peak that is coincident with the central axis X. 
     
     
         16 . The method of  claim 10 , further comprising
 at the second location, rotating the aircraft assembly from the horizontal orientation to the vertical orientation; and   landing the aircraft assembly in the vertical orientation at the second location.   
     
     
         17 . The method of  claim 10 , wherein the wing body is shaped as a hollow polygonal prism with the central axis X being a central axis for the hollow polygonal prism. 
     
     
         18 . The method of  claim 10 , wherein aircraft comprises:
 an aircraft body, and   one or more rotors that generate upward lift for the aircraft assembly during takeoff of the aircraft assembly in the vertical orientation and that generate forward propulsion of the aircraft assembly in the horizontal orientation.   
     
     
         19 . The method of  claim 10 , wherein the aerodynamic lift generated by the wing body reduces power required to fly in the horizontal orientation compared to forward flight of the aircraft assembly in the vertical orientation. 
     
     
         20 . The method of  claim 10 , wherein the wing body has an airfoil profile and wherein the airfoil profile generates the aerodynamic lift of the wing body to cause the wing body supporting equal to or greater than 70% of the weight of the aircraft assembly.