CPC B64C 29/0033 (2013.01) [B64C 5/02 (2013.01); B64C 11/46 (2013.01); B64C 39/12 (2013.01)] | 18 Claims |
1. An aircraft, comprising:
a canard having a leading edge and a trailing edge;
a forward swept and fixed wing having a trailing edge;
a plurality of tilt rotor submodules, including:
a first tilt rotor submodule, wherein:
the leading edge of the canard contacts the first tilt rotor submodule at a position that is within a range of 40% to 60%, inclusive, of a length of the first tilt rotor submodule where 0% corresponds to a forward tip of the first tilt rotor submodule and 100% corresponds to an aft tip of the first tilt rotor submodule; and
the trailing edge of the canard contacts the first tilt rotor submodule at position that is within a range of 55% to 80%, inclusive, of the length of the first tilt rotor submodule; and
a plurality of other tilt rotor submodules that are coupled to the trailing edge of the forward swept and fixed wing; and
a dovetail attached to an underside of a fuselage, wherein the dovetail pushes a nose of the aircraft down during a deep stall, wherein the fuselage rests on the dovetail when the aircraft is on the ground, and wherein the forward swept and fixed wing includes a corresponding curved section for each of the plurality of other tilt rotor submodules that is parallel to a curve of propeller disks associated with the plurality of other tilt rotor submodules when the plurality of other tilt rotor submodules are in a hovering position.
|