Multi-mode aerial vehicle
View Patent ↗A multi-mode aerial vehicle hybrid wing includes a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis, a tilt wing attached at a first side to a free end of the fixed wing wherein the tilt wing is rotatable ninety degrees about its axis, and a duct attached to a second side of the tilt wing. The duct includes a plurality of pivotal control surfaces positioned at a top entrance of the duct, dual counter-rotating rotors positioned at an underside of the duct, a plurality of cross stators positioned at a back entrance of the duct, and a plurality of stator pivotal control surfaces within each of the cross stators of the duct. The multi-mode aerial vehicle hybrid wing also includes a winglet attached to the duct opposite to the tilt wing.
1. A multi-mode aerial vehicle, comprising:
an elongated fuselage having a front end, a rear end with a curved guide slot, a right side, a left side, and a wing-in-ground (WIG) effect bottom;
a right-fixed wing extending from the right side of the elongated fuselage;
a right tilt wing attached at a first side to a free end of the right fixed wing, the right tilt wing being rotatable ninety degrees about its axis;
a right duct attached to a second side of the right tilt wing;
a right winglet attached to the right duct opposite to the right tilt wing;
a left-fixed wing extending from the left side of the elongated fuselage;
a left tilt wing attached at a first side to a free end of the left fixed wing, the left tilt wing being rotatable ninety degrees about its axis;
a left duct attached to a second side of the left tilt wing;
a left winglet attached to the left duct opposite to the left tilt wing;
a tilt tail located within the curved guide slot at the rear end of the elongated fuselage, the tilt tail being rotatable ninety degrees within the curved guide slot;
a tilting mechanism coupling, via a gearbox, a right shaft integrated with the right tilt wing, a left shaft integrated with the left tilt wing, and a rear shaft integrated with the tilt tail within the curved guide slot; and
a rear duct attached to the tilt tail, the rear duct including a vertical stabilizer, a right horizontal stabilizer, and a left horizontal stabilizer.
2. The multi-mode aerial vehicle of claim 1 , wherein the right duct includes a plurality of pivotal control surfaces positioned at a top entrance of the right duct,
dual counter-rotating rotors positioned at an underside of the right duct,
an engine centrally located within the right duct,
a plurality of cross stators positioned at a back entrance of the right duct, and
a plurality of stator pivotal control surfaces within each of the cross stators of the right duct.
3. The multi-mode aerial vehicle of claim 2 , wherein the left duct includes
a plurality of pivotal control surfaces positioned at a top entrance of the left duct,
dual counter-rotating rotors positioned at an underside of the left duct,
an engine centrally located within the left duct,
a plurality of cross stators positioned at a back entrance of the left duct, and
a plurality of stator pivotal control surfaces within each of the cross stators of the left duct.
4. The multi-mode aerial vehicle of claim 3 , wherein the rear duct includes
a plurality of pivotal control surfaces positioned at a top entrance of the rear duct,
dual counter-rotating rotors positioned at an underside of the rear duct,
an engine centrally located within the rear duct,
a plurality of cross stators positioned at a back entrance of the rear duct, and
a plurality of stator pivotal control surfaces within each of the cross stators of the rear duct.
5. The multi-mode aerial vehicle of claim 4 , wherein each of the right tilt wing, the left tilt wing, and the tilt tail are configured to rotate for vertical take-off and landing (VTOL), short take-off and landing (STOL), and horizontal take-off and landing (HTOL).
6. The multi-mode aerial vehicle of claim 1 , wherein the WIG-effect bottom includes
a surrounding ring cavity,
at least one bottom stabilizer, and
at least one rear stabilizer.
7. The multi-mode aerial vehicle of claim 6 , wherein the WIG-effect bottom facilitates water landings and cruises over a water surface.
8. The multi-mode aerial vehicle of claim 1 , further comprising:
a hydraulically-slidable landing gear assembly.
9. The multi-mode aerial vehicle of claim 8 , wherein the hydraulically-slidable landing gear assembly includes
a plurality of inner leg members adjustable and slidable within corresponding outer leg members attached to the WIG-effect bottom,
a loading force-sensitive contact sensor attached to a bottom end of each of the inner leg members, and
a foot attached to the bottom end of each of the inner leg members.
10. The multi-mode aerial vehicle of claim 1 , further comprising:
a hydraulically-extendable bridge assembly.
11. The multi-mode aerial vehicle of claim 10 , wherein the hydraulically-extendable bridge assembly includes
a first inner bridge member slidable within an outer bridge member, and
a second inner bridge member slidable within the first inner bridge member.
12. The multi-mode aerial vehicle of claim 1 , further comprising:
a material integrated within walls of each of the right duct, the left duct, and the rear duct.
13. The multi-mode aerial vehicle of claim 1 , wherein the multi-mode aerial vehicle includes a manned multi-mode aerial vehicle.
14. A multi-mode aerial vehicle hybrid wing, comprising:
a fixed wing configured to extend from a side of an elongated fuselage and double over its longitudinal axis
a tilt wing attached at a first side to a free end of the fixed wing, the tilt wing being rotatable ninety degrees about its axis;
a duct attached to a second side of the tilt wing, the duct including
a plurality of pivotal control surfaces positioned at a top entrance of the duct,
dual counter-rotating rotors positioned at an underside of the duct,
a plurality of cross stators positioned at a back entrance of the duct, and
a plurality of stator pivotal control surfaces within each of the cross stators of the duct; and
a winglet attached to the duct opposite to the tilt wing.
15. The multi-mode aerial vehicle hybrid wing of claim 14 , further comprising:
a tilting mechanism coupling, via a gearbox, a first shaft integrated with the tilt wing, and further coupling a second shaft with an opposite tilt wing and coupling a rear shaft with a tilt tail of a multi-mode aerial vehicle.
16. The multi-mode aerial vehicle hybrid wing of claim 14 , further comprising:
a material integrated within walls of the duct.
17. A multi-mode aerial vehicle hybrid tail, comprising:
a tilt-tail configured to fit within a curved guide slot at a rear end of an elongated fuselage, the tilt tail being rotatable ninety degrees within the curved guide slot;
a duct attached to the tilt-tail at an opposite end to the curved guide slot, the duct including
a plurality of pivotal control surfaces positioned at a top entrance of the duct,
dual counter-rotating rotors positioned at an underside of the duct,
a plurality of cross stators positioned at a back entrance of the duct, and
a plurality of stator pivotal control surfaces within each of the cross stators of the duct;
a vertical stabilizer attached to the duct at an opposite side to the tilt-tail;
a first horizontal stabilizer attached to the duct at a first side; and
a second horizontal stabilizer attached to the duct at a second opposite side.
18. The multi-mode aerial vehicle hybrid tail of claim 17 , further comprising:
a tilting mechanism coupling, via a gearbox, a rear shaft with the tilt-tail, and further coupling a first and a second shaft with an opposing pair of multi-mode aerial vehicle hybrid wings.
19. The multi-mode aerial vehicle hybrid tail of claim 17 , further comprising:
a material integrated within walls of the duct.