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
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.
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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 fi
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; anda 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, anda 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, anda 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, anda 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, andat 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, anda 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, anda 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 axisa 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, anda plurality of stator pivotal control surfaces within each of the cross stators of the duct; anda 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, anda 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; anda 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.
Posva, David, Aircraft having the ability for hovering flight, fast forward flight, gliding flight, short take-off, short landing, vertical take-off and vertical landing.
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