A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude
A vertical takeoff and landing craft that utilizes lifting, propulsion and maneuvering (LPM) assemblies comprising a series of blade foils arranged along track elongated loop paths disposed at the sides of a fuselage. These LPM assemblies are provided with control mechanisms enabling lift, attitude changes, altitude changes and directional flight propulsion and control including those needed for hovering as well as vertical takeoff and landing. The LPM assemblies are configured to drive large volumes of air in a manner and scale favorably similar to conventional rotorcraft while in contrast, providing capability for faster flights by eliminating or minimizing speed limiting factors commonly associated with rotorcraft.
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1. A craft, comprising: a fuselage;a first lifting assembly coupled to the fuselage, comprising at least one blade foil, the at least one blade foil being configured to travel around an elongated loop path to provide lift to the fuselage,wherein the elongated loop path comprises a top portion and a
1. A craft, comprising: a fuselage;a first lifting assembly coupled to the fuselage, comprising at least one blade foil, the at least one blade foil being configured to travel around an elongated loop path to provide lift to the fuselage,wherein the elongated loop path comprises a top portion and a bottom portion and wherein a leading edge of the at least one blade foil travelling along the top portion of the elongated loop path becomes the trailing edge as the at least one blade foil travels along the bottom portion of the elongated loop path. 2. The craft of claim 1, wherein the lifting assembly is further configured to provide maneuvering and propulsion. 3. The craft of claim 1, wherein the lift is provided in a fluid comprising one of air and water. 4. The craft of claim 1, wherein at least one of a pitch and a chord of the at least one blade foil is configured to be dynamically controllable as the at least one blade foil travels along the predefined elongated loop path. 5. The craft of claim 1, wherein the first lifting assembly is coupled to one side of the fuselage and wherein the craft further comprises a second lifting assembly, similar to the first lifting assembly, coupled to another side of the fuselage. 6. The craft of claim 1, wherein each of the first and second lifting assemblies are independently controllable and movable relative to the fuselage. 7. The craft of claim 1, wherein the first lifting assembly is configured such that the at least one blade foil is coupled to the fuselage by a control assembly configured to control a configuration of the at least one blade foil as it travels around the elongated loop path. 8. The craft of claim 7, wherein the control assembly comprises, for each of the at least one blade foil, a control arm configured to change at least one of a chord and a pitch of the blade foil to which the control arm is coupled. 9. The craft of claim 8, wherein the control assembly comprises an elongated cone-shaped control track defining a curvature that is followed by each control arm. 10. The craft of claim 9, wherein the control assembly is configured to move the control track about x, y and z axes and wherein the control assembly is configured to control at least of the chord and pitch of each blade foil by selectively moving the control track along the x, y and z axes thereof. 11. The craft of claim 1, wherein the elongated loop path is ovaloid-shaped. 12. A craft, comprising: a fuselage;a first lifting, propulsion and maneuvering (LPM) assembly coupled to one side of the fuselage, comprising a first elongated cone-shaped control track or control belt with angled control elements a plurality of first blade foils, each of which being coupled to the first control track or belt by respective control arms and configured to travel around a first elongated loop path, a configuration of the first blade foils being controllable as the control arms follow a curvature of the first control track or belt as the first blade foils travel around the first elongated loop path. 13. The craft of claim 12, further comprising a second LPM assembly coupled to another side of the fuselage, comprising a second elongated cone-shaped control track or control belt with angled control elements, a plurality of second blade foils, each of which being coupled to the control track or belt by respective control arms and configured to travel around a second elongated loop path, a configuration of the second blade foils being controllable as the control arms follow a curvature of the second control track or belt as the second blade foils travel around the second elongated loop path. 14. The craft of claim 13, wherein the first and the second LPM assemblies are configured to be independently movable relative to the fuselage. 15. The craft of claim 12, wherein the controllable configuration of the first blade foils comprises at least one of a pitch and a chord of the first blade foils. 16. The craft of claim 12, wherein the first LPM assembly is configured to be movable relative to the fuselage along x, y and z axes. 17. The craft of claim 12, further comprising, for each of the first blade foils, a control arm configured to follow a curvature of the first control track or belt to control the configuration of the first blade foils. 18. The craft of claim 12, wherein a configuration of individual ones, groups of or all of the first blade foils are independently controllable. 19. The craft of claim 12, wherein the first elongated loop path comprises a top portion and a bottom portion and wherein leading edges of the first blade foils travelling along the top portion of the first elongated loop path become trailing edges as the first blade foils travel along the bottom portion of the first elongated loop path. 20. The craft of claim 12, wherein the first elongated loop path comprises a top portion and a bottom portion and wherein leading edges of the first blade foils travelling along the top portion of the first elongated loop path are maintained as leading edges as the first blade foils travel along the bottom portion of the first elongated loop path. 21. The craft of claim 12, configured to operate in a fluid medium comprising one of air and water. 22. The craft of claim 12, wherein the first elongated loop path is ovaloid-shaped. 23. A method of moving a craft through a fluid medium, comprising: moving a plurality of first blade foils along a first elongated loop path defined adjacent a first side of a fuselage;moving a plurality of second blade foils along a second elongated loop path defined adjacent a second side of the fuselage;controlling at least one of a movement and attitude of the craft by controlling a configuration of the first and second blade foils. 24. The method of claim 23, wherein the first blade foils are disposed around the first elongated loop path such that each leading edge of the first blade foils is adjacent to and substantially parallel with a trailing edge of a next adjacent first blade foil. 25. The method of claim 23, wherein moving comprises causing leading edges of the first and second blade foils travelling along the top portions of the first and second elongated loop paths, respectively, to become trailing edges as the first and second blade foils travel along the bottom portions of the first and second elongated loop paths, respectively. 26. The method of claim 23, wherein moving comprises maintaining leading edges of the first and second blade foils travelling along the top portions of the first and second elongated loop paths, respectively, as leading edges as the first and second blade foils travel along the bottom portions of the first and second elongated loop paths, respectively. 27. The method of claim 23, wherein controlling comprises controlling at least one of a pitch and chord of the first and second blade foils. 28. The method of claim 23, wherein controlling comprises independently controlling a configuration of groups or individual ones of the first and second blade foils. 29. The method of claim 23, wherein controlling comprises causing respective first control arms of the first blade foils to follow a first elongated cone-shaped control track or belt with angled control elements disposed on the first side of the fuselage and causing second respective control arms of the second blade foils to follow a second elongated cone-shaped control track or belt with angled control elements disposed the second side of the fuselage. 30. The method of claim 23, wherein controlling comprises comprise controlling the configuration of the first blade foils independently of the configuration of the second blade foils. 31. The method of claim 23, wherein controlling comprises: controlling the first blade foils to assume first configurations while travelling along a top portion of the first elongated loop path and to assume second configurations while travelling along a bottom portion of the first elongated loop path; andcontrolling the second blade foils to assume first configurations while travelling along a top portion of the second elongated loop path and to assume second configurations while travelling along a bottom portion of the second elongated loop path. 32. The method of claim 23, wherein the first blade foils form part of a first lifting, propulsion and maneuvering (LPM) assembly coupled to the first side of the fuselage and wherein the second blade foils form part of a second LPM assembly coupled to the second side of the fuselage, and wherein controlling comprises controlling a position and orientation of each of the first and second LPM assemblies relative to the fuselage. 33. The method of claim 32, wherein controlling comprises controlling the first and second LPM assemblies independently of one another.
Gonzales Gilbert R. (677 Creed Ave. Las Cruces NM 88005) La Monica ; Jr. John A. (1607 N. Euclid Tucson AZ 85719), Lift generating mechanism for an aircraft.
Servanty Pierre (14 Avenue Jean-Jacques Rousseau 93600 Aulnay Sous Bois FRX), Rotor for developing sustaining and propelling forces in a fluid, steering process, and aircraft equipped with such roto.
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