초록 ▼

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.

대표청구항 ▼

1. A method, comprising: providing a fuselage;coupling a first lifting assembly to the fuselage, the first lifting assembly comprising at least one blade foil and an elongated loop path that comprises a first portion and a second portion;generating lift to the fuselage by causing the at least one bl

1. A method, comprising: providing a fuselage;coupling a first lifting assembly to the fuselage, the first lifting assembly comprising at least one blade foil and an elongated loop path that comprises a first portion and a second portion;generating lift to the fuselage by causing the at least one blade foil to travel around the elongated loop path such that a leading edge of the at least one blade foil travelling along the first portion of the elongated loop path becomes the trailing edge as the at least one blade foil travels along the second portion of the elongated loop path. 2. The method of claim 1, further configuring manipulating the first lifting assembly to provide maneuvering and propulsion. 3. The method of claim 1, wherein generating lift is carried out in a fluid comprising at least one of air and water. 4. The method of claim 1, further comprising dynamically controlling at least one of a pitch and a chord of the at least one blade foil as the at least one blade foil travels along the elongated loop path. 5. The method of claim 1, wherein coupling comprises coupling the first lifting assembly to one side of the fuselage and wherein the method further comprises coupling a second lifting assembly to another side of the fuselage. 6. The method of claim 5, further comprising independently controlling and moving each of the first and second lifting assemblies relative to the fuselage. 7. The method of claim 1, further comprising coupling the at least one blade foil to a control assembly that is configured to control a configuration of the at least one blade foil as the at least one blade foil travels around the elongated loop path. 8. The method of claim 7, wherein the control assembly comprises, for each of the at least one blade foil, a control arm, and wherein the method further comprises the control arm changing at least one of a chord and a pitch of the blade foil to which the control arm is coupled. 9. The method of claim 8, wherein the control assembly comprises an elongated cone-shaped control track defining a curvature and wherein the method further comprises causing each control arm to follow the curvature of the elongated cone-shaped control track. 10. The method of claim 9, further comprising configuring the control assembly to selectively move the control track in all directions about x, y and z axes and configuring the control assembly 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 method of claim 3, wherein coupling comprises configuring the elongated loop path of the first lifting assembly to be ovaloid-shaped. 12. A method, comprising: providing a fuselage;providing and coupling a first lifting, propulsion and maneuvering (LPM) assembly to one side of the fuselage, the first LPM comprising a first elongated cone-shaped control assembly that comprises a first elongated loop path, a plurality of first angled control elements and a plurality of first blade foils, each of the plurality of first blade foils being coupled to the first control assembly by a respective one of a plurality of first control arms;causing each of the plurality of first blade foils to travel around the first elongated loop path; andcontrolling, as the plurality of first blade foils travel around the first elongated loop path, a configuration of the plurality of first blade foils as the plurality of first control arms follow a curvature of the first control assembly. 13. The method of claim 12, further comprising providing and coupling a second LPM assembly to another side of the fuselage, the second LPM comprising a second elongated cone-shaped control assembly that comprises a second elongated loop path, a plurality of second angled control elements and a plurality of second blade foils, each of the plurality of second blade foils being coupled to the second control assembly by a respective one of a plurality of second control arms; causing each of the plurality of second blade foils to travel around the second elongated loop path; andcontrolling, as the plurality of second blade foils travel around the second elongated loop path, a configuration of the plurality of second blade foils as the plurality of second control arms follow a curvature of the second control assembly. 14. The method of claim 13, further comprising independently moving the first and the second LPM assemblies relative to the fuselage. 15. The method of claim 12, further comprising controlling at least one of a pitch and a chord of the plurality of first blade foils. 16. The method a claim 12, further comprising configuring the first LPM assembly to be selectively movable relative to the fuselage in all directions along x, y and z axes. 17. The method of claim 12, further comprising controlling the configuration of the first blade foils by causing, for each of the first blade foils, a control arm to follow a curvature of the first control assembly. 18. The method of claim 12, further comprising independently controlling a configuration of individual ones, groups of or all of the first blade foils. 19. The method of claim 12, wherein the first elongated loop path comprises a first portion and a second portion and wherein the method further comprises controlling the first blade foils such that leading edges of the first blade foils travelling along the first portion of the first elongated loop path become trailing edges as the first blade foils travel along the second portion of the first elongated loop path. 20. The method of claim 12, wherein the first elongated loop path comprises a first portion and a second portion and wherein the method further comprises maintaining leading edges of the first blade foils travelling along the first portion of the first elongated loop path as leading edges as the first blade foils travel along the second portion of the first elongated loop path. 21. The method of claim 12, further comprising configuring the first LPM to operate in a fluid medium comprising at least one of air and water. 22. The method of claim 12, further comprising configuring the first elongated loop path to be ovaloid-shaped. 23. A craft configured to move through a fluid medium, comprising: a plurality of first blade foils configured to move along a first elongated loop path defined adjacent a first side of a fuselage; anda plurality of second blade foils configured to move along a second donated loop path defined adjacent a second side of the fuselage,wherein at least one of a movement and attitude of the craft within the fluid medium is controllable by controlling a configuration of the plurality of first and second blade foils. 24. The craft of claim 23, wherein the plurality of first blade foils are disposed around the first elongated loop path such that each leading edge of each of the plurality of first blade foils is adjacent to and substantially parallel with a trailing edge of a next adjacent first blade foil. 25. The craft of claim 23, wherein leading edges of the plurality of first and second blade foils travelling along first portions of the first and second elongated loop paths, respectively, are configured to become trailing edges as the plurality of first and second blade foils travel along second portions of the first and second elongated loop paths, respectively. 26. The craft of claim 23, wherein leading edges of the plurality of first and second blade foils travelling along first portions of the first and second elongated loop paths, respectively, are configured to be maintained as leading edges as the plurality of first and second blade foils travel along second portions of the first and second elongated loop paths, respectively. 27. The craft of claim 23, wherein the plurality of first and second blade foils are configured such that at least one of a pitch and chord thereof is controllable. 28. The craft of claim 23, wherein a configuration of groups or individual ones of the plurality of first and second blade foils are independently controllable. 29. The craft of claim 23, further comprising: first elongated cone-shaped control assembly defining a first curvature and comprising angled a plurality of first control elements disposed on the first side of the fuselage;a first plurality of control arms, each coupled to a respective one of the plurality of first blade foils, configured to follow the first curvature;a second elongated cone-shaped control assembly defining a second curvature and comprising a plurality of second angled control elements disposed the second side of the fuselage; anda second plurality of control arms, each coupled to a respective one of the plurality of second blade foils, configured to follow the second curvature. 30. The craft of claim 23, wherein the configuration of the first blade foils is configured to be controllable independently of the configuration of the second blade foils. 31. The craft of claim 23, wherein: the plurality of first blade foils are configured and controllable to assume first configurations while travelling along a first portion of the first elongated loop path and to assume second configurations while travelling along a second portion of the first elongated loop path; andthe plurality of second blade foils are configured and controllable to assume first configurations while travelling along a first portion of the second elongated loop path and to assume second configurations while travelling along a second 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 a position and orientation of each of the first and second LPM assemblies is controllable relative to the fuselage. 33. The method of claim 32, wherein the first and second LPM assemblies are controllable independently of one another.