Aerial vehicles and related methods
The airframe-connected airfoils with angled channels and integrated control systems enhance the operational efficiency and control of a float-and-fly UAV, addressing the need for improved maneuverability and reduced loads in both water and air environments.
Patent Information
- Application Number
- PCT/US2024/051824
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-10-23
- Filing Date
- 2024-10-17
- Publication Date
- 2025-11-13
AI Technical Summary
There is a need for a float-and-fly uncrewed aerial vehicle (UAV) that can efficiently operate in various environments, including water and air, with improved control mechanisms and reduced structural and drag loads.
The design incorporates an airframe connected to multiple airfoils with angled channels for fluid communication with blowers, wing members with rudder elements, and propulsors for controlling flight dynamics, along with a combination of control surfaces and differential thrusters for enhanced maneuverability and stability.
The design enables efficient operation in both water and air with reduced drag and structural loads, allowing for short takeoff and landing capabilities, and provides precise control through integrated control surfaces and thrust mechanisms.
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Abstract
Description
AERIAL VEHICLES AND RELATED METHODSCopyright Notice
[0001] © 2024 LeVanta Tech Inc. A portion of the disclosure of this patent document contains material that is subject to copyright protection. The copyright owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure, as it appears in the Patent and Trademark Office patent file or records, but otherwise reserves all copyright rights whatsoever. 37 CFR § 1 .71 (d).Cross-Reference to Related Applications
[0002] This application claims priority to U.S. Provisional Patent Application No.63 / 592,561 , filed October 23, 2023 and entitled AERIAL VEHICLES AND RELATED METHODS, the contents of which are incorporated herein by reference in their entirety.Technical Field
[0003] The present disclosure relates to aerospace technology, in particular to uncrewed aerial vehicles and related methods.Background
[0004] Airfoils and vehicles incorporating the same and methods of use are disclosed in W02022040463. Additional wing-in-ground effect (WIG) vehicles are disclosed in US20230127417. A need exists for a float-and-fly uncrewed aerial vehicle (UAV).Brief Description of the Drawings
[0005] Non-limiting embodiments of the present disclosure are illustrated in the accompanying drawings, in which:
[0006] Fig. 1 illustrates a perspective view of one embodiment of an aerial vehicle disclosed herein.
[0007] Figs. 2A and 2B depict the results of computational fluid dynamic modeling of one embodiment of an airfoil wherein a lower portion of the internal channel is angled rearward, relative to the leading edge of the airfoil. Fig. 2A depicts a graphical front view. Fig. 2B depicts a graphical side view.Detailed Description
[0008] The contents of W02022040463 and US20230127417, including the claims, are incorporated herein in their entirety.
[0009] Disclosed herein are vehicles comprising an airframe operatively connected to one or more blowers. The airfoil includes an upper surface and a lower surface extending laterally along a leading edge to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is in fluidic communication with at least one of the one or more blowers. A wing member operably couples the airfoil to the airframe and provides fluidic communication between the one or more blowers and the airfoil. The wing member includes a rudder element.
[0010] The vehicle may include first and second wing members each operably connected to separate first and second rear airfoils. The separate first and second rear airfoils may be adjacent the airframe without overlapping vertically with the airframe. The airframe may include an elevator at the tail of the airframe.
[0011] The airfoil may be pivotable in one dimension.
[0012] The airfoil may optionally include a nozzle extending downward from the lower surface of the airfoil in fluidic communication with the channel of the airfoil. The nozzle may be extendable and retractable.
[0013] A vehicle will typically include multiple airfoils. In certain configurations, each airfoil may be operably connected to individual blowers. The vehicle may include one or more propulsors separate from the one or more blowers.
[0014] In certain configurations, the vehicle may have a single airfoil located longitudinally in front of the airframe and operably connected to the airframe and a single blower by a boom.
[0015] Any of the vehicles disclosed herein may include an airfoil comprising an upper surface and a lower surface extending laterally along a leading edge to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil is configured to be operatively connected to the airframe via the upper surface of each airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is configured to be in fluidic communication with at least one of the one or more blowers, and wherein a lower portion of the channel is angled rearward,relative to the leading edge (see, e.g. Figs. 2A and 2B). The lower portion of the channel may be angled rearward 10 to 50 degrees, relative to vertical, 15 to 45 degrees, 20 to 30 degrees, or about 20 degrees. The angled lower portion of the channel results in thrust as well as lift when fluid is blown through the channel.
[0016] Methods of controlling a flying vehicle are also disclosed herein. The methods include providing a flying vehicle comprising an airframe operatively connected to one or more blowers, at least two airfoils, wherein each airfoil comprises an upper surface and a lower surface extending laterally along a leading edge to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is in fluidic communication with at least one of the one or more blowers, and first and second wing members each operably connected to separate first and second rear airfoil, wherein each wing member operably couples a respective airfoil to the airframe and providing fluidic communication between the one or more blowers and the airfoil, and wherein the first and second wing members each comprise a rudder element, respectively. The methods may include controlling roll of the vehicle, at least partially, with a pitch of the first rear airfoil relative to a pitch of the second rear airfoil. The methods may further include controlling yaw of the vehicle with the rudder element on each of the first and second wing members.
[0017] When the vehicle includes a single airfoil located longitudinally in front of the airframe and operably connected to the airframe by a boom, the methods may include controlling at least partially a pitch of the vehicle by a pitch of the front airfoil.
[0018] The vehicle may include at least two propulsors separate from the one or more blowers. The methods may include controlling at least partially yaw of the vehicles by differential thrust in the at least two propulsors.
[0019] The vehicle may include an elevator at the tail of the airframe. The methods may include controlling at least partially a pitch of the vehicle by controlling a pitch of the elevator.
[0020] Modulating a pressure underneath each airfoil via control of a separate blower operably connected to that airfoil may also be used for controlling at least partially and / or stabilizing at least partially the vehicle relative to a surface, such as the ocean surface.
[0021] One embodiment of an aerial vehicle (see Fig. 1 ) consists of a main body,which like in a conventional vehicle (such as an aircraft, ship or ground vehicle), holds the payload, the energy storage and the powerplant. The body is designed as a lifting body, leading to lower Hoverfoil loadings, reducing structural loadings and reducing drag both in water and air operation. Three Hoverfoils placed under the flotation line of the main body are the main aero-hydrodynamic surfaces. Each of the Hoverfoils is located at the end of a "leg" (aka “wing”) that connects it to the body. Two of the Hoverfoils are placed at the rear section of the vehicle, one on each side, and are connected to the body through a wing each. The front Hoverfoil is placed at the end of a front boom that protrudes from the front of the body. The vehicle floats with its main body with the submerged lifting surfaces while on station, and raises above the water surface in forward flight. Two of the Hoverfoils are placed behind the center of gravity while a front Hoverfoil balances the vehicle longitudinally. The placement of a Hoverfoil in the front allows for all the lifting surfaces to lift upwards throughout the operational envelope, and helps push the center of gravity to the front. The front lifting surface presents a higher wing loading than the rear ones.
[0022] The control of the vehicle is achieved thanks to a combination of control surfaces and differential thrusters. The powerplant used on the alpha is battery- powered electric. Thrust is achieved using 5 electric ducted fans, powering each of the Hoverfoils, and providing forward thrust. The Hoverfoil-powering fans are placed in the main body and each have a separate intake at the top surface. The intakes at the top help create depression on the upper surface of the body slightly increasing lift and aspirating the boundary layer, which results in slightly reduced drag. Behind the fans, the air is directed to the lower surface of each of the Hoverfoils where it is injected at a slightly backwards angle. This airflow is a primary source of lift during takeoff and landing at very low speeds, and it confers the vehicle the capability of very short takeoff and landing, suitable for water operations. Two additional fans are placed horizontally in front of the center of gravity (CG) on top of the body and provide thrust like any conventional thruster on an aircraft. These two fans are the primary source of thrust and are used mainly in horizontal flight. Additionally, control surfaces add controllability to the vehicle. Each of the Hoverfoils is fitted with a servo motor which allows for independent pitch control. The differential actuation of the front and rear Hoverfoils provides pitch control while the differential actuation of the rear Hoverfoils provides roll. Yaw is achieved by differentially actuating the thrusters. The vehicle is fitted also with an elevator at the rear end of the body, whichprovides redundancy on pitch control and can actuate as a pitch trim. Two rudders (shown in outline) are placed at the trailing edges of the wings, providing additional yaw control.
[0023] Figs. 2A and 2B depict an airfoil with an air duct (internal channel) placed at an angle of ~20 degrees with respect to the normal to the base plane and a smooth transition between the duct and the pressure surface (underside). The flow pattern for the geometry, in the “air on” condition is shown.
[0024] The phrases “operably connected to,” “connected to,” “coupled to,” “operatively connected,” or “operative connection” refer to any form of interaction between two or more entities, including mechanical, electrical, magnetic, electromagnetic, fluid, and thermal interaction. Likewise, “f lu id ically connected to” or “fluidical ly connecting” refers to any form of fluidic interaction between two or more entities. Two entities may interact with each other even though they are not in direct contact with each other. For example, two entities may interact with each other through an intermediate entity.
[0025] The term “proximal” is used herein to refer to “near” or “at” the object disclosed.
[0026] It will be apparent to those having skill in the art that many changes may be made to the details of the above-described embodiments without departing from the underlying principles of the invention.
Claims
Claims1. A vehicle comprising: an airframe operatively connected to one or more blowers; an airfoil comprising an upper surface and a lower surface extending laterally along a leading edge to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is in fluidic communication with at least one of the one or more blowers, and a wing member operably coupling the airfoil to the airframe and providing fluidic communication between the one or more blowers and the airfoil, wherein the wing member comprises a rudder element.
2. The vehicle of claim 1 , further comprising first and second wing members each operably connected to separate first and second rear airfoils.
3. The vehicle of claim 2, wherein the separate first and second rear airfoils are adjacent the airframe without overlapping vertically with the airframe.
4. The vehicle of any one of claims 1 -3, wherein the airframe comprises an elevator at the tail of the airframe.
5. The vehicle of any one of claims 1 -4, wherein the airfoil is pivotable in one dimension.
6. The vehicle of any one of claims 1 -5, wherein the airfoil further comprises a nozzle extending downward from the lower surface of the airfoil in fluidic communication with the channel of the airfoil.
7. The vehicle of claim 6, wherein the nozzle for each airfoil is extendable and retractable.
8. The vehicle of any one of claims 1 -7, further comprising multiple airfoils and wherein each airfoil is operably connected to a single blower.
9. The vehicle of claim 8, further comprising one or more propulsors separate from the one or more blowers.
10. The vehicle of claim 8 or claim 9, further comprising a single airfoil located longitudinally in front of the airframe and operably connected to the airframe and a single blower by a boom.11 . The vehicle of any one of claims 1 -10, wherein a lower portion of the channel is angled rearward, relative to the leading edge.
12. The vehicle of claim 1 1 , wherein the lower portion of the channel is angled rearward 10 to 50 degrees, relative to vertical, 15 to 45 degrees, 20 to 30 degrees, or about 20 degrees.
13. An airfoil comprising an upper surface and a lower surface extending laterally along a leading edge to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil is configured to be operatively connected to the airframe via the upper surface of each airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is configured to be in fluidic communication with at least one of the one or more blowers, and wherein a lower portion of the channel is angled rearward, relative to the leading edge.
14. The airfoil of claim 13, wherein the lower portion of the channel is angled rearward 10 to 50 degrees, relative to vertical, 15 to 45 degrees, 20 to 30 degrees, or about 20 degrees.
15. The airfoil of claim 13 or of claim 14, wherein the angled lower portion of the channel results in thrust as well as lift when fluid is blown through the channel.
16. A method of controlling a vehicle, the method comprising: providing a flying vehicle comprising: an airframe operatively connected to one or more blowers; at least two airfoils, wherein each airfoil comprises an upper surface and a lower surface extending laterally along a leading edge to first and second arcuatewingtips defining a concave region bounded by the lower surface of the airfoil, wherein the airfoil comprises a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is in fluidic communication with at least one of the one or more blowers, and first and second wing members each operably connected to separate first and second rear airfoil, wherein each wing member operably couples a respective airfoil to the airframe and providing fluidic communication between the one or more blowers and the airfoil, and wherein the first and second wing members each comprise a rudder element, respectively, and controlling roll of the vehicle, at least partially, with a pitch of the first rear airfoil relative to a pitch of the second rear airfoil, and controlling yaw of the vehicle with the rudder element on each of the first and second wing members.
17. The method of claim 16, wherein the vehicle further comprises a single airfoil located longitudinally in front of the airframe and operably connected to the airframe by a boom, and controlling at least partially a pitch of the vehicle by a pitch of the front airfoil.
18. The method of claim 16 or claim 17, wherein the vehicle further comprises at least two propulsors separate from the one or more blowers, and controlling at least partially yaw of the vehicles by differential thrust in the at least two propulsors.
19. The method of any one of claims 16-18, wherein the vehicle further an elevator at the tail of the airframe, and controlling at least partially a pitch of the vehicle by controlling a pitch of the elevator.
20. The method of any one of claims 16-19, further comprising modulating a pressure underneath each airfoil via control of a separate blower operably connected to that airfoil.21 . The method of claim 20, further comprising controlling at least partially and / or stabilizing at least partially the vehicle by modulating the pressure underneath each airfoil, relative to the other airfoils and / or a surface.