WO2022040463A1 - Profils aérodynamiques et véhicules incorporant ces derniers - Google Patents

Profils aérodynamiques et véhicules incorporant ces derniers Download PDF

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Publication number
WO2022040463A1
WO2022040463A1 PCT/US2021/046767 US2021046767W WO2022040463A1 WO 2022040463 A1 WO2022040463 A1 WO 2022040463A1 US 2021046767 W US2021046767 W US 2021046767W WO 2022040463 A1 WO2022040463 A1 WO 2022040463A1
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WO
WIPO (PCT)
Prior art keywords
airfoil
vehicle
channel
airfoils
blowers
Prior art date
Application number
PCT/US2021/046767
Other languages
English (en)
Inventor
Kelly ECHOLS
Randall PETERSEN
Aaron FOWLKS
Aaron BJELKA
Dawson WANGSGARD
Dylan LUND
Original Assignee
Levanta Tech Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Levanta Tech Llc filed Critical Levanta Tech Llc
Priority to EP21859158.4A priority Critical patent/EP4200204A4/fr
Publication of WO2022040463A1 publication Critical patent/WO2022040463A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/04—Air-cushion wherein the cushion is contained at least in part by walls
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/04—Air-cushion wherein the cushion is contained at least in part by walls
    • B60V1/046—Air-cushion wherein the cushion is contained at least in part by walls the walls or a part of them being rigid
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/08—Air-cushion wherein the cushion is created during forward movement of the vehicle by ram effect
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60V—AIR-CUSHION VEHICLES
    • B60V1/00—Air-cushion
    • B60V1/11—Stability or attitude control
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/16—Frontal aspect
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings

Definitions

  • the present disclosure relates to aerospace technology, in particular to airfoils and vehicles incorporating the same.
  • FIG. 1 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 100.
  • FIG. 2 illustrates a front view of the airfoil 100.
  • FIG. 3 illustrates a side view of the airfoil 100.
  • FIG. 4 illustrates a cross-sectional side view of the airfoil 100 taken along the lateral centerline of the airfoil 100.
  • Fig. 5 illustrates an underneath perspective view of the airfoil 100.
  • Fig. 6 illustrates a lateral centerline cross-sectional view of a variation of the airfoil 100.
  • Fig. 7 illustrates a lateral centerline cross-sectional view of the airfoil 100a depicting the nozzle 140 extended from within the channel 130.
  • Fig. 8 illustrates an underneath perspective view of the airfoil 100a with the nozzle 140 extended.
  • FIG. 9 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 200.
  • Fig. 10 illustrates a front view of the airfoil 200.
  • Fig. 11 illustrates a side view of the airfoil 200.
  • Fig. 12 illustrates a cross-sectional slice of the airfoil 200 taken along the lateral centerline of the airfoil 200.
  • Fig. 13 illustrates an underneath perspective view of the airfoil 200.
  • FIG. 14 illustrates a perspective view of a variation of the airfoil 200, the airfoil 200a, with the flap 216 downward oriented.
  • Fig. 15 illustrates a cross-sectional slice of the airfoil 200a.
  • FIG. 16 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 200b.
  • Fig. 17 illustrates a cross-sectional slice of the airfoil 200b with the vent 219 closed by the flap 218, taken along the lateral centerline of the airfoil 200b.
  • Fig. 18 illustrates a cross-sectional slice of the airfoil 200b with the vent 219 open, taken along the lateral centerline of the airfoil 200b.
  • Fig. 19 illustrates a perspective view from above of one embodiment of a vehicle disclosed herein, vehicle 300.
  • Fig. 20 illustrates an underneath perspective view of the vehicle 300 from below.
  • Fig. 21 illustrates a perspective view from above of another embodiment of a vehicle disclosed herein, vehicle 300a.
  • Fig. 22 illustrates an underneath perspective view of the vehicle 300a.
  • Fig. 23 illustrates a cross-sectional side view of the vehicle 300a taken along the lateral centerline.
  • Fig. 24 depicts a plot comparing lift generated as forward velocity increases at various heights off the ground with no air pushed through the channel, which simulates forward velocity, for the airfoil 200.
  • Fig. 25 depicts a plot showing lift force as a function of mass flow through the channel for the airfoil 200.
  • Fig. 26 depicts wind tunnel data for an embodiment of the airfoil disclosed herein.
  • Fig. 27 depicts the wind tunnel setup and 3D-printed model.
  • Fig. 28 depicts the CFD-determined percent increase in lift between two different embodiments of the airfoils disclosed herein at one height above a surface.
  • Fig. 29 depicts the CFD-determined percent increase in lift between two different embodiments of the airfoils disclosed herein at a second height above a surface.
  • Rotary-wing aircraft such as the quadcopters commonly used as drones, have the benefit of vertical take-off and landing (VTOL); however, they tend to have limited range due to inefficiencies associated with horizontal movement. Fixed wing aircraft are more efficient at horizontal movement and tend to have better range and speed than rotary-wing aircraft. However, fixed-wing aircraft typically need runways for take-off and landing.
  • VTOL vertical take-off and landing
  • the airfoils disclosed herein can be used for hovering, ground effect flight, and flight above ground effect.
  • the airfoils utilize blown air (or another fluid, such as an exhaust gas) for hovering.
  • the airfoil design provides lift.
  • the blown air can be turned off or directed elsewhere, when sufficient forward speeds are achieved to provide all of the necessary lift.
  • Vehicles incorporating the airfoils disclosed herein can approach the efficiencies and range of fixed wing aircraft (or perhaps exceed those efficiencies when flying in ground effect), but with instantaneous hover capability, removing the need for a runway.
  • 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.
  • “fluidically connected to” or “fluidically 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.
  • proximal is used herein to refer to “near” or “at” the object disclosed.
  • the airfoil has an upper surface and a lower surface and is configured for operative connection to an airframe via the upper surface of the airfoil.
  • the airfoil has a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is configured for fluidic communication with one or more blowers.
  • the upper surface and the lower surface preferably extend laterally to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil.
  • the airfoil may 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.
  • Ventehicles including the airfoils may have an airframe operatively connected to one or more blowers. Fluid provided by the one or more blowers into the channels of each of the airfoils generates lift for the vehicles.
  • the blowers may supply fluid with sufficient pressure to facilitate hover of the vehicles.
  • the channel may include a straight tube.
  • the channel includes a swept tube wherein a lower orifice of the channel is offset relative to an upper orifice of the channel.
  • the airfoil can include a selectively openable vent located in the upper surface of the airfoil and rearward of an upper orifice of the channel and wherein the vent is in fluidic communication with the channel, whereby when the vent is in an open position, fluid provided into the channels exits at least partially through the vent and over the upper surface of the airfoil.
  • a centerline of the airfoil has a stationary angle of attack of 5° to 25°, of 5° to 20°, of 5° to 15°, of 10° to 20°, or of 10° to 15°.
  • the first and second arcuate wingtips may have a stationary angle of attack of zero or near zero.
  • Methods of hovering a vehicle are also disclosed herein.
  • the methods include providing multiple airfoils operably connected to an airframe of a vehicle, wherein each airfoil comprises an upper surface and a lower surface extending laterally to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil.
  • Each airfoil is configured for operative connection to the airframe via the upper surface of the airfoil.
  • the airfoil includes a channel extending through the upper surface and the lower surface of the airfoil, wherein an upper orifice of the channel is configured for fluidic communication with one or more blowers.
  • the airfoil is designed such that moving the vehicle forward directs atmospheric air over and under each of the airfoils and provides additional lift for the vehicle.
  • FIG. 1 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 100.
  • Fig. 2 illustrates a front view of the airfoil 100.
  • Fig. 3 illustrates a side view of the airfoil 100.
  • Fig. 4 illustrates a cross-sectional side view of the airfoil 100 taken along the centerline of the airfoil 100.
  • Fig. 5 illustrates an underneath perspective view of the airfoil 100.
  • the airfoil 100 has an upper surface 110 and a lower surface 120 and is configured for operative connection to an airframe via the upper surface 110 of the airfoil 100.
  • the airfoil 100 has a channel 130 extending from the upper orifice 131 in the upper surface 110 to the lower orifice 131 in the lower surface 120 of the airfoil 100.
  • the channel 130 is configured for fluidic communication with one or more blowers. For example, fresh air or exhaust gas supplied by blowers may be blown through the channel 130.
  • the upper surface 110 and the lower surface 120 extend laterally to first arcuate wingtip 114 and second arcuate wingtip 115.
  • the upper orifice 131 protrudes upwards from the upper surface 110.
  • the upper orifice 131 may be flush with the upper surface 110.
  • the upper orifice may be operably connected to an airframe and/or a blower via a flange, a rigid aerotube (i.e., aerodynamic structural tube that both provides mechanical attachment to the airframe and fluidic connection with the blower), flexible tubing, or other structure for conveying fluid from a blower to the channel 130.
  • the channel 130 is a straight tube.
  • the centerline of the airfoil 100 has a stationary angle of attack of 7° (i.e., alpha equals 7°).
  • the stationary angle of attack refers to the angle of attack of the airfoil when the airfoil is not moving, such as when an aircraft utilizing the airfoil is stationary.
  • the angle of attack is the angle of imaginary line “c,” the “chord line,” extending from the leading edge 112 to the trailing edge 113 relative to horizontal.
  • the first and second arcuate wingtips 114 and 115 have a stationary angle of attack of zero. Or stated another way, the edges of the first and second arcuate wingtips 114 and 115 are horizontal when a vehicle utilizing the airfoil is stationary.
  • the trailing edge 113 and the first and second arcuate wingtips 114 and 115 are separate edges that join at points.
  • the trailing edge 113 can extend smoothly and continuously to the leading edge 112, such as in a continuous arc. This applies to all of the airfoil embodiments disclosed herein.
  • Fluid can be supplied through the channel 130 with sufficient volume and pressure to lift the airfoil 100 (and a vehicle attached thereto) off the surface. Additionally, as fluid exits the channel 130 and the airfoil 100 elevates, at least a portion of the fluid may accumulate in the concave region 125 and aid a pressure build up under the airfoil 100.
  • FIGs. 6-8 illustrate a variation of the airfoil 100, airfoil 100a.
  • Airfoil 100a includes an extendable and retractable nozzle 140.
  • Fig. 6 illustrates a centerline cross-sectional view of the airfoil 100a depicting the nozzle 140 retracted within the channel 130.
  • Fig. 7 illustrates a centerline cross-sectional view of the airfoil 100a depicting the nozzle 140 extended from within the channel 130.
  • Fig. 8 illustrates an underneath perspective view of the airfoil 100a with the nozzle 140 extended.
  • the nozzle 140 extends close to the horizontal plane defined by the trailing edge 113 and the first and second arcuate wingtips 114 and 115. Alternatively, the nozzle 140 can be flush with the plane defined by those edges or it can extend beyond those edges.
  • the nozzle 140 can direct fluid from one or more blowers towards a surface (such as the ground, water, or other takeoff surface). The nozzle 140 directs fluid from the channel 130 in close proximity to the surface. This may reduce the volume and/or pressure of the fluid needed to achieve hover.
  • the nozzle 140 can be retracted and the airfoil 100a function the same as the airfoil 100.
  • the nozzle 140 is permanently extended.
  • the nozzle 140 includes a foot 141 at the end of the nozzle 140.
  • the illustrated foot 141 aligns the end of the nozzle 140 with the lower surface 120.
  • the illustrated nozzle 140 is an open tube and the foot 141 surrounds the perimeter.
  • the foot 141 provides increased surface area proximal the end of the nozzle 140.
  • the nozzle 140 and the foot 141 can be capped off. Fluid could be discharged from slits, holes, or other apertures in the underside of the foot 141.
  • the foot 141 could be made of a flexible material that inflates with fluid blown through the nozzle 140 and deflates when fluid is not pushed into it.
  • FIG. 9 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 200.
  • Fig. 10 illustrates a front view of the airfoil 200.
  • Fig. 11 illustrates a side view of the airfoil 200.
  • Fig. 12 illustrates a cross-sectional slice of the airfoil 200 taken along the centerline of the airfoil 200.
  • Fig. 13 illustrates an underneath perspective view of the airfoil 200.
  • the airfoil 200 has an upper surface 210 and a lower surface 220 and is configured for operative connection to an airframe via the upper surface 210 of the airfoil 200.
  • the airfoil 200 has a channel 230 extending from the upper orifice 231 in the upper surface 210 to the lower orifice 231 in the lower surface 220 of the airfoil 200.
  • the channel 230 is configured for fluidic communication with one or more blowers. For example, fresh air or exhaust gas supplied by blowers may be blown through the channel 230.
  • the upper surface 210 and the lower surface 220 extend laterally to first arcuate wingtip 214 and second arcuate wingtip 215.
  • the upper orifice 231 protrudes upwards from the upper surface 210. In other variations, the upper orifice 231 may be flush with the upper surface 210.
  • the upper orifice may be operably connected to an airframe and/or a blower via a flange, a rigid aerotube (i.e., aerodynamic structural tube that both provides mechanical attachment to the airframe and fluidic connection with the blower), flexible tubing, or other structure for conveying fluid from a blower to the channel 230.
  • a rigid aerotube i.e., aerodynamic structural tube that both provides mechanical attachment to the airframe and fluidic connection with the blower
  • flexible tubing or other structure for conveying fluid from a blower to the channel 230.
  • the channel 230 is a swept tube.
  • the lower orifice 232 of the channel 230 is offset relative to the upper orifice 231 .
  • the centerline of the airfoil 200 has a stationary angle of attack of 7°.
  • the first and second arcuate wingtips 214 and 215 have a stationary angle of attack of zero. Or stated another way, the edges of the first and second arcuate wingtips 214 and 215 are horizontal when a vehicle utilizing the airfoil is stationary.
  • the trailing edge 213 and the first and second arcuate wingtips 214 and 215 are separate edges that join at points. Alternatively, the trailing edge 213 can extend smoothly and continuously to the leading edge 212, such as in a continuous arc.
  • Fluid can be supplied through the channel 230 with sufficient volume and pressure to lift the airfoil 200 (and a vehicle attached thereto) off a surface. Additionally, as fluid exits the channel 230 and the airfoil 200 elevates, at least a portion of the fluid may accumulate in the concave region 225 and aid a pressure build up under the airfoil 200.
  • Figs. 14 and 15 illustrate a variation of the airfoil 200, airfoil 200a with an adjustable flap 216 operably connected to the trailing edge 213.
  • Fig. 14 illustrates a perspective view of the airfoil 200a with the flap 216 downward oriented.
  • Fig. 15 illustrates a cross-sectional slice of the airfoil 200a.
  • flap 216 can be used with any of the airfoils disclosed herein.
  • air may separate from the upper surface 210, causing a reduction in lift. Even if air is not separating from the upper surface 210, it may be beneficial to increase the speed of the air flowing over the upper surface 210 to thereby reduce the pressure and increase the lift.
  • FIGs. 16-18 illustrate a variation of the airfoil 200, airfoil 200b with an adjustable flap 218 and a vent 219.
  • Fig. 16 illustrates a perspective view of one embodiment of an airfoil disclosed herein, airfoil 200b.
  • Fig. 17 illustrates a cross- sectional slice of the airfoil 200b with the vent 219 closed by the flap 218, taken along the centerline of the airfoil 200b.
  • Fig. 18 illustrates a cross-sectional slice of the airfoil 200b with the vent 219 open, taken along the centerline of the airfoil 200b. With the vent 219 open, fluid blown through the channel 230 is at least partially redirected out the vent 219 and over the upper surface 210.
  • vent 219 may be implemented a number of different ways, such as multiple vents 219 located in the upper surface 210. Additionally, the flap 218 may only open outward, without occluding fluid flow in the channel 230.
  • vent 219 could penetrate entirely through the airfoil 200, forming a separate channel from the lower surface 220 to the upper surface 210 without fluidically connecting with the channel 230.
  • air present near the lower surface 220 could travel through the vent 219 and over the upper surface 210 (such as over the trailing portion of the upper surface 210), aiding in lift.
  • the concept of the vent 219 may be applied to any of the airfoil embodiments disclosed herein.
  • Figs. 19-23 illustrate non-limiting generalized embodiments of vehicles incorporating the airfoil 100.
  • Fig. 19 illustrates a perspective view of a vehicle 300 from above.
  • Fig. 20 illustrates a perspective view of a vehicle 300 from below.
  • the vehicle 300 includes an airframe 350 operatively connected to one or more blowers (not shown).
  • the vehicle 300 includes four airfoils 100, two in the front and two in the back.
  • Each airfoil 100 is rigidly secured to the airframe 350 via an aerotube 360 in fluidic communication with the one or more blowers (not shown) and with the channel 130 of each airfoil 100. Fluid supplied by the one or more blowers is blown through the channels 130, providing lift and allowing the vehicle 300 to hover.
  • Forward propulsion provides forward movement for the vehicle 300.
  • Vehicle 300 could be configured for manned or unmanned operation.
  • the vehicle 300 may be sized to accommodate a single pilot, two pilots, numerous passengers, relatively small cargo, palletized cargo, containerized cargo, or combinations of the foregoing.
  • Fig. 21 illustrates a perspective view of a vehicle 300a from above.
  • Fig. 22 illustrates a perspective view of a vehicle 300a from below.
  • Fig. 23 illustrates a cross-sectional side view of the vehicle 300a taken along the centerline.
  • the vehicle 300a includes four airfoils 100, two in the front and two in the back. Each airfoil 100 is rigidly secured to the airframe 350a via an aerotube 360a in fluidic communication with the blowers 370 and with the channel 130 of each airfoil 100.
  • the blowers 370 include a fan 371 mechanically driven by a jet turbine 375.
  • Atmospheric air is drawn into the fan 371 and directed via the front two aerotubes 360a to the channels 130 of the adjacent front two airfoils 100.
  • the fan 371 is driven by a shaft powered by the jet turbine 375.
  • Atmospheric air and fuel are applied to the jet turbine 375.
  • the jet turbine 375 includes a compressor (not separately illustrated). The compressor compresses the exhaust from the jet turbine 375 and is operably connected to the rear aerotubes 360a and rear two channels 130 of the rear airfoils 100. The compressed exhaust is directed through the channels 130.
  • the air and exhaust supplied to the channels 130 provide lift, allowing the vehicle 300a to hover.
  • the jet turbine 375 also provides propulsion for forward motion of the vehicle 300a.
  • the air supplied by the fan 371 through the forward channels 130 can be varied or entirely eliminated or closed off.
  • the exhaust supplied by the turbine 371 through the rear channels 130 can be varied and redirected, such as to aid forward propulsion.
  • a benefit of the design of the vehicle 300a is that a single propulsion system is used to provide both hover and forward motion. This can provide weight-to-thrust ratio benefits over designs that use separate hover and flight power systems (e.g., separate rotors for take-off and flight) or that require bulky equipment to rotate power equipment from hover mode to flight mode (e.g., motors for rotating rotors from take- off/landing mode to flight mode).
  • separate hover and flight power systems e.g., separate rotors for take-off and flight
  • bulky equipment to rotate power equipment from hover mode to flight mode e.g., motors for rotating rotors from take- off/landing mode to flight mode.
  • the propulsion system of vehicle 300a can also be used with vehicle 300.
  • the vehicle 300a can be sized to be ridden like a motorcycle or ATV. The controls, windshield, seats, etc. are not illustrated.
  • the vehicle 300a can also be enlarged to accommodate one or more passengers, cargo, or both within the airframe 350a.
  • the vehicle 300a can be configured for manned or unmanned operation.
  • a variety of power supplies could be used.
  • the jet turbine could be electrically driven or hydrogen or natural gas powered.
  • Hydrogen fuel cells or batteries could be used to provide electricity to electric motors.
  • a horizontal fan such as a central centrifugal fan, could be used to supply airflow to the various airfoils 100.
  • a separate forward propulsion system would be required, such as externally-mounted rotors or turbines.
  • a drone could include a central compartment for storage of cargo. The central fan could be mounted above the central compartment and the airfoils mounted outside the central compartment.
  • a vehicle utilizing the airfoils could be an exosuit worn by a single individual.
  • a mechanized exosuit could provide the airframe (e.g., a support framework along the arms, legs, and torso with mechanized joints) for supporting the airfoils, blowers, and power supply.
  • a central fan or jet turbine could supply air or exhaust to airfoils mounted at the hands and feet (e.g., one airfoil for each hand and each foot).
  • two airfoils are fluidically connected to a single blower 370 (e.g., fan 371 or jet turbine 375).
  • a separate blower may be operably connected to each airfoil.
  • Each airfoil could be structurally connected to the other airfoils, such as via a frame.
  • individual airfoils could also be individually mounted to an object to be transported. For example, a storage container as it is being offloaded from a transport ship could be outfitted with temporary airfoils that each have their own blower and power supply (for example, a magnetic L-shaped bracket could secure the airfoil to a bottom edge of a steel shipping container).
  • Separate power supplies and forward propulsion fans could also be magnetically attached to the shipping container.
  • the shipping container could then be flown in ground effect over the water from the transport ship (anchored a distance from the port) to the port.
  • the shipping container could potentially be flown/hovered directly to a distribution center.
  • the airfoils are fixed to a vehicle.
  • the airfoils can be articulatable.
  • the angle of attack during takeoff could be adjusted.
  • the lateral angles of individual or all of the airfoils could be adjusted to aid in steering a vehicle.
  • the ability to freely pivot each airfoil from its upper surface may provide enhanced maneuverability when flying in ground effect, as compared to mono-wing-type ground effect vehicles.
  • Vehicle utilizing the airfoils disclosed herein may have improved stability in ground effect compared to conventional ground effect vehicles. Having multiple airfoils may stabilize vehicles, as compared to a single airfoil.
  • the airfoils disclosed herein may be made of any material sufficiently strong and lightweight, such as fiberglass, carbon fiber, titanium, and/or aluminum.
  • the upper and lower surfaces may be rigid. Alternatively, the upper and lower surfaces may have flexible regions. For example, at sufficient speeds, it may be desirable to change the shape of the airfoil to achieve a more conventional wing shape.
  • the laterally arcuate shape of airfoil could be modulated with a piston and rod attached to the upper surface of the shroud, on each side lateral to the channel. As the pistons contract, the lateral concavity of the airfoil could be reduced. Additionally, the angle of attack of the airfoil could be adjusted by actuators operatively coupled to the airfoil and the airframe.
  • Vehicles including the airfoils disclosed herein could also include conventional wings.
  • the conventional wings could be permanently extended from the airframe or could be selectably deployable. Deployment of the wings could occur by extension of retracted wing portions or by lowering wings kept in a vertical position.
  • the airfoils disclosed herein could function as landing gear, so to speak. Fluid could be blown through the channels of the airfoils during take-off, acceleration, deceleration, and landing. During flight, fluid flow through the channels could be blocked or directed to forward propulsion.
  • the airfoils connections to the airframe could be designed to retract the airfoils within the airframe or rotate the airfoils up against the fuselage of the airframe.
  • Fig. 24 depicts a plot comparing lift generated as forward velocity increases at various heights off the ground with no air pushed through the channel, which simulates forward velocity.
  • the dashed line represents the required 890 N of lift force theorized to achieve hover.
  • Fig. 25 depicts a plot showing lift force as a function of mass flow through the channel.
  • the forward velocity was set at 42.19 m/s and the height at 400 mm. This plot shows the increase in lift force as the mass flow increases.
  • the solid horizontal line represents the 890 N of lift force needed to create hover for the presumed weight.
  • a 1/7 th scale model of the 1 m 2 airfoil 200 design without the channel was 3D printed and tested in a small wind tunnel at the 3 highest speeds the wind tunnel could perform for angles of attack between 0 — 20 degrees (relative to the angle of attack of the first and second arcuate wingtips).
  • Fig. 27 depicts the wind tunnel setup and 3D-printed model. Due to testing constraints, the airfoil was mounted upside down and no channel flow was applied. [0099] As discussed above, it was determined that in certain flow regimes, the pressure beneath the airfoil was decreased because of fast air moving beneath it. A flap was added at the rear of the foil (see Figs. 14 and 15 and airfoil 200a) and computational fluid dynamics testing performed.
  • Figs. 28 and 29 represent the percent increase in lift between the original results and the results obtained with the flap.
  • a vehicle comprising: an airframe operatively connected to one or more blowers; and multiple airfoils, wherein each airfoil comprises an upper surface and a lower surface extending laterally to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, wherein each airfoil is operatively connected to the airframe via the upper surface of each airfoil, wherein each 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.
  • each airfoil further comprising a nozzle extending downward from the lower surface of the airfoil in fluidic communication with the channel of the airfoil.
  • each airfoil channel comprises a swept tube wherein a lower orifice of the channel is offset relative to an upper orifice of the channel.
  • each airfoil includes a selectively openable vent located in the upper surface of the airfoil and rearward of an upper orifice of the channel and wherein the vent is in fluidic communication with the channel, whereby when the vent is in an open position, fluid provided by the one or more blowers into the channels exits at least partially through the vent and over the upper surface of the airfoil and thereby generates lift for the vehicle.
  • each airfoil is rigidly secured to the airframe via an aerotube in fluidic communication with the one or more blowers and with the channel of the airfoil.
  • An airfoil comprising an upper surface and a lower surface extending laterally to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil, the airfoil configured for operative connection to an airframe via the upper surface of the airfoil, the airfoil comprising a channel extending through the upper surface and the lower surface of the airfoil, wherein an upper orifice of the channel is configured for fluidic communication with one or more blowers.
  • An airfoil comprising an upper surface and a lower surface and configured for operative connection to an airframe via the upper surface of the airfoil, the airfoil comprising a channel extending from the upper surface to the lower surface of the airfoil, wherein the channel is configured for fluidic communication with one or more blowers, and comprising a nozzle extending downward from the lower surface of the airfoil in fluidic communication with the channel of the airfoil.
  • the airfoil of paragraph [00125] wherein the upper surface and the lower surface extend laterally to first and second arcuate wingtips defining a concave region bounded by the lower surface of the airfoil.

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  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Sont divulgués ici des profils aérodynamiques et des véhicules incorporant ces derniers. Les profils aérodynamiques comprennent une surface supérieure et une surface inférieure. Chaque profil aérodynamique est conçu de façon à être relié de manière fonctionnelle à une cellule par l'intermédiaire de la surface supérieure du profil aérodynamique. Chaque profil aérodynamique comprend un canal s'étendant de la surface supérieure à la surface inférieure du profil aérodynamique. Chaque canal est conçu pour une communication fluidique avec une ou plusieurs soufflantes.
PCT/US2021/046767 2020-08-19 2021-08-19 Profils aérodynamiques et véhicules incorporant ces derniers WO2022040463A1 (fr)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3361386A (en) * 1965-08-09 1968-01-02 Gene W. Smith Vertical or short take-off and landing aircraft
US6860449B1 (en) * 2002-07-16 2005-03-01 Zhuo Chen Hybrid flying wing
US20120237341A1 (en) * 2009-12-02 2012-09-20 Jean-Michel Simon Lift and propulsion device, and heavier-than-air aircraft provided with such a device
US20190016453A1 (en) * 2017-07-12 2019-01-17 Donatas SKULSKIS Vertical take-off and landing (vtol) aircraft and a propulsion system for a vehicle vertical take-off and landing (vtol)
US20190023389A1 (en) * 2017-07-21 2019-01-24 General Electric Company Vertical Takeoff and Landing Aircraft

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB951186A (en) * 1962-12-18 1964-03-04 Temple Leslie Vertical take-off and landing aircraft
DK149224C (da) * 1973-01-27 1986-08-11 Guenther W Joerg Vingefartoej med to i indbyrdes afstand bag hinanden anbragte baereflader
US5566775A (en) * 1992-08-10 1996-10-22 Schoell; Harry Skirted surface effect vehicle
FR3008383B1 (fr) * 2013-07-12 2017-11-24 Hutchinson Dispositif de sustentation a soufflante(s) axiale(s), et aerodyne equipe d'un tel dispositif

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3361386A (en) * 1965-08-09 1968-01-02 Gene W. Smith Vertical or short take-off and landing aircraft
US6860449B1 (en) * 2002-07-16 2005-03-01 Zhuo Chen Hybrid flying wing
US20120237341A1 (en) * 2009-12-02 2012-09-20 Jean-Michel Simon Lift and propulsion device, and heavier-than-air aircraft provided with such a device
US20190016453A1 (en) * 2017-07-12 2019-01-17 Donatas SKULSKIS Vertical take-off and landing (vtol) aircraft and a propulsion system for a vehicle vertical take-off and landing (vtol)
US20190023389A1 (en) * 2017-07-21 2019-01-24 General Electric Company Vertical Takeoff and Landing Aircraft

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP4200204A4 *

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EP4200204A4 (fr) 2024-02-07

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