Aircraft with propellers positioned at the wingtips

Abstract

An aircraft is provided that includes an airframe having a first wing with a curved wingtip positioned above a second wing with a curved wingtip. A rotor assembly positioned between the curved wingtips between the first and second wings can be utilized to provide both vertical thrust for vertical takeoff of the aircraft and autorotation to generate electrical energy for recharging an onboard power source. The first wing can be formed in a V-shape. An additional rotor assembly can be included in a rotatable canard that provides forward and vertical thrust to the aircraft.

Description

[Technical field]

[0001] This application claims priority to U.S. Provisional Patent Application No. 62 / 956,227, filed December 31, 2019.

[0002] The present invention relates generally to aircraft and propellers utilized therein, and more particularly to wingtip-positioned propellers operatively engaged to electric motor-generators configured to both provide thrust to the aircraft for flight and to capture wingtip vortex energy and convert it to electrical power during the aircraft's flight. [Background technology]

[0003] In recent years, with the advent of unmanned aerial vehicles, many conventional subsonic runway takeoff and vertical takeoff air vehicles are propeller driven for effectiveness. In such air vehicles, the propeller is engaged with a rotating hub having radially projecting blades that rely on the motion of an engaged motor to generate lift and drag. The propeller converts rotational force from an electric motor operatively connected to a power source into linear thrust that propels the air vehicle upward and forward depending on the motion of the air vehicle at that time.

[0004] When operatively powered by a power source such as a battery and / or a slow-discharging capacitor, such a thrust-producing propeller gradually increases the airflow and reduces the air pressure up to the propeller plane, where the air pressure increases abruptly in the downstream flow which then gradually decreases as it decreases to a free stream value upon reaching the rotating propeller plane.

[0005] Currently, such light unmanned or remotely controlled aircraft operate with vertical takeoff and landing during their operation, however, when equipped with landing gear, such vehicles are easily operated with conventional runway takeoff and landing operations.

[0006] In vertical operation, such aircraft conventionally utilize at least one, and preferably multiple, propellers operatively coupled to electric motors that are oriented to generate thrust in a vertical direction.

[0007] While moving vertically, control of the vehicle requires generating and varying thrust across multiple rotors and / or controlling the pitch angle of the rotor blades. To transition from vertical to horizontal flight, some aircraft tilt thrust-generating components or the entire vehicle, while other light aircraft utilize separate motor-driven propellers for each flight mode.

[0008] All of these systems require controllers to maintain the aircraft's orientation in flight, as well as to control the various wing surfaces and propellers to keep the aircraft in the air and move it vertically and horizontally in flight.

[0009] In view of the above, before describing at least one preferred embodiment of an aircraft system with wingtip-located propellers herein, it should be understood that the disclosed devices and systems are not limited in application to the details of use and the arrangement of components or steps set forth in the following description or illustrated in the drawings. The various arrangements and operations of the aircraft system disclosed herein are possible in other embodiments and can be practiced and carried out in various ways, all of which will become apparent to one of ordinary skill in the art once considering the information herein.

[0010] Furthermore, it should be understood that the phraseology and terminology used herein is for the purpose of explanation and should not be considered limiting. Thus, those skilled in the art will appreciate that the concepts on which the present disclosure is based can be readily utilized as the basis for other aircraft having wingtip-located propellers operatively engaged with wingtip-engaged motorized generators. It is therefore important that these equivalent structures and methods are considered to be within the scope of the embodiments, objectives, and claims of this specification, provided they do not depart from the spirit and scope of the present invention. Summary of the Invention [Problem to be solved by the invention]

[0011] In recent years, lightweight, propeller-driven aircraft have been widely used for both hobbyists and professionals, such as aerial observation, surveying, and photography. New designs show great promise for providing transportation of both cargo and people between multiple locations, especially those locations where vertical take-off and landing (VTOL) is utilized.

[0012] The aircraft and systems herein can be configured to operate in various modes of the systems and methods herein to provide higher cruising speeds combined with longer flight and coast time capabilities. Additionally, the aircraft configurations and operating systems herein provide for extension of both the range and flight capabilities of such aircraft. [Means for solving the problem]

[0013] In a particularly preferred mode of the aircraft system herein, the extended flight envelope is provided by including wingtip-positioned propellers, each of which is operatively engaged with an electric motor-generator. By wingtip-positioned propellers herein is meant that the propellers are operatively engaged with the motor-generators and positioned between the curved tip of a first upper wing and the tip of a second wing positioned below the first or upper wing. The wingtip-positioned propellers engaged with their respective motor-generators rotate in a substantially horizontal plane. By substantially horizontal plane is meant that the plane of rotation of each wingtip-positioned propeller is within 20° of the first and second wing planes.

[0014] When positioned between the respective curved wing tips, each propeller may be operated to provide lift to the aircraft when powered by an on-board power source. When unpowered, the propeller operatively positioned between two respective curved wing tips is operative to capture vortex energy from both the first and second wing tips. This vortex energy operates to rotate each propeller, and an operatively engaged motorized generator operates to harvest wind energy and convert it to electrical energy to recharge the on-board power source. Such on-board power sources are known, such as one or a combination of operatively connected batteries and / or capacitors.

[0015] In addition to capturing the vortex energy generated at each of the wing tips during level flight, experiments have shown that the propellers located at the wing tips also capture wind power generated from vortices from the wings and canards, as well as the propeller wake from the propeller engaged at the canard, as well as the ambient wind. Such wingtip positioning provides multiple means for generating and storing electricity for on-board power sources.

[0016] Additionally, the tip positioning of the propellers engaged with the respective engine generators may also be actuated to essentially provide regenerative braking or autorotation during the aircraft's forward motion descent. This occurs during autorotation of the propellers positioned at each wingtip from the airflow created during the aircraft's descent. This propeller rotation rotates the engaged engine generator to generate electrical current that can be delivered to recharge the on-board power source.

[0017] In addition to the mentioned preferred propellers operatively engaged to the motorized generators and oriented horizontally at the wing tips, in a particularly preferred mode herein, the aircraft may include a propeller driven by a motorized generator rotatably engaged to a forwardly positioned canard. While such a motor-driven propeller is merely engaged to the wing, positioning a canard engaged to the fuselage and positioned on the fuselage forward of both the first or upper wing and the second wing allows for a larger diameter horizontally rotating propeller at the wing tip, as well as directional control of thrust using actuators that rotate the canard.

[0018] When positioned in this manner, both canards are rotatable in engagement with the aircraft, thereby rotating the respective propeller planes operatively connected to the canard-mounted motorized generators. For vertical takeoff and landing, each propeller plane engaged with the canards can be rotated by rotating the respective canards to move the propeller plane between a vertical plane of orientation and a substantially horizontal plane. A substantially horizontal plane of orientation of the propellers means that the propeller plane engaged with the rotating canards is substantially parallel to the plane of the first and / or second wing. A vertical plane of orientation of the propellers engaged with the canards means that the plane of rotation of each such propeller is perpendicular or substantially perpendicular to the plane of the first and / or second wing. Thus, rotation of each canard rotates the motorized generators in the canards, which in turn rotates the plane of rotation of each propeller engaged with the respective motorized generator.

[0019] For horizontal or forward flight, the canards are rotatable to move the associated propeller planes between a substantially parallel plane and a substantially vertical plane of rotation of the propellers associated with each canard. Thus, rotation of each canard rotates the associated motor-generator, which in turn rotates the propeller planes associated with the motor-generators associated with their respective canards.

[0020] In the mode of the aircraft herein having motorized generators and with each propeller operably engaged to a motorized generator engaged to each respective canard, the canards can be rotated by a controller. During such rotation, each propeller can be rotated simultaneously between a substantially horizontal plane of rotation and a substantially vertical plane of rotation as needed at a particular moment of flight. This rotation of each propeller plane can thus be controlled to provide lift and / or forward thrust as needed by the aircraft during takeoff, forward thrust, or landing. Software running on the controller or in operative communication with the controller can operate actuators or motors to rotate each of the canards to provide the required lift and / or forward thrust during any period of the aircraft's flight. When power is not provided, the propellers located at the wing tips are autorotating, so that the propellers always provide lift, which can generate significant resistance to stalling the aircraft.

[0021] As will be appreciated, for vertical takeoff and landing, the plane of rotation of the propellers engaged to the canards can be substantially horizontal, as can the planes of rotation of the propellers engaged to the wingtips. Such an orientation allows for thrust from the four propellers to lift the aircraft off the ground during takeoff, and for the four propellers to automatically rotate to slow the descent during landing.

[0022] Once ascending, the plane of rotation of the propellers engaged to the canards can be rotated by controlled rotation of actuators engaged to each canard, thereby positioning the propellers engaged to the canards in a plane of rotation for providing forward thrust to the aircraft to generate lift from the first and second wings during flight. During vertical take-off and landing (VTOL), the propellers engaged to the two canards are rotated back to a substantially horizontal plane of rotation, and the electric generators engaged therewith are powered by an on-board power source to rotate the engaged propellers during descent and / or vertical take-off. The electric generators engaged to the two wingtip-positioned propellers are also powered by an on-board power source during VTOL.

[0023] Additionally, during level flight of the aircraft, the two canard-engaged motorized generators engaged with the propellers positioned at the wing tips are not powered and auto-rotate during this flight. When performing the sinusoidal regenerative flight path referred to herein, the canard-engaged motorized generators are powered and generate thrust from the attached propellers up to the highest point of the flight path. At the highest point, the power to the canard-engaged motorized generators is disconnected in descent. This allows the propellers on the canard-engaged motorized generators to auto-rotate against the relative wind created by gravity accelerating the aircraft downward. This gives the engaged motorized generators a rotation that can be utilized to generate electricity that is delivered to the on-board power source. At the bottom of the descent, power from the on-board power source can be reconnected to the two canard-engaged motorized generators, rotating the two canard-engaged propellers to provide forward thrust to enable the aircraft to climb back to the highest point.

[0024] An additional mode of the aircraft device herein is characterized by a first or upper wing having a V-shape or configuration. In this V-configuration, a central portion of the first or upper wing is engaged with a vertical stabilizer or tail extending from the aft end of the aircraft fuselage. From a central position, the first or upper wing extends, in a V-shape as viewed from above, toward the forward end of the fuselage where the canard is engaged with the respective curved wing tips. The curved wing tips of the V-shaped wing connect to a bearing about which a propeller positioned at the wing tip rotates, or to a housing of an electric motor generator, or in any manner to an electric motor generator and propeller positioned at the wing tip, holding the electric motor generator in a fixed position and allowing the engaged propeller to rotate. Of course, this can vary depending on the curvature of the respective wing tips, the material forming them, and other factors that will occur to those skilled in the art.

[0025] In experiments, it was found that this V-shaped first or upper wing provides additional lift during forward flight relative to a straight upper wing, because it has a longer extension than a wing that projects substantially at right angles or only at a slight angle from the fuselage. It was unexpectedly found that the V-shaped first wing propels the aircraft in flight more easily. The reduction in the force required for propulsion was observed from further testing due to the fact that the V-shaped first wing directs more air to the tail or vertical stabilizer during forward flight. Forward flight then requires less power to move the flaps and propel the aircraft, saving power and increasing flight time than would be possible with a substantially straight wing that projects substantially at right angles to the fuselage axis.

[0026] Thus, in one mode of the aircraft herein, substantial benefits are provided by positioning an engine generator engaged to a propeller rotating in the horizontal plane at the intersection of the curved wing tips to capture vortex energy during flight to recharge on-board power, and to generate power to recharge on-board power during the aircraft's descent. In a second mode of the aircraft herein, the addition of an engine generator engaged to the canard with a propeller that can change plane of rotation by controlled rotation of the canard provides additional power generation during vertical descent and the ability to provide thrust for vertical takeoff. In yet another preferred mode of the invention herein, the addition of a V-shaped first or upper wing to the overall configuration increases overall lift during forward flight, reducing the power required to propel the aircraft forward, thereby extending the available power for long flights.

[0027] With regard to the above description, before describing at least one preferred embodiment of an air vehicle having a wingtip-positioned propeller engaged with an engine-driven generator as disclosed herein, it should be understood that the invention is not limited to the application of the details of the structure and the arrangement of the components in the following description or illustrated in the drawings. The invention described herein is capable of other embodiments and can be practiced and carried out in various ways that will be apparent to those skilled in the art. Moreover, it should be understood that the phraseology and terminology employed herein is for the purpose of description and should not be regarded as limiting.

[0028] Thus, those skilled in the art will appreciate that the concepts based on the present disclosure may be readily utilized as the basis for other wingtip-positioned propeller-driven air vehicle structures, as well as canard-engaged propeller designs, and methods and systems for carrying out some of the objectives of the devices of the present disclosure, and it is important that these equivalent structures and methods be considered within the scope of the appended claims to the extent that they do not depart from the spirit and scope of the present invention.

[0029] As used in the claims to describe various inventive aspects and embodiments, "comprising" is meant to include, but is not limited to, the words following "comprising." Thus, the term "comprising" indicates that the recited elements are required or essential, but other elements may be optionally present or absent. "Consisting of" means to include and be limited to everything that follows the phrase "consisting of." Thus, the phrase "consisting of" indicates that the recited elements are required or essential, and that no other elements are present. "Consisting essentially of" is meant to include any elements recited after this phrase, and is limited to other elements that do not interfere with or contribute to the function or action specified in the disclosure for the recited elements. Thus, the phrase "consisting essentially of" indicates that the recited elements are required or essential, but other elements may be optionally present or absent depending on whether they affect the function or action of the recited elements. Finally, the term "substantially" means plus or minus ten percent, unless a size or dimension, or a particular part or configuration, is otherwise defined.

[0030] The goal of the present invention is to provide for the capture of wind vortex energy, propeller wake slipstream energy, from the driving rotor and ambient wind during aircraft flight, and the generation of electrical power through the positioning of motorized generators engaged to the wing tips operatively connected to the propellers.

[0031] Another goal of the present invention is to provide for the capture of wind energy during the descent of an aircraft via wind-driven rotation of wingtip-located motorized generators operatively engaged to the propellers, which auto-spin during descent to generate electricity.

[0032] An additional goal of the invention herein is to provide rotatable canards engaged to the airframe that are controllable to rotate the plane of rotation of the propeller for both vertical and horizontal flight by rotating an engine-driven generator operatively connected to the propeller.

[0033] It is yet another object of the invention herein to provide a dual wing aircraft having a substantially V-shaped first or upper wing to increase airflow to the horizontal stabilizer or tail during flight.

[0034] Other objects, features, and advantages of the present aircraft, as well as advantages over the current prior art, will become apparent from the following description and are achieved by the improvements described in this specification and the following detailed description which fully discloses the present invention, but should not be considered as limiting thereto.

[0035] The accompanying drawings, which are incorporated herein and form a part of this specification, illustrate some of the exclusive and non-exclusive examples of embodiments and / or features of the various modes of the aircraft of the invention herein, which may be utilized alone or in combination, as noted. The embodiments and figures disclosed herein are intended to be illustrative and not limiting. [Brief description of the drawings]

[0036] [Figure 1] FIG. 1 is a front perspective view of an aircraft system herein showing a preferred configuration of an engine-driven generator engaged to a propeller positioned between a curved tip of a first or upper wing and a curved tip of a second wing positioned below the first wing, and a V-shaped configuration of the upper or first wing. [Diagram 2] FIG. 1 is a top view of an aircraft herein showing a V-shaped first or upper wing, showing a horizontal plane of rotation of a propeller positioned at the wingtip engaged to an engine-driven generator, and showing the canard being rotated to a position having a propeller engaged to the engine-driven generator in a substantially vertical plane of rotation. [Diagram 3] 3 is a representation of the aircraft system of FIGS. 1 and 2 showing the canard rotating from the horizontal position of FIG. 1 to a vertical position, thereby positioning a propeller connected to the canard in either a vertical plane of rotation, or a horizontal plane, or various planes of rotation therebetween. [Figure 4] FIG. 4 is a representation of an aircraft system herein of a similar type to FIGS. 1-3 but showing that the first or upper wing extends substantially perpendicular to the axis of the fuselage. [Diagram 5] FIG. 1 shows a particularly preferred positioning of a second rotor with a propeller engaged to an electric motor, operably connected to the curved tip of the first or upper wing and to the curved tip of the second wing positioned below it, such as by bearings and / or connections to the housing of the electric motor. [Figure 6] FIG. 2 illustrates an exemplary mode of operation of an aircraft system herein during vertical takeoff and landing. [Figure 7] FIG. 1 illustrates a mode of operation of the aircraft system herein in which vortex energy may be captured during forward flight and / or gliding to spin propellers positioned at the wingtips to generate electricity during flight. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0037] Other aspects of the aircraft systems herein will be more readily understood when considered in conjunction with the accompanying figures and the following detailed description, none of which should be considered limiting.

[0038] In this description, terms such as up, upward, down, below, front, back, top, upper, bottom, lower, left, right, first, second, and other such directional terms refer to the way the device appears oriented in the figures and are used merely for convenience. They are not intended to be limiting or to require that the aircraft device be used or positioned in any particular orientation.

[0039] 1-7, where like components are identified with the same numerals. In FIG. 1, a front perspective view of an aircraft system 10 herein is seen showing a preferred configuration having a rotor assembly including motor-driven generators 12 and 13 operably connected to a propeller 14 having a plurality of blades 16.

[0040] In a particularly preferred mode of the system 10, a first rotor assembly 11 having a first motor-driven generator 12 operably engaged to a propeller 14 having blades 16, and a second rotor assembly 15 having a second motor-driven generator 13 operably engaged to the propeller 14 having blades 16 are both operably positioned at an engagement between a first curved wing tip 18 of a first wing 20, i.e., an upper wing, and a second curved wing tip 22 of a second wing 24 positioned below the first wing 20. As shown, the first rotor assembly 11 with the motor-driven generator 12 is positioned on the right side of the airframe 26, and the second rotor assembly 15 with the second motor-driven generator 13 is positioned on the left side of the airframe 26.

[0041] As shown, both the first rotor assembly 11 and the second rotor assembly 15 are positioned at engagements located between the distal ends of the first curved wing 18 at both ends of the first wing 20 and the distal ends of the second curved wing 22 at both ends of the second wing 24, respectively. Such connection of the curved wing tips 18 and 22 to the first rotor assembly 11 and the second rotor assembly 15 may be made to the housing of the respective motor-driven generator 12 or 13, or may be a connection of one or both curved wing tips 18 and 20 to a housing surrounding the motor-driven generator 12 or 13, or may utilize fasteners or connectors therebetween, or may be a connection of one curved wing tip 18 to a bearing or mounting on which the propeller 14 rotates, and a connection of the other wing tip 22 to the exterior of the motor-driven generator 12 or 13. Thus, the connection of either the first rotor assembly 11 or the second rotor assembly 15, each having a respective motor generator engaged with a propeller, between both wing tips 18 and 20 means that the respective motor assemblies 11 and 15 are held securely and fixed in place, which allows sufficient area for the propeller 14, which is operably engaged with the motor generator, to rotate in a horizontal plane of rotation extending into the space 31 between the first blade 20 and the second blade 24.

[0042] The propellers 14 operatively engaged with the first and second rotor assemblies 11, 15 rotate the engaged blades 16 in a substantially horizontal plane when the engine generators 12 and 13 are in an energized mode and are supplied with power from the on-board power supply 34. As mentioned, the horizontal plane extends into the space 31 between the two blades on one side of both rotating assemblies.

[0043] During forward flight of the aircraft, vortex currents generated at the ends of both the first wing 20 and the second wing 24 engaged at the curved wing tips can impart a rotational force to the blades 16 and the propeller 14. This rotational force turns both the first motor-generator 12 in the first rotor assembly 11 and the second motor-generator 13 in the second rotor assembly 15, thereby generating electrical energy that is transferred to the power source 34 and serves to recharge the power source 34.

[0044] During the aircraft's descent upon landing, airflow communicating against the blades 16 of the propeller 14 provides a force to rotate the first engine-powered generator 12 and the second engine-powered generator 13, causing both to autorotate and slow the descent while simultaneously generating power that can be conveyed to the power source 34. As mentioned, the power source 34 may be a battery and / or a capacitor, or other power storage reservoir known in the art, alone or in combination, operatively connected to transmit and receive power via wire connections to the first engine-powered generator 12, the second engine-powered generator 13, and the third rotor assembly 45 having a third engine-powered generator 46, and the fourth rotor assembly 47 having a fourth engine-powered generator 48.

[0045] Although the aircraft herein is depicted with a third rotor assembly 45 and a fourth rotor assembly 47 engaged to the canards 38 and 40 at the front portion of the fuselage 26 to provide forward thrust for horizontal flight of the aircraft, the aircraft may also operate without the canards 38 and 40 and obtain great utility from a two wing configuration with the first rotor assembly 11 and the second rotor assembly 15 mounted between the two wings at curved wing tips. Thus, the third rotor assembly 45 is operatively connected to the aircraft and may provide forward thrust for horizontal flight in the mode of the aircraft system 10 herein that obtains power generation from the rotation of the propellers 14 in the first rotor assembly 11 and the second rotor assembly 15 as described herein, as well as lift. This provides great power generation and lift during autorotation of the horizontally rotating propellers 14 of the first rotor assembly 11 and the second rotor assembly 15, even with the exclusion of the canards 38 and 40.

[0046] 1-3, positioned at the rear of the aircraft fuselage 26 is a tail or horizontal stabilizer 28 to which a center portion 30 of the first wing 20 is operatively connected. Both the first wing 18 and the second wing 24 are shown having control surfaces, such as flaps 32, and may include other conventional control surfaces as occurs in the art.

[0047] The aircraft system 10 herein works well with any aircraft having a first wing 18 having a first curved wing tip 18 and a second wing 24 having a second curved wing tip 22, where the first rotor assembly 11 and the second rotor assembly 15 are engaged between the distal ends of the first curved wing tip 18 at either end of the first wing 20 that curves towards the second wing 20 and the second curved wing tip 22 at either end of the second wing 24 that curves upwardly towards the first wing 20. Such an arrangement is shown in an enlarged view in FIG. 4 and in FIGS. 1-3.

[0048] Of course, other configurations that would occur to one skilled in the art in which the first curved tip 18 of the first wing 20 and the second curved tip 22 of the second wing 24 curve towards each other may also be engaged with the first rotor assembly 11 and the second rotor assembly 15, respectively, in such engagement, each of the rotor assemblies 11 and 15 having a propeller 14 that rotates in a horizontal plane extending into the space 31 between the first wing 20 and the second wing 24, and which achieve the benefits noted herein and are considered to be within the scope of the claims herein.

[0049] Particularly preferred is a configuration of the first wing 20 that is substantially V-shaped, as shown in Figures 1-3. As mentioned above, this V-shaped wing 20 has been shown to provide the additional benefit of improving aircraft progression by directing the horizontal airflow over the upper surface of the second wing 24 and toward the horizontal stabilizer 28 so that it proceeds under the first wing 20. The increased contact airflow has been shown in experiments to facilitate aircraft progression and keep the aircraft more stable in the horizontal plane 36, which is substantially aligned with or proceeds substantially parallel to the surface of the second wing. As a result, the inclusion of this V-shaped first wing 20 in addition to the first and second motor-driven generators 12 and 13 positioned at the wing tips further improves the performance of the aircraft.

[0050] Also shown in FIG. 1 and providing additional utility for VTOL and forward thrust are the starboard canard 38 and the port canard 40, each of which may be configured to rotate 360°. A controller 42 is in operative communication with a canard actuator 44 or motor that provides simultaneous rotation of both the starboard canard 38 and the port canard 40, as shown in FIG. 3. Such controllers 42 are widely useful and utilized and may include gyroscopes, accelerometers, magnetometers, and other components that allow for calculating and adjusting the positioning of the aircraft by adjusting the positioning of the canards 38 and 40 and the propeller speeds of all propellers, as well as adjusting control surfaces such as the flaps 32 before and during flight. The controller 42 may be on-board the aircraft or in operative communication with control actuators and the like in the aircraft.

[0051] The controlled rotation allows both canards 38 and 40, when included, to rotate between a substantially horizontal position as shown in Figures 1 and 2 to a substantially vertical position as shown in Figure 3. Changing the orientation of the starboard canard 38 simultaneously changes the orientation of the third rotor assembly 45 and the third motor or generator 38 engaged thereto. Changing the orientation of the fourth rotor assembly 47 on the starboard canard 40 by rotating the starboard canard 40 simultaneously changes the orientation of the fourth motor or generator 48 and the propeller 14 engaged thereto.

[0052] Both the third engine generator 46 and the fourth engine generator 48 have propellers 14 engaged thereto, the propellers 14 having blades 16. As shown in Figures 1 and 2, the starboard canard 38 and the port canard 40 are rotated by the canard actuator 44 to a substantially parallel position to be substantially aligned or run substantially parallel to the parallel plane 36 for forward flight of the aircraft. Such a configuration may be utilized for runway takeoff and during forward flight. Of course, the canards may be rotated in engagement with the actuator 44 to run in any plane at any time.

[0053] As shown in Figure 3, both the right canard 38 and the left canard 40 are rotated to a substantially vertical position, and the propellers 14 of the first rotor assembly 11 and the second rotor assembly 15, as well as the third rotor assembly 45 and the fourth rotor assembly 47 and their propellers 14 and blades 16 rotate in a substantially horizontal plane. This configuration can be utilized for vertical takeoff and landing of the aircraft. The propellers 14 of the first motor-driven generator 12 and the second motor-driven generator 13, as well as the third motor-driven generator 46 and the fourth motor-driven generator 48, all undergo powered rotation to provide VTOL lift.

[0054] During vertical landing of the aircraft, the automatic rotation of the propeller 14, which provides power to turn one or more of the first engine generator 12, the second engine generator 13, the third engine generator 46, and the fourth engine generator 48, will generate electricity, which can be transmitted to recharge the power source 34. Of course, in flight, the starboard canard 38 and the port canard 40 can be rotated by the actuator 44 to propel the aircraft and / or change the aircraft's direction and / or altitude, as commanded by the controller 42 as needed.

[0055] As mentioned, Figure 4 shows an alternative configuration of the aircraft device 10 in which the first wing 20 and the second wing 24 are in a biplane configuration rather than the mentioned V-shaped configuration of the first wing 20 shown in Figures 1-3. As also mentioned, any configuration conceivable by one skilled in the art having the first wing 20 positioned above the second wing 24 and allowing the first rotor assembly 11 and the second rotor assembly to be positioned between the curved wing tips 18 and 22 at either end of the wings is considered to be within the scope of this patent.

[0056] A close-up view of the tip positioning of the second rotor assembly 15 with the second motor-generator 13 having a bladed propeller is shown in FIG. 5. As shown, the first wing 20 has a first curved wing tip 18 that curves downward toward the second wing 24. As further shown, the second wing 24 has a second curved wing tip 22 that curves upward toward the upper first wing 20. The second rotor assembly 15 with the second motor-generator 13 is shown operatively engaged with both the first wing tip 18 and the second wing tip 22 and engaged with the propeller 14. The first rotor assembly 11 with the first motor-generator 12 is engaged with the wing tips 18 and 22 in the same manner as the opposite ends of the two wings.

[0057] Such engagement of the curved wing tips, for example to rotor assemblies 11 and 15, may be to the external housing of the power generator 12 or 13, or to bearings or other mountings that hold the power generator 12 or 13 in a fixed position, thereby holding the propeller 14 and the blades 16 extending from the propeller 14 in a fixed horizontal plane. This allows the propeller 14 to receive power from the power source 34, provide vertical thrust for vertical lift, and auto-rotate during descent to slow the descent and simultaneously generate electricity. Additionally, this positioning allows the engaged propeller 14 to capture vortex forces generated at the wing tips during forward flight to generate power to recharge the power source 34.

[0058] FIG. 6 is an exemplary flow chart showing detailed steps of process 100 for the operation of canards 38 and 44, rotors, and capacitors for VTOL operation in accordance with the flight curve (curve 300 in FIG. 7) of aircraft 100 (FIGS. 1-5).

[0059] The process begins at step 102. At step 104, the canard up orientation is confirmed. At step 106, all engine generators are energized to generate lift. The aircraft is permitted to climb to a desired or favorable altitude at step 108. The canard angle is reduced at step 110.

[0060] In step 112, the aircraft begins to descend. The engine generator is deenergized in step 114. Autorotation of the wingtip-located engine generator begins in step 116, resulting in recharging of the power source 34. In step 118, the aircraft descends to a desired or favorable altitude. Once this desired or favorable altitude is achieved, thereafter in step 120, the angle of attack of the canards 38 and 40 is increased, resulting in an increase in altitude resulting from the aircraft's thrust. In step 122, before a decrease in speed is detected, such as by the aircraft controller 42, discharge of the power source 34 begins in step 124. The drive rotor is then energized in step 126, after which the aircraft ascends to maximum altitude in step 108.

[0061] FIG. 7 illustrates an example mode of operation of the aircraft system 10 herein, in which vortex energy and autorotation energy are captured to spin propellers positioned at the wing tips and generate electricity to charge the power source 34 during flight.

[0062] Curve 200 illustrates through various stages of electrical generation associated with aircraft 100 (FIGS. 1-5) ascending or descending in altitude.

[0063] Phase 201 illustrates an initial consumption phase, which may correspond to the aircraft 10 taking off from the ground. During this phase, altitude is gained from the aircraft and electricity from the power source 34 may be consumed by the aircraft.

[0064] Step 202 indicates a segment / point on curve 200 that may correspond to vertical take-off and landing (VTOL) of aircraft 10 .

[0065] Step 204 illustrates the segment of curve 300 that corresponds to the initial climb in altitude of aircraft 10 .

[0066] Phase 205 shows the glide regeneration phase of the aircraft as described herein. During this phase, while the angle of attack changes with respect to the external crosswind (the right main first engine generator 12 and the left main second engine generator 13 (FIG. 1)), a drop in altitude occurs in conjunction with the regenerative power generated as a result of the automatic rotation of the first engine generator 12 and the second engine generator 13, increasing the lift from the second wing 24 and the first wing 20 while generating electricity from the rotation. Additionally, the third engine generator 46 and the fourth engine generator 48 can be deenergized to capture and store electricity generated from the relevant wind.

[0067] Step 206 represents the segment of curve 200 that corresponds to the initiation of gliding without power.

[0068] Step 208 indicates an inflection point in curve 200 representing the aircraft 10 of FIGS. 1-3 beginning to climb back to altitude.

[0069] Phase 209 indicates a discharge phase of the power source 34. Energy from the power source 34, such as batteries and / or capacitors, which may be charged on-board the aircraft, may be advantageously used to power on-board operations of the aircraft. The power source discharge segment in curve 200 corresponds to a segment of curve 200 that exhibits an advantageous slope or angle that maximizes lift against drag, wing performance, additional crosswind electricity generation, etc. Altitude gain or loss and electricity generation or use by on-board engine generators are noted in each of the phase sections referenced herein.

[0070] Stage 211 illustrates energy regeneration during glide of the aircraft, which is enabled during unpowered glide 212, while some or all of the engine generators are powered to rotate and generate electricity as described above.

[0071] The aircraft system disclosed herein, including an engine generator engaged with a propeller positioned between the curved wing tips of two wings of an aircraft, has other applications, which can be understood by those skilled in the art. The interpretation in the features of the present invention does not limit the scope of the claims of this application, and other applications developed by those skilled in the art who have considered this application are considered to be included in the present invention.

[0072] Although the device is shown in its simplest form and potential configuration, it is additionally noted and anticipated that various components and aspects of the disclosed wing system may be otherwise configured or slightly modified when forming the invention herein. Accordingly, those skilled in the art will appreciate that the descriptions and representations set forth in this disclosure are merely meant to represent examples of preferred modes of the curved wing system engaged with the motorized generator herein, within the full scope and intent of the present invention, and are not to be considered limiting in any way.

[0073] Moreover, while all essential characteristics and features of the present invention have been shown and described herein with reference to specific embodiments thereof, a range of modifications, variations and alternatives are contemplated in the foregoing disclosure, as well as the following claims. It is apparent that some examples and some features of the present invention may be utilized without the corresponding use of other features without departing from the scope of the present invention as described. It is also to be understood that various alternatives, modifications and variations may be made by those skilled in the art without departing from the spirit or scope of the present invention. Consequently, all such modifications, variations and alternatives are included within the scope of the present invention as defined by the following claims.

Claims

1. 1. An aircraft, a fuselage having a forward end and an aft end, and having a right side and a left side opposite the right side; a first wing having a first curved wing tip located on the right side of the fuselage and a second curved wing tip located on the left side of the fuselage; a second wing positioned below the first wing, the second wing having a first curved wing tip on the right side of the fuselage and a second curved wing tip positioned on the left side of the fuselage; a first rotor assembly positioned between a distal end of the first curved tip of the first wing and a distal end of the first curved tip of the second wing; a second rotor assembly positioned between a distal end of the second curved tip of the first wing and a distal end of the second curved tip of the second wing; Equipped with a first curved tip of the first wing and a first curved tip of the second wing curve toward each other; a second curved tip of the first wing and a second curved tip of the second wing curve toward each other; the first rotor assembly includes a first motor-generator and a first propeller including a plurality of blades engaged with the first motor-generator, the propeller rotating in a horizontal plane, the horizontal plane extending into a gap between the first wing and the second wing; The second rotor assembly includes a second motor-generator and a second propeller including a plurality of blades engaged with the second motor-generator, the second propeller rotating in the horizontal plane.

2. the first wing is V-shaped; a vertical stabilizer engaged with the vehicle body at a first end and extending to a distal end; 2. The aircraft of claim 1, wherein the first wing has a center portion engaged with the distal end of the vertical stabilizer.

3. a starboard canard extending from a first end engaged with the right side of the fuselage to a distal end thereof; a left canard extending from a first end engaged with the left side of the fuselage to a distal end thereof; a third rotor assembly located on the starboard canard and having a third motor-generator engaged with a propeller; a fourth rotor assembly located on the port canard and having a fourth motor-generator engaged with a propeller; 13. The aircraft of claim 1, further comprising:

4. a starboard canard extending from a first end engaged with the right side of the fuselage to a distal end thereof; a left canard extending from a first end engaged with the left side of the fuselage to a distal end thereof; a third rotor assembly located on the starboard canard and having a third motor-generator engaged with a propeller; a fourth rotor assembly located on the port canard and having a fourth motor-generator engaged with a propeller; 3. The aircraft of claim 2, further comprising:

5. the first end of the starboard canard and the first end of the port canard are both engaged to an actuator; the actuator is rotatable; both the starboard canard and the port canard are rotatable between a horizontal orientation and a vertical orientation by rotation of the actuator; the horizontal orientation positions the propellers of the third rotor assembly and the propellers of the fourth rotor assembly in a vertical orientation such that they generate forward thrust during horizontal flight of the aircraft; 4. The aircraft of claim 3, wherein the vertical orientation positions the propellers of the third rotor assembly and the propellers of the fourth rotor assembly in a horizontal orientation such that they generate vertical thrust during vertical flight of the vehicle.

6. the first end of the starboard canard and the first end of the port canard are both engaged to an actuator; The actuator is rotatable; both the starboard canard and the port canard are rotatable between a horizontal orientation and a vertical orientation by rotation of the actuator; the horizontal positioning positions the propellers of the third rotor assembly and the propellers of the fourth rotor assembly in a vertical position such that they generate forward thrust during horizontal flight of the aircraft; 5. The aircraft of claim 4, wherein the vertical orientation positions the propellers of the third rotor assembly and the propellers of the fourth rotor assembly in a horizontal orientation such that they generate vertical thrust during vertical flight of the vehicle.

7. and further comprising a regenerative charging process used in connection with charging an on-board power source of the vehicle using automatic rotation of the propeller engaged with the first rotor assembly and the propeller engaged with the second rotor assembly; 6. The aircraft of claim 5, wherein electrical energy generated by the regenerative charging process is transferred to the power source to recharge the power source.

8. 7. The aircraft of claim 6, further comprising a regenerative charging process used in connection with charging an on-board power source using automatic rotation of the propeller engaged with the first rotor assembly and the propeller engaged with the second rotor assembly, and wherein electrical energy generated by the regenerative charging process is transferred to the power source to recharge the power source.

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