Abstract
Variations of an aerial vehicle, all with capability of vertical take-off and landing (VTOL), with one variation comprising at least three engines, at least three rotors, a flight control system, battery, and propulsion system. The second VTOL aerial vehicle variation being a hybrid with engine-powered rotors and electric-powered rotors configured to work with a flight control system and battery. The first and second variations having the option of a genset system which recharges the battery. The third VTOL aerial vehicle variation being all-electric-powered rotors configured to work with a flight control system and a genset system which powers the rotors and/or recharges the battery.
Claims
1. An aerial vehicle comprising: at least three engines each configured to drive a respective rotor to rotate, rotation of the rotors generating thrust and causing the aerial vehicle to fly; a flight control system configured to provide controlled flight for the aerial vehicle comprising: electronic speed control unit to control a device configured to control the throttle of the engine, which controls the amount of power provided by the engines; and a gyroscope or stabilization device; a battery pack providing power to the flight control system; and a propulsion system configured to provide power to the rotors comprising: the engines; and a drive mechanism configured to provide power to the rotors.
2.-3. (canceled)
4. The aerial vehicle of claim 1, wherein the battery pack is rechargeable, the battery pack to provide power for the flight control system, the aerial vehicle further comprising: a genset system comprising an engine and an electric generator system configured to provide power to the battery pack.
5. An aerial vehicle comprising: a hybrid propulsion system comprising an engine configured to drive a respective engine-powered rotor to rotate; and a battery pack configured to provide power to an electric-powered rotor motor, which is connected to a rotor, rotation of the engine-powered rotor and the electric-powered motor's rotor generating thrust and causing the aerial vehicle to fly; and a flight control system connected to the battery pack comprising: a device configured to control the throttle of the engine, which controls the amount of power provided by the engines; and a stabilization device working in concert with an electronic speed control unit enabling stabilization of the aerial vehicle for controlled flight.
6.-7. (canceled)
8. The aerial vehicle of claim 5, wherein the battery pack is rechargeable, the aerial vehicle further comprising: a genset system comprising the engine, and an electric generator system configured to provide power to the rechargeable battery pack or the rotor motor; and a bridge rectifier configured to convert AC power generated by the genset system or generator motor to DC power and provide the DC power to either or both the rechargeable battery and the rotor motor.
9. The aerial vehicle of claim 5, wherein there is a fuel cell used to provide electric power.
10. A manned aerial vehicle comprising: an electric rotor motor configured to drive a respective rotor to rotate, rotation of the rotor generating thrust and causing the manned aerial vehicle to fly; a flight control system comprising: an electronic speed control configured to control an amount of power provided to the rotor motor; and a stabilization device working in concert with the electronic speed control unit enabling stabilization of the aerial vehicle for controlled flight; a rechargeable battery configured to provide power to the rotor motor; a genset system comprising an engine and electric generator system configured to provide power to the rechargeable battery pack or the rotor motor comprising: the engine configured to generate mechanical power; a generator motor coupled to the engine and configured to generate AC power using the mechanical power generated by the engine; a bridge rectifier configured to convert the AC power generated by the genset system or generator motor to DC power and provide the DC power to either or both the rechargeable battery and the rotor motor; an electronic control unit configured to control a throttle of the engine based, at least in part, on a power demand of at least one load; and a seat for a driver.
11. The manned aerial vehicle of claim 10 further comprising a plurality of additional electric rotor motors connected to a battery pack and flight control system.
12. (canceled)
13. The aerial vehicle of claim 10, wherein there is a fuel cell used to provide electric power.
14.-16. (canceled)
17. The aerial vehicle of claim 10, further comprising a power distribution board configured to distribute DC power from either or both the rechargeable battery or the bridge rectifier to the load(s).
18.-19. (canceled)
20. The aerial vehicle of claim 5, wherein the rechargeable battery is configured to provide the power to the rotor motor(s) when the engine(s) and the generator motor are turned off.
21. The aerial vehicle of claim 10, wherein the rechargeable battery is configured to provide the power to the rotor motor(s) when the engine(s) and the generator motor are turned off.
22.-33. (canceled)
34. The aerial vehicle of claim 1, further comprising ducted fans or shrouded propellers configured to add thrust or lift from the rotor(s).
35. The aerial vehicle of claim 5, further comprising ducted fans or shrouded propellers configured to add thrust or lift from the rotor(s).
36. The aerial vehicle of claim 10, further comprising ducted fans or shrouded propellers configured to add thrust or lift from the rotor(s).
37. The aerial vehicle of claim 1, further comprising articulating rotor mount to act as a tilt rotor or tilt wing for increased movement or forward flight or to be folded in a downward position for parking or storage.
38. The aerial vehicle of claim 5, further comprising articulating rotor mount to act as a tilt rotor or tilt wing for increased movement or forward flight or to be folded in a downward position for parking or storage.
39. The aerial vehicle of claim 10, further comprising articulating rotor mount to act as a tilt rotor or tilt wing for increased movement or forward flight or to be folded in a downward position for parking or storage.
40.-44. (canceled)
45. The aerial vehicle of claim 10, wherein the aerial vehicle has wheels on the bottom of the vehicle allowing it to propel itself while on the ground, the propulsion of one or more of the wheels coming from an electric motor.
46.-49. (canceled)
50. The aerial vehicle of claim 5, wherein the aerial vehicle is with or without fixed wings.
51. The aerial vehicle of claim 10, wherein the aerial vehicle is with or without fixed wings.
Description
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] FIG. 1 Diagram depicting a possible configuration of an illustrative embodiment of an aerial vehicle, which shows an engine-powered mechanical propulsion system for the aerial vehicle.
[0027] FIG. 2 Diagram depicting a possible configuration of an illustrative embodiment of an aerial vehicle, which includes a hybrid propulsion system comprised of an engine-powered mechanical propulsion of the rotors and an electrically-powered rotor motor.
[0028] FIG. 3 Diagram depicting a possible configuration of an illustrative embodiment of an aerial vehicle, which includes an engine-powered mechanical propulsion of the rotors and where the engine is part of a genset system, which can recharge a battery pack.
[0029] FIG. 4 Diagram depicting a possible configuration of an illustrative embodiment of an aerial vehicle, which includes a hybrid propulsion system comprised of an engine-powered mechanical propulsion of the rotors and an electrically-powered rotor motor and where the engine is part of a genset system, which can recharge a battery pack.
[0030] FIG. 5 Diagram depicting a possible configuration of an illustrative embodiment of an aerial vehicle, which includes electric rotor motors providing power of the rotors and where an engine is part of a genset system, which can recharge a battery pack.
[0031] FIG. 6 shows an illustrative embodiment of an aerial vehicle according to the diagram of FIG. 4, where the mechanical powered rotor may be sufficiently large to do the “heavy lifting” while the smaller rotors may be electric powered for stabilizing the aerial vehicle and provide additional forward thrust.
[0032] FIG. 7 shows an illustrative embodiment of an aerial vehicle according to the diagram of FIG. 2, wherein the aerial vehicle is a hybrid mechanical and electrical powered aerial vehicle.
[0033] FIG. 8 shows an illustrative embodiment of an aerial vehicle according to the diagram of FIG. 5, wherein the hybrid aerial vehicle generates electrical power and where all rotors are powered electrically.
[0034] FIG. 9 shows an illustrative embodiment of an aerial vehicle according to the diagram of FIG. 1, wherein the aerial vehicle is mechanically powered.
[0035] FIG. 10 shows an illustrative embodiment of an aerial vehicle with the props (rotors) of the aerial vehicle folded in for parking.
[0036] FIG. 11 shows an illustrative embodiment of an aerial vehicle with a canopy over the cockpit of the aerial vehicle giving some level of protection to the passenger inside from outside elements of weather, noise, and such.
[0037] FIG. 12 shows an illustrative embodiment of an aerial vehicle with the props of the aerial vehicle tilted to assist in facilitating movement.
[0038] FIG. 13 shows an illustrative embodiment of an aerial vehicle where the operator rides on the outside of the aerial vehicle.
[0039] FIG. 14 shows an illustrative embodiment of an aerial vehicle where the operator rides on the inside of the aerial vehicle.
DETAILED DESCRIPTION
[0040] Aside from the preferred embodiment or embodiments disclosed below, this invention is capable of other embodiments and of being practiced or being carried out in various ways. Thus, it is to be understood that the invention is not limited in its application to the details of construction and the arrangements of components set forth in the following description or illustrated in the drawings. If only one embodiment is described herein, any claims herein are not to be limited to that embodiment. Moreover, any such claims are not to be read restrictively unless there is clear and convincing evidence manifesting a certain exclusion, restriction, or disclaimer.
[0041] Although specific features of the invention are shown in some drawings and not in others, this is for convenience only as each feature may be combined with any or all of the other features in accordance with the invention. The words “including”, “comprising”, “having”, and “with” as used herein are to be interpreted broadly and comprehensively and are not limited to any physical interconnection. Moreover, any embodiments disclosed in the subject application are not to be taken as the only possible embodiments. Other embodiments will occur to those skilled in the art.
[0042] One or more embodiments of a genset system provide a power source with energy conversion efficiency. In manned aerial vehicle applications, the genset system of one or more embodiments can be used to overcome the weight of the vehicle and load necessary to provide extended endurance and load capabilities.
[0043] FIG. 1 is a diagram depicting one embodiment of an aerial vehicle, which includes an engine-powered mechanical propulsion where speed of the engines are controlled by the electric control unit which consist of a stepper motor or some other throttle mechanism and works congruently with the stabilization device, a gyroscope or other computer aided instrument to maintain controlled flight. The engine drives the rotor, which is attached to the engine via a drive mechanism, wherein the drive mechanism may be a direct connection illustratively via a vertical drive shaft, or through a gear reduction drive, or through other means such as shafts and gearboxes or belts and pulleys. A fuel source supplies fuel to the engine, while a battery pack provides power to the electric control unit.
[0044] FIG. 2 is a diagram depicting another embodiment of an aerial vehicle, which includes a hybrid propulsion system comprised of an engine-powered mechanical propulsion of the rotors and an electrically-powered rotor motor. Where both speed of the engines and speed of rotor motor are controlled by the electric control units which works congruently with the stabilization device, a gyroscope or other computer aided instrument is used to maintain controlled flight. The mechanical powered rotor is attached to the engine directly via a vertical drive shaft, or through a gear reduction drive, or through other means such as shafts and gearboxes or belts and pulleys. The electric powered rotor may be attached directly to the rotor motor. A fuel source supplies fuel to the engine, while a battery pack provides power to the electric control units for the engine speed and for the electric rotor motors.
[0045] FIG. 3 is a diagram depicting another possible configuration of an aerial vehicle, which includes engine-powered mechanical propulsion of the rotors and where the engine is part of a genset system, which has an alternator/generator attached to the engine which generates electric power to recharge the battery pack thus allowing for longer flight time. Subsequently, the battery pack is not the limiting factor in flight duration, but instead the amount of fuel for the engine that is stored on the aerial vehicle may be limiting. The speed of the engine is controlled by the electric control unit which includes a stepper motor or some other throttle mechanism and works congruently with the stabilization device, a gyroscope or other computer aided instrument to maintain controlled flight. The rotor may be attached directly to a vertical drive shaft of the engine, or through a gear reduction drive, or through other means such as shafts and gearboxes or belts and pulleys. A fuel source supplies fuel to the engine, while the rechargeable battery pack provides power to the electric control unit.
[0046] FIG. 4 is a diagram depicting another illustrative embodiment of an aerial vehicle, which includes a hybrid propulsion system comprised of an engine to provide mechanical propulsion of the rotors and an electrically-powered rotor motor. The engine is part of a genset system, where an alternator/generator is attached to the engine which generates electric power to recharge the battery pack thus allowing for longer life of the battery pack, thus enabling the use of a smaller battery pack or longer flight durations. Both the speed of the engine and speed of rotor motor are controlled by the electric control units which works congruently with the stabilization device, a gyroscope or other computer aided instrument to maintain controlled flight. The mechanical powered rotor may be attached directly to a vertical drive shaft of the engine, or through a gear reduction drive, or through other means such as shafts and gearboxes or belts and pulleys. The electric powered rotor illustratively is attached directly to the rotor motor. A fuel source supplies fuel to the engine, while a battery pack provides power to the electric control units for the engine speed and for the electric rotor motors.
[0047] FIG. 5 is a diagram depicting another illustrative aerial vehicle, which includes electric rotor motors providing power of the rotors and where an engine is part of a genset system, which has an alternator/generator attached to the engine which generates electric power. In one embodiment where DC electric motors are used, this configuration includes a bridge rectifier configured to convert the AC power generated by the genset system or generator motor to DC power and provide the DC power to either or both the rechargeable battery and an Electronic Speed Controller (ESC), which governs amount of power provided to the rotor motor(s). This genset system provides electric power to the electric motor(s) or is used to recharge the battery pack thus allowing for longer flight time. Thus, for the electric-powered rotor motor(s), the battery pack may not be the limiting factor in flight duration, but instead the length of flight may be limited by the amount of fuel for the engine that is stored on the aerial vehicle. The speed of the engine is controlled by the electric control unit which includes a stepper motor or some other throttle mechanism. The throttle to the engine can be increased thus generating more electric power from the genset system for increased power to the battery pack or otherwise. The ESC and works congruently with the stabilization device, a gyroscope or other computer aided instrument to maintain controlled flight. The rotor is attached directly to the electric rotor motor. A fuel source supplies fuel to the engine, while the rechargeable battery pack provides power to the electric control units for the engine speed and for the electric rotor motors.
[0048] FIG. 6 depicts one possible embodiment of the aerial vehicle 60 as described in FIG. 4. This includes a fuel source 9, e.g., a vessel for storing gasoline, a mixture of gasoline and oil mixture, hydrogen, or similar type fuel or mixture. The fuel source 9 provides fuel to an engine or fuel cell 1, of a first power system. The engine 1 can use the fuel provided by the fuel source to generate mechanical energy. While one engine 1 is depicted, it is understood that the use of multiple engines are within the scope of this invention. The mechanical energy can be transferred from the engine 1 crank/driveshaft (not shown) to the mechanically powered rotors 10 belts and pulleys 11, although it is understood that other drive means may be used such as shafts and gearboxes. The engine will be part of the genset (engine-generator) system, which includes an alternator/generator motor 2 coupled to the engine 1. While a genset system is depicted, it is understood that the use of a fuel cell, hydrogen or otherwise, to provide electric power is within the scope of this invention. The generator motor 2 functions to generate AC output power using mechanical power generated by the engine. In various embodiments, a shaft (not shown) of the engine 1 includes a fan (not shown) that dissipates heat away from the engine. In various embodiments, the generator motor is coupled to the engine through a polyurethane coupling. The genset system includes a bridge rectifier 3 and a rechargeable battery 4. The bridge rectifier 3 is coupled between the generator motor 2 and the rechargeable battery 4 and converts the AC output of the generator motor 2 to DC power to charge the rechargeable battery 4 or provide DC power to electric motor 12 with use of an electric speed control (ESC) 5 to govern amount of power supplied to electric motor 12. The ESC 5 can control the power provided by bridge rectifier 3 and/or rechargeable battery 4 to rotor motor 12 provided by generator motor 2. Rotor motor 12 powers a rotor 6, which may be inside a duct or shroud as shown in this FIG. 6. As shown, there are two rotors 6, one on either side of aerial vehicle 60. Although only one rotor motor 12 may be seen in FIG. 6, it is understood that each rotor 6 may be provided with a rotor motor. It is understood that if rotor motor 12 runs on AC current, then a DC-to-AC inverter is configured into the system to provide AC power to electric motor 12. The rechargeable battery 4 may thereby provide DC or AC power to rotor motor 12 depending upon type of electric motor used. Although only one ESC is shown, each electric motor 12 may have its respective ESC 5 governing the amount of power to that motor and the engine may have its separate speed control unit to govern the throttle position. In one example, an output of the bridge rectifier 3 and/or the rechargeable battery 4 is provided to one or more ESCs 5 integrated with the stabilization device 8, which may be a gyroscope or some other computer aided device used for controlled flight of the aerial vehicle. It is understood that some flight controllers (not shown) combine the ESC, the stabilization device, as well as a battery management system, battery monitor logger, and battery indicator display into one component or one single device.
[0049] FIG. 7 shows one possible embodiment as described in FIG. 2, showing a hybrid mechanical and electrical powered aerial vehicle 70. This includes a fuel source 79, e.g., a vessel for storing gasoline, a mixture of gasoline and oil mixture, or similar type fuel or mixture. The fuel source provides fuel to at least one engine 73. The engine(s) can use the fuel provided by the fuel source to generate mechanical energy. The mechanical energy can be transferred from the engine(s) crank/driveshaft to the mechanically powered rotors 74 directly using belts and pulleys 77, but it is understood that rotors may be driven by other means such as shafts and gearboxes. A battery pack 75, which provides power to the electric motor 71, is wired to its respective electric speed control (ESC) 76 to govern amount of power supplied to electric motor 71. The ESC 76 can control the amount power provided by the battery pack 75 to its respective electric rotor motor 71. The ESC 76 may be configured to work in concert with a small stepper or servo motor or actuator (not shown) that acts to adjust the throttle position of the engine 73. Electric propeller motor 71 powers the rotor 72, which creates lift allowing the aerial vehicle to fly. In one example, the battery pack 75 provides power to one or more ESCs 76 integrated with the stabilization device 78, which may be a gyroscope or some other computer aided device used for controlled flight of the aerial vehicle. It is understood that some flight controllers (not shown) combine the ESC, the stabilization device, as well as a battery management system, battery monitor logger, and battery indicator display into one component or one single device. While a battery pack 75 is depicted, it is understood that the use of a fuel cell supplied by a fuel source, hydrogen or otherwise, is within the scope of this invention.
[0050] FIG. 8 is an illustrative hybrid aerial vehicle 80 of FIG. 5, wherein all rotors are powered by electric motors causing lift and flight of the aerial vehicle. Aerial vehicle 80 includes a fuel source 81, e.g., a vessel for storing gasoline, a mixture of gasoline and oil mixture, hydrogen, or similar type fuel or mixture. The fuel source provides fuel to an engine 811, which is configured to be part of a genset (engine-generator) system. The engine 811 can use the fuel provided by the fuel source 81 to generate mechanical energy. This genset system also includes an alternator or generator motor 82 coupled to the engine. The generator motor functions to generate AC output power using mechanical power generated by the engine. In various embodiments, a shaft of the engine includes a fan (not shown) that dissipates heat away from the engine. In various embodiments, the generator motor is coupled to the engine, illustratively through a polyurethane coupling. The genset system includes a bridge rectifier 83 and a rechargeable battery 84. The bridge rectifier 83 is coupled between the generator motor 82 and the rechargeable battery 84 and converts the AC output of the generator motor 82 to DC power to charge the rechargeable battery 84 or provide DC power to electric motor 87 with use of an electric speed control (ESC) 85 to govern amount of power supplied to motor. If AC motors are chosen then a DC-to-AC Inverter may be included in the system to provide AC power to the AC motor 87, which provides power to the rotor 88 causing the aerial vehicle to fly. In one example, an output of the bridge rectifier 83 and/or the rechargeable battery 84 is provided to one or more electronic speed control devices (ESC) 85 integrated with its respective rotor motors 87, which provide power to the rotor 88, which may be inside a duct or shroud 812 as shown in this FIG. 8. The ESC 85 can control the DC power provided by generator motor 82 via bridge rectifier 83 and/or rechargeable battery 84 to one or more rotor motors 87. The ESCs 85 are configured to adjust the amount of power provided to the rotor motors 87 with input from the stabilization device 86, which may be a gyroscope or some other computer aided device used for controlled flight of the aerial vehicle. In various embodiments, the ESCs 85 can control an amount of power provided to one or more rotor motors 87 in response to input received from an operator. It is understood that some flight controllers (not shown) combine the ESC, the stabilization device, as well as a battery management system, battery monitor logger, and battery indicator display into one component or one single device. While a genset system is depicted, it is understood that the use of a fuel cell, hydrogen or otherwise, to provide electric power is within the scope of this invention.
[0051] For example, if an operator provides input to move aerial vehicle to the right, then the ESC controlling the right-side rotor motor 89 can provide less power to rotor motor 89 on the right of the aerial vehicle to cause the rotor motors to spin propellers/rotors on the right side of the aerial vehicle slower causing the aerial vehicle to turn right and/or the ESC controlling the left-side motor 810 can provide more power to rotor motor 810 on the left of the aerial vehicle to cause the rotor motors to spin propellers/rotors on the left side of the aerial vehicle faster than propellers on the ride side of the aerial vehicle causing the aerial vehicle to turn right. As power is provided at varying levels to one or more rotor motors the aerial vehicle can change directions and/or speed in response to input received from an operator.
[0052] FIG. 9 shows a mechanically powered aerial vehicle 90 according to the diagram of FIG. 1. Aerial vehicle 90 includes a fuel source 95, e.g., a vessel for storing gasoline, a mixture of gasoline and oil mixture, or similar type fuel or mixture. The fuel source 95 provides fuel to at least three engines 91. The engines can use the fuel provided by the fuel source to generate mechanical energy. Illustratively, the mechanical energy can be transferred from the engines crank/driveshaft to the mechanically powered rotors 96 directly or through a reduction gear or other means such as shafts and gearboxes or belts and pulleys. FIG. 9 shows rotors 96 attached directly to a vertical crank/drive shaft of the engine 91, but it is understood that the connection may be made through a gear reduction drive mounted between the vertical crank/drive shaft of the engine and the rotor 96, which may be inside a duct or shroud 97. A battery pack 93 provides power to electronic speed controls 92 configured to control the throttle position and therefore control the amount of power provided by its respective engine to the aerial vehicle. While four electronic speed controls 96 are shown, it is understood that other configurations are possible, illustratively with the number of electronic speed controls matching the number of engines. The electronic speed controls 92 are configured to work in concert with a small stepper or servo motor or actuator (not shown) that acts to adjust the throttle position of the engine 91. The electronic speed controls 92 are configured to work in concert with the stabilization device 94, which may be a gyroscope or some other computer aided device used for controlled flight of the aerial vehicle. As power is provided at varying levels to one or more engine 91 as required by the electronic speed controls 92 and the stabilizer 94 the aerial vehicle can change directions and/or speed in a controlled manner in response to input received from an operator. It is understood that some flight controllers (not shown) combine the ESC, the stabilization device, as well as a battery management system, battery monitor logger, and battery indicator display into one component or one single device.
[0053] FIG. 10 shows one possible embodiment of an aerial vehicle 100. The props may be exposed or in a shroud (also known as a shrouded propeller or ducted fan) as shown in this image. The prop mounting 101 may turn so the rotor turns from vertical to more of a horizontal facing angle thus creating increased forward speed. The prop mounting may also be configured to pivot, as in this image where it is folded down for storage.
[0054] FIG. 11 shows an illustrative embodiment of an aerial vehicle 110 with a canopy 111 over the cockpit of the aerial vehicle giving some level of protection to the passenger inside from outside elements of weather, noise, and such.
[0055] FIG. 12 shows an illustrative embodiment of an aerial vehicle 120 with tilt rotors 121 where the rotors (props) of the aerial vehicle are tilted to assist in facilitating movement.
[0056] FIG. 13 shows an illustrative embodiment of an aerial vehicle 130 where the operator rides on the outside 131 of the aerial vehicle.
[0057] FIG. 14 shows an illustrative embodiment of an aerial vehicle 140 where the operator rides on the inside 141 of the aerial vehicle.
