U.S. patent application number 16/387057 was filed with the patent office on 2019-08-08 for micro hybrid generator system drone.
The applicant listed for this patent is Top Flight Technologies, Inc.. Invention is credited to Eli M. Davis, Julian Lemus, Long N. Phan, Sanjay Emani Sarma, Benjamin Arthur Sena, Cody Miles Wojcik.
Application Number | 20190241264 16/387057 |
Document ID | / |
Family ID | 55961008 |
Filed Date | 2019-08-08 |
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United States Patent
Application |
20190241264 |
Kind Code |
A1 |
Phan; Long N. ; et
al. |
August 8, 2019 |
MICRO HYBRID GENERATOR SYSTEM DRONE
Abstract
An unmanned aerial vehicle comprising at least one rotor motor.
The rotor motor is powered by a micro hybrid generation system. The
micro hybrid generator system comprises a rechargeable battery
configured to provide power to the at least one rotor motor, a
small engine configured to generate mechanical power, a generator
motor coupled to the small engine and configured to generate AC
power using the mechanical power generated by the small engine, a
bridge rectifier configured to convert the AC power generated by
the generator motor to DC power and provide the DC power to either
or both the rechargeable battery and the at least one rotor motor,
and an electronic control unit configured to control a throttle of
the small engine based, at least in part, on a power demand of at
least one load, the at least one load including the at least one
rotor motor.
Inventors: |
Phan; Long N.; (Somerville,
MA) ; Sarma; Sanjay Emani; (Lexington, MA) ;
Wojcik; Cody Miles; (Fremont, NH) ; Davis; Eli
M.; (Cambridge, MA) ; Sena; Benjamin Arthur;
(Winthrop, MA) ; Lemus; Julian; (Somerville,
MA) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Top Flight Technologies, Inc. |
Malden |
MA |
US |
|
|
Family ID: |
55961008 |
Appl. No.: |
16/387057 |
Filed: |
April 17, 2019 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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15693859 |
Sep 1, 2017 |
10266262 |
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16387057 |
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14942600 |
Nov 16, 2015 |
9764837 |
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15693859 |
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62080554 |
Nov 17, 2014 |
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62080482 |
Nov 17, 2014 |
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62079866 |
Nov 14, 2014 |
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62079890 |
Nov 14, 2014 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64C 27/08 20130101;
Y02T 50/40 20130101; B64C 2201/066 20130101; B64C 2201/108
20130101; B64D 27/02 20130101; Y02T 50/60 20130101; B64C 2201/027
20130101; Y02T 50/44 20130101; B64C 39/024 20130101; B64C 2201/042
20130101; B64D 1/08 20130101; B64D 2027/026 20130101; B64D 2221/00
20130101; B64D 1/22 20130101; B64D 33/08 20130101; G05D 1/101
20130101; B64C 2201/044 20130101; B64F 3/02 20130101; B64D 27/24
20130101; B64C 27/001 20130101; Y02T 50/64 20130101; B64C 2201/063
20130101 |
International
Class: |
B64C 39/02 20060101
B64C039/02; B64D 33/08 20060101 B64D033/08; B64D 27/24 20060101
B64D027/24; B64D 1/22 20060101 B64D001/22; B64D 1/08 20060101
B64D001/08; B64F 3/02 20060101 B64F003/02; G05D 1/10 20060101
G05D001/10; B64D 27/02 20060101 B64D027/02; B64C 27/00 20060101
B64C027/00; B64C 27/08 20060101 B64C027/08 |
Claims
1. (canceled)
2. An unmanned aerial vehicle system comprising: an unmanned aerial
vehicle comprising: a flight module comprising a rotor motor
configured to drive rotation of a propeller of the unmanned aerial
vehicle; a mobile ground module detachably connected to the
unmanned aerial vehicle; and a hybrid energy generation system
comprising: a rechargeable battery configured to provide electrical
energy to one or more of the rotor motor and the mobile ground
module; an engine configured to generate mechanical energy; and a
generator configured to convert the mechanical energy generated by
the engine into electrical energy, the generator being electrically
connected to one or more of the rechargeable battery, the rotor
motor, and the mobile ground module.
3. The unmanned aerial vehicle system of claim 2, comprising a
tether connecting the mobile ground module to the unmanned aerial
vehicle.
4. The unmanned aerial vehicle system of claim 3, in which the
generator is electrically connected to the mobile ground module via
the tether.
5. The unmanned aerial vehicle system of claim 2, in which the
mobile ground module is operable when electrically disconnected
from the unmanned aerial vehicle.
6. The unmanned aerial vehicle system of claim 2, in which the
mobile ground module includes the hybrid energy generation
system.
7. The unmanned aerial vehicle system of claim 2, in which the
unmanned aerial vehicle includes the hybrid energy generation
system.
8. The unmanned aerial vehicle system of claim 2, in which the
mobile ground module comprises a leg wheel motion system.
9. The unmanned aerial vehicle system of claim 2, in which the
mobile ground module comprises a threaded base motion system.
10. The unmanned aerial vehicle system of claim 2, in which the
mobile ground module comprises a mobile robot.
11. The unmanned aerial vehicle system of claim 2, wherein the
hybrid energy generation system comprises a flexible coupling
device that directly couples a rotor of the engine to the
generator.
12. The unmanned aerial vehicle system of claim 11, in which the
flexible coupling device comprises a heat transfer element disposed
between the engine and the generator.
13. A method of operating an unmanned aerial vehicle system, the
method comprising: operating a hybrid energy generation system to
generate electrical energy, comprising: generating mechanical
energy in an engine of the hybrid energy generation system; in a
generator of the hybrid energy generation system, converting the
mechanical energy generated by the engine into electrical energy;
and providing at least some of the electrical energy produced by
the generator to a rechargeable battery of the hybrid energy
generation system; providing electrical energy from one or more of
the generator and the rechargeable battery to a flight module of an
unmanned aerial vehicle, the flight module comprising a rotor motor
configured to drive rotation of a propeller of the unmanned aerial
vehicle; and providing electrical energy from one or more of the
generator and the rechargeable battery to a mobile ground module
detachably connected the unmanned aerial vehicle.
14. The method of claim 13, in which providing electrical energy to
a mobile ground module comprises providing electrical energy to the
mobile ground module via a tether.
15. The method of claim 13, comprising controlling the mobile
ground module to autonomously detach from the flight module.
16. The method of claim 15, in which the mobile ground module
comprises the hybrid energy generation system, and in which
controlling the mobile ground module to autonomously detach from
the flight module comprises controlling the mobile ground module
including the hybrid energy generation system to autonomously
detach from the flight module.
17. The method of claim 13, controlling the hybrid energy
generation system to autonomously detach from the flight
module.
18. The method of claim 13, comprising cooling the hybrid energy
generation system by a heat transfer system included in a flexible
coupling device that directly couples a rotor of the engine to the
generator.
19. The method of claim 13, comprising operating the mobile ground
module when the mobile ground module is electrically disconnected
from the hybrid energy generation system.
Description
BACKGROUND OF THE INVENTION
[0001] This application is a continuation application and claims
priority under 35 USC .sctn. 120 to U.S. patent application Ser.
No. 15/693,859, filed Sep. 1, 2017. U.S. patent application Ser.
No. 15/693,859 is a continuation of U.S. patent application Ser.
No. 14/942,600, filed Nov. 16, 2015 (now U.S. Pat. No. 9,764,837),
which claims priority to U.S. Provisional Application No.
62/080,554, filed on Nov. 17, 2014, U.S. Provisional Application
No. 62/080,482, filed on Nov. 17, 2014, U.S. Provisional
Application No. 62/079,890, filed on Nov. 14, 2014, and U.S.
Provisional Application No. 62/079,866, filed on Nov. 14, 2014. The
contents of all of which are incorporated here by reference in
their entirety.
FIELD OF THE INVENTION
[0002] This invention relates to a micro hybrid generator system
drone.
[0003] A typical conventional multi-rotor UAV is significantly less
complex, easier to operate, less expensive, and easier to maintain
than a typical conventional single rotor aerial vehicle, such as a
helicopter or similar type aerial vehicle. For example, a
conventional multi-rotor UAV may include four or more rotor motors,
four or more propellers coupled thereto, four or more electronic
speed controllers, a flight control system (auto pilot), an RC
radio control, a frame, and a rechargeable battery, such as a
lithium polymer (LiPo) or similar type rechargeable battery. In
contrast, a single rotor aerial vehicle, such as a helicopter, may
have thousands of parts. Additionally, single rotor aerial vehicles
are also notoriously difficult to operate, diagnose problems, and
are expensive to maintain.
[0004] Multi-rotor UAVs can perform vertical take-off and landing
(VTOL) and are capable of aerial controls with similar
maneuverability to single rotor aerial vehicles. Multi-rotor UAVs
are relatively easy to assemble and may use commercial off the
shelf (COTS) hardware including auto pilot flight controllers that
are easily adaptable to standard configurations, e.g., a
quad-rotor, a hex-rotor, an octo-rotor, and the like.
[0005] A typical conventional multi-rotor UAV relies solely on
rechargeable battery or batteries to provide power to drive the
rotor motors coupled to the propellers to provide flight. A typical
conventional multi-rotor UAV includes a lithium polymer (LiPo)
battery which may provide about 150 to 210 Wh/kg. This may provide
a typical loaded flight time of about 15 minutes and an unloaded
flight time of about 32 to 45 minutes. Advance lithium sulfur
batteries may also be used which provide about 400 Wh/kg of power.
In this case, the flight times are about 30 minutes in a loaded
configuration.
[0006] In operation, the battery is used for the entire flight of
the conventional multi-rotor UAV. Thus, when the battery is
depleted, the UAV will stop operating. If the UAV is in flight,
this can result in a catastrophic crashing of the UAV.
Additionally, if aggressive maneuvers are needed during flight,
such as quickly veering away from an object or moving quickly to
avoid a potential threat, such maneuvers require instantaneous peak
power which can quickly deplete the battery and significantly
reduce flight time significantly.
[0007] Thus, conventional battery powered multi-rotor UAVs have
limited endurance and payload and provide no backup power in the
event the battery supply is depleted. Additionally, conventional
commercial UAVs are very expensive and not commercially viable at
scale today. [0007] Conventional portable generators are heavy and
may be difficult to transport to desired locations. Additionally,
micro grid power systems used for electric grid power backup or
ultra-micro power systems used in cell towers for power backup rely
solely on batteries to provide the needed backup power.
[0008] Thus, there is a need for a small, lightweight, portable
generator system which can provide power in such applications.
Additionally, there is a need for UAVs with improved operational
characteristics. For example, there is a need for UAVs capable of
operating for longer durations.
SUMMARY
[0009] The following implementations and aspects thereof are
described and illustrated in conjunction with systems, tools, and
methods that are meant to be exemplary and illustrative, not
necessarily limiting in scope. In various implementations one or
more of the above-described problems have been addressed, while
other implementations are directed to other improvements.
[0010] In various embodiments, an unmanned aerial vehicle
comprising at least one rotor motor configured to drive at least
one propeller to rotate, rotation of the at least one propeller
generating thrust and causing the unmanned aerial vehicle to fly.
In various embodiments, the unmanned aerial vehicle comprises an
electronic speed control configured to control an amount of power
provided to the at least one rotor motor. Further, in various
embodiments, an unmanned aerial vehicle comprises a micro hybrid
generator system configured to provide power to the at least one
rotor motor comprising. In various embodiments, an unmanned aerial
vehicle comprises a rechargeable battery configured to provide
power to the at least one rotor motor. Further, in various
embodiments, an unmanned aerial vehicle comprises a small engine
configured to generate mechanical power. Additionally, in various
embodiments, an unmanned aerial vehicle comprises a generator motor
coupled to the small engine and configured to generate AC power
using the mechanical power generated by the small engine. Further,
in various embodiments, an unmanned aerial vehicle comprises a
bridge rectifier configured to convert the AC power generated by
the generator motor to DC power and provide the DC power to either
or both the rechargeable battery and the at least one rotor motor.
In various embodiments, an unmanned aerial vehicle comprises an
electronic control unit configured to control a throttle of the
small engine based, at least in part, on a power demand of at least
one load, the at least one load including the at least one rotor
motor.
[0011] These and other advantages will become apparent to those
skilled in the relevant art upon a reading of the following
descriptions and a study of the several examples of the
drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
[0012] FIG. 1 depicts a diagram of an example micro hybrid
generator system.
[0013] FIG. 2 depicts a side perspective view of a micro hybrid
generator system.
[0014] FIG. 3A depicts a side view of a micro hybrid generator.
[0015] FIG. 3B depicts an exploded side view of a micro hybrid
generator.
[0016] FIG. 4 depicts a perspective view of a micro hybrid
generator system.
[0017] FIG. 5 is a perspective view of a UAV integrated with a
micro hybrid generator system.
[0018] FIG. 6 depicts a graph comparing energy density of different
UAV power sources.
[0019] FIG. 7 depicts a graph of market potential for UAVs against
flight time for an example two plus hours of flight time micro
hybrid generator system of one or more embodiments when coupled to
a UAV is able to achieve an example of the total market potential
vs. endurance for the micro hybrid generator system for UAVs of
this invention.
[0020] FIG. 8 shows an example flight pattern of a UAV with a micro
hybrid generator system.
[0021] FIG. 9 depicts a system diagram for a micro hybrid generator
system with detachable subsystems.
[0022] FIG. 10a depicts a diagram of a micro hybrid generator
system with detachable subsystems integrated as part of a UAV.
[0023] FIG. 10b depicts a diagram of a micro hybrid generator
system with detachable subsystems integrated as part of a ground
robot.
[0024] FIG. 11 shows a ground robot with a detachable flight pack
in operation.
[0025] FIG. 12 shows a control system of a micro hybrid generator
system.
[0026] FIG. 13 shows a top perspective view of a top portion of a
drone powered through a micro hybrid generator system.
[0027] FIG. 14 shows a top perspective view of a bottom portion of
a drone powered through a micro hybrid generator system.
[0028] FIG. 15 shows a top view of a bottom portion of a drone
powered through a micro hybrid generator system.
[0029] FIG. 16 shows a side perspective view of a micro hybrid
generator system.
[0030] FIG. 17 shows a side perspective view of a micro hybrid
generator system.
DETAILED DESCRIPTION OF THE INVENTION
[0031] 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 based on
this provisional patent application 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.
[0032] One or more embodiments of a micro hybrid generator system
provide a small portable micro hybrid generator power source with
energy conversion efficiency. In UAV applications, the micro hybrid
generator system of one or more embodiments can be used to overcome
the weight of the vehicle, the micro hybrid generator drive, and
fuel necessary to provide extended endurance and payload
capabilities in UAV applications. In other applications, the micro
hybrid generator device system can be used as a small, lightweight,
portable generator for residential and commercial applications or
as a micro-grid generator or an ultra-micro-grid generator, and the
like.
[0033] The micro hybrid generator system of one or more embodiment
of can comprise two separate power systems. A first power system
included as part of the micro hybrid generator system can be a
small and efficient gasoline powered engine coupled to a generator
motor. In various embodiments, the first power system serves as a
primary source of power of the micro hybrid generator system. A
second power system, included as part of the micro hybrid generator
system, can be a high energy density rechargeable battery.
Together, the first power system and the second power system,
combine to form a high energy continuous power source and high peak
power availability for a UAV, including when a UAV performs
aggressive maneuvers. Further, one of the first power system and
the second power system can serve as back-up power sources of the
micro hybrid generator system if a corresponding one of the first
power system or the second power system fails. In various
embodiments, the micro hybrid generator system can serve as a
portable, lightweight generator to provide power in residential and
commercial applications or as a micro-grid or ultra-micro-grid
generator.
[0034] FIG. 1 depicts a diagram of an example micro hybrid
generator system 10. The micro hybrid generator system 10 includes
a fuel source 12, e.g., a vessel for storing gasoline, a mixture of
gasoline and oil mixture, or similar type fuel or mixture. The fuel
source 12 provides fuel to a small engine 14, of a first power
system. The small engine 14 can use the fuel provided by the fuel
source 12 to generate mechanical energy. In one example, the small
engine 14 can have dimensions of about 12'' by 11'' by 6'' and a
weight of about 3.5 lbs. to allow for integration in a UAV. In one
example, the small engine 14 may be an HWC/Zenoah G29 RCE 3D
Extreme available from Zenoah, 1-9 Minamidai Kawagoe, Saitama
350-1165, Japan. The micro hybrid generator system 10 also includes
a generator motor 16 coupled to the small engine 14. The generator
motor 16 functions to generate AC output power using mechanical
power generated by the small engine 14. In various embodiments, a
shaft of the small engine 14 includes a fan that dissipates heat
away from the small engine 14. In various embodiments, the
generator motor 16 is coupled to the small engine 14 through a
polyurethane coupling.
[0035] In one embodiment, the micro hybrid generator system 10 can
provide 1.8 kW of power. Further in the embodiment, the micro
hybrid generator system 10 can include a small engine 14 that
provides approximately 3 horsepower and weighs approximately 1.5
kg, e.g. a Zenoah.RTM. G29RC Extreme engine. In the embodiment, the
micro hybrid generator system 10 includes a generator motor 16 that
is a brushless motor, 380 Kv, 8 mm shaft, part number 5035-380,
available from Scorpion Precision Industry.RTM.. In another
embodiment, the micro hybrid generator system 10 can provide 10 kW
of power. Further in the another embodiment, the micro hybrid
generator system 10 can include a small engine 14 that provides
approximately between 15-16.5 horsepower and weighs approximately 7
pounds, e.g. a Desert Aircraft.RTM. DA-150. In the another
embodiment, the micro hybrid generator system 10 includes a
generator motor 16 that is a Joby Motors.RTM. JM1 motor.
[0036] The micro hybrid generator system 10 includes a bridge
rectifier 18 and a rechargeable battery 20. The bridge rectifier 18
is coupled between the generator motor 16 and the rechargeable
battery 20 and converts the AC output of the generator motor 16 to
DC power to charge the rechargeable battery 20 or provide DC power
to load 78 by line 82 or power to DC-to-AC inverter 84 by line 86
to provide AC power to load 90. The rechargeable battery 20 may
provide DC power to load 92 by line 94 or to DC-to-AC inverter 96
by line 98 to provide AC power to load 100. In one example, an
output of the bridge rectifier 18 and/or the rechargeable battery
20 of micro hybrid generator system 10 is provided by line 102 to
one or more electronic speed control devices (ESC) 24 integrated in
one or more rotor motors 25 as part of an UAV. The ESC 24 can
control the DC power provided by bridge rectifier 18 and/or
rechargeable battery 20 to one or more rotor motors provided by
generator motor 16. In one example, the ESC 24 can be a
T-Motor.RTM. ESC 45A (2-6 S) with SimonK. In one example, the
bridge rectifier 18 can be a model #MSD I00-08, diode bridge 800V
IOOA SM3, available from Microsemi Power Products Group.RTM..
[0037] In various embodiments, the ESC 24 can control an amount of
power provided to one or more rotor motors 25 in response to input
received from an operator. For example, if an operator provides
input to move a UAV to the right, then the ESC 24 can provide less
power to rotor motors 25 on the right of the UAV to cause the rotor
motors to spin propellers on the right side of the UAV slower than
propellers on the left side of the UAV. As power is provided at
varying levels to one or more rotor motors 25, a load, e.g. an
amount of power provided to the one or more rotor motors 25, can
change in response to input received from an operator.
[0038] In one embodiment, the rechargeable battery 20 may be a LiPo
battery, providing 3000 mAh, 22.2V 65 C, Model PLU65-30006,
available from Pulse Ultra Lipo.RTM., China. In other designs, the
rechargeable battery 20 may be a lithium sulfur (LiSu) rechargeable
battery or similar type of rechargeable battery.
[0039] The micro hybrid generator system 10 includes an electronic
control unit (ECU) 22. The ECU 22, and other applicable systems
described in this paper, can be implemented as a computer system, a
plurality of computer systems, or parts of a computer system or a
plurality of computer systems. In general, a computer system will
include a processor, memory, non-volatile storage, and an
interface. A typical computer system will usually include at least
a processor, memory, and a device (e.g., a bus) coupling the memory
to the processor. The processor can be, for example, a
general-purpose central processing unit (CPU), such as a
microprocessor, or a special-purpose processor, such as a
microcontroller.
[0040] The memory can include, by way of example but not
limitation, random access memory (RAM), such as dynamic RAM (DRAM)
and static RAM (SRAM). The memory can be local, remote, or
distributed. The bus can also couple the processor to non-volatile
storage. The non-volatile storage is often a magnetic floppy or
hard disk, a magnetic-optical disk, an optical disk, a read-only
memory (ROM), such as a CD-ROM, EPROM, or EEPROM, a magnetic or
optical card, or another form of storage for large amounts of data.
Some of this data is often written, by a direct memory access
process, into memory during execution of software on the computer
system. The non-volatile storage can be local, remote, or
distributed. The non-volatile storage is optional because systems
can be created with all applicable data available in memory.
[0041] Software is typically stored in the non-volatile storage.
Indeed, for large programs, it may not even be possible to store
the entire program in the memory. Nevertheless, it should be
understood that for software to run, if necessary, it is moved to a
computer-readable location appropriate for processing, and for
illustrative purposes, that location is referred to as the memory
in this paper. Even when software is moved to the memory for
execution, the processor will typically make use of hardware
registers to store values associated with the software, and local
cache that, ideally, serves to speed up execution. As used herein,
a software program is assumed to be stored at an applicable known
or convenient location (from non-volatile storage to hardware
registers) when the software program is referred to as "implemented
in a computer-readable storage medium." A processor is considered
to be "configured to execute a program" when at least one value
associated with the program is stored in a register readable by the
processor.
[0042] In one example of operation, a computer system can be
controlled by operating system software, which is a software
program that includes a file management system, such as a disk
operating system. One example of operating system software with
associated file management system software is the family of
operating systems known as Windows.RTM. from Microsoft Corporation
of Redmond, Wash., and their associated file management systems.
Another example of operating system software with its associated
file management system software is the Linux operating system and
its associated file management system. The file management system
is typically stored in the non-volatile storage and causes the
processor to execute the various acts required by the operating
system to input and output data and to store data in the memory,
including storing files on the non-volatile storage.
[0043] The bus can also couple the processor to the interface. The
interface can include one or more input and/or output (I/O)
devices. The I/O devices can include, by way of example but not
limitation, a keyboard, a mouse or other pointing device, disk
drives, printers, a scanner, and other I/O devices, including a
display device. The display device can include, by way of example
but not limitation, a cathode ray tube (CRT), liquid crystal
display (LCD), or some other applicable known or convenient display
device. The interface can include one or more of a modem or network
interface. It will be appreciated that a modem or network interface
can be considered to be part of the computer system. The interface
can include an analog modem, isdn modem, cable modem, token ring
interface, Ethernet interface, satellite transmission interface
(e.g. "direct PC"), or other interfaces for coupling a computer
system to other computer systems. Interfaces enable computer
systems and other devices to be coupled together in a network.
[0044] A computer system can be implemented as a module, as part of
a module, or through multiple modules. As used in this paper, a
module includes one or more processors or a portion thereof. A
portion of one or more processors can include some portion of
hardware less than all of the hardware comprising any given one or
more processors, such as a subset of registers, the portion of the
processor dedicated to one or more threads of a multi-threaded
processor, a time slice during which the processor is wholly or
partially dedicated to carrying out part of the module's
functionality, or the like. As such, a first module and a second
module can have one or more dedicated processors, or a first module
and a second module can share one or more processors with one
another or other modules. Depending upon implementation-specific or
other considerations, a module can be centralized or its
functionality distributed. A module can include hardware, firmware,
or software embodied in a computer-readable medium for execution by
the processor. The processor transforms data into new data using
implemented data structures and methods, such as is described with
reference to the FIGS. in this paper.
[0045] The ECU 22 is coupled to the bridge rectifier 18 and the
rechargeable battery 20. The ECU 22 can be configured to measure
the AC voltage of the output of the generator motor 16, which is
directly proportional to the revolutions per minute (RPM) of the
small engine 14, and compares it to the DC power output of the
bridge rectifier 18. The ECU 22 can control the throttle of the
small engine 14 to cause the DC power output of the bridge
rectifier 18 to increase or decrease as the load changes, e.g., a
load of one or more electric motors 25 or one or more of loads 78,
90, 92, and 100. In one example, the ECU 22 can be an Arduino.RTM.
MEGA 2560 Board R3. In various embodiments, a load of one or more
electric motors 25 can change as the ESC 24 changes an amount of
power provided to the electric motors 25. For example, if a user
inputs to increase the power provided to the electric motors 25
subsequently causing the ESC 24 to provide more power to the
electric motors 25, then the ECU 22 can increase the throttle of
the small engine 14 to cause the production of more power to
provide to the electronic motors 25.
[0046] The ECU 22 can function to maintain voltage output of loads
by reading the sensed analog voltage, converting these to ADC
counts, comparing the count to that corresponding to a desired
voltage, and increasing or decreasing the throttle of the small
engine 14 according to the programmed gain if the result is outside
of the dead band.
[0047] In one example, the micro hybrid generator system 10 can
provide about 1,800 watts of continuous power, 10,000 watts of
instantaneous power (e.g., 6 S with 16,000 mAh pulse battery) and
has a 1,500 Wh/kg gasoline conversion rate. In one example, the
micro hybrid generator system 10 has dimensions of about 12'' by
12'' by 12'' and a weight of about 8 lbs.
[0048] FIG. 2 depicts a side perspective view of a micro hybrid
generator system 10. FIG. 3A depicts a side view of a micro hybrid
generator 10. FIG. 3B depicts an exploded side view of a micro
hybrid generator 10. The micro hybrid generator system 10 includes
a small engine 14 coupled to generator motor 16. In one embodiment,
the small engine 14 includes a coupling/cooling device 26 which
provides coupling of the shaft of the generator motor 16 to the
shaft of small engine 14 and also provides cooling with sink fins
27. For example, FIGS. 3A and 3B, show in further detail one
embodiment of coupling/cooling device 26, which includes
coupling/fan 28 with set screws 30 that couple shaft 32 of
generator motor 16 and shaft 34 of small engine 14.
Coupling/cooling device 26 may also include rubber coupling ring
36.
[0049] In various embodiments, the micro hybrid generator system 10
includes components to facilitate transfer of heat away from the
micro hybrid generator system 10 and/or is integrated within a UAV
to increase airflow over components that produce heat. For example,
the hybrid generator system 10 can include cooling fins on specific
components, e.g. the rectifier, to transfer heat away from the
micro hybrid generator system. In various implementations, the
micro hybrid generator system 10 includes components and is
integrated within a UAV to cause heat to be transferred towards the
exterior of the UAV.
[0050] In various embodiments, the micro hybrid generator system 10
and/or a UAV integrating the micro hybrid generator system 10 is
configured to allow 406 cubic feet per minute of airflow across at
least one component of the micro hybrid generator system 10. A
small engine 14 of the micro hybrid generator system 10 can be run
at an operating temperature 150.degree. C. and if an ambient
temperature in which the micro hybrid generator system 10, in order
to remove heat generated by the small engine 14, an airflow of 406
cubic feet per minute is achieved across at least the small engine
16. Further in various embodiments, the small engine 14 is operated
at 16.5 Horsepower and generates 49.2 kW of waste heat, e.g. each
head of the small engine produces 24.6 kW of waste heat. In various
embodiments, electric ducted fans are used to concentrate airflow
over the engine heads. For example, 406 cubic feet per minute
airflow can be achieved over engine heads of the small engine 14
using electric ducted fans.
[0051] In various embodiments, the micro hybrid generator system 10
is integrated as part of a UAV using a dual vibration damping
system. A small engine 14 of the micro hybrid generator system can
utilize couplings to accommodate for misalignment between the
engine and generator. A dual vibration damping system using both
compression and torsional dampers can provide damping between the
micro hybrid generator system 10 and a structure to which it is
mounted, e.g. a drone. In one example, the small engine 14 produces
a mean torque of 1.68 Nm at 10,000 RPM.
[0052] In various embodiments, a urethane coupling is used to
couple the small engine 14 to the generator motor 16. Further in
the one example, the urethane coupling can have a durometer value
of between 90 A to 75 D. Example urethane couplings used to secure,
at least part of, the micro hybrid generator system 10 to a UAV
include L42 Urethane, L100 Urethane, L167 Urethane, and L315
Urethane. Urethane couplings used to secure, at least part of, the
micro hybrid generator system 10 to a UAV can have a tensile
strength between 20 MPa and 62.0 MPa, between 270 to 800%
elongation at breaking, a modulus between 2.8 MPa and 32 MPa, an
abrasion index between 110% and 435%, and a tear strength split
between 12.2 kN/m and 192.2 kN/m.
[0053] Small engine 14, FIGS. 2 and 3, also includes fly wheel 38
which reduces mechanical noise and/or engine vibration. Preferably,
small engine 14 includes Hall Effect sensor 40, FIG. 3, and Hall
Effect magnet coupled to fly wheel 38 as shown. In one example,
Hall-effect sensor 40 may be available from RCexl Min
Tachometer.RTM., Zhejiang Province, China.
[0054] When small engine 14 is operational, fly wheel 38 spins at a
speed based on throttle. The spinning speed of fly wheel 38 is
measured by Hall effect sensor 40. The voltage generated by Hall
effect sensor 40 is input into an ECU 22. In various embodiments,
the ECU 22 compares the output by the generator motor 16 to ensure
that a proper voltage is maintained and the battery does not
discharge beyond a certain threshold. ECU 22 can then control the
throttle of either or both the generator motor 16 and the small
engine 14 to increase or decrease the voltage as needed to supply
power to one or more of loads 78, 90, 92, and/or 100 or one or more
rotor motors 25.
[0055] Small engine 14 may also include a starter motor 42, servo
44, muffler 46, and vibrational mount 48.
[0056] FIG. 4 is a perspective view of a micro hybrid generator
system 10. The micro hybrid generator system 10 includes a small
motor 14 and generator motor 16 coupled to a bridge rectifier
18.
[0057] FIG. 5 is a perspective view of a UAV 150 integrated with a
micro hybrid generator system 10. The UAV 150 includes six rotor
motors 25 each coupled to propellers 60, however it is appreciated
that a UAV integrated with a micro hybrid generator system 10 can
include more or less rotor motors and propeller. The UAV 150 can
include a Px4 flight controller.RTM. implemented as part of a 3 DR
Pixhawk.RTM..
[0058] In one embodiment, small engine 14, as shown in FIGS. 1-5
may be started using an electric starter 50. Fuel source 12, as
shown in FIG. 1 (also shown in FIG. 5) delivers fuel to small
engine 14 to spin its rotor shaft directly coupled to generator
motor 16 as shown in FIG. 3 and applies a force to generator motor
16. The spinning of generator motor 16 generates electricity and
the power generated by motor generator 16 is proportional to the
power applied by shaft of small engine 14. Preferably, a target
rotational speed of generator motor 16 is determined based on the
KV (rpm/V) of generator motor 16. For example, if a target voltage
of 25 Volt DC is desired, the rating of generator motor 16 would be
about 400 KV. The rotational speed of the small engine 14 may be
determined by the following equations:
RPM=KV (RPMVolt).times.Target Voltage (VDC) (1)
RPM=400 KV.times.25 VDC (2)
RPM=10,000 (3)
[0059] In this example, for generator motor 16 to generate 25 VDC
output, the shaft of generator motor 16 coupled to the shaft of
small engine 14 needs to spin at about 10,000 RPM. [0060] As the
load, e.g., one or more motors 25 or one or more of loads 78, 90,
92, and/or 100, is applied to the output of generator motor 16, the
voltage output of the battery drops, which is sensed by the ECU 22,
which subsequently can increase a throttle of the small engine 14.
In this case, ECU 22 can be used to help regulate the throttle of
small engine 14 to maintain a consistent output voltage that varies
with loads, preventing the system from losing power under load. ECU
22 can act like a standard governor for gasoline engines but
instead of regulating an RPM, it can regulate a target voltage
output of either or both a bridge rectifier and a generator motor
16 based on a closed loop feedback controller.
[0060] Power output from generator motor 16 can be in the form of
alternating current (AC) which needs to be rectified by bridge
rectifier 18. Bridge rectifier 18 can convert the AC power into
direct current (DC) power, as discussed above. In various
embodiments, the output power of the micro hybrid generator system
10 can be placed in a "serial hybrid" configuration, where the
generator power output by generator motor 16 may be available to
charge the rechargeable battery 20 or provide power to another
external load.
[0061] In operation, there can be at least two available power
sources when the micro hybrid generator system 10 is functioning. A
primary source can be from the generator motor 16 through directly
from the bridge rectifier and a secondary power source can be from
the rechargeable battery 20. Therefore, a combination of continuous
power availability and high peak power availability is provided,
which may be especially well-suited for UAV applications or a
portable generator applications. In cases where either primary
(generator motor 16) power source is not available, system 10 can
still continue to operate for a short period of time using power
from rechargeable battery 20 allowing a UAV to sustain safety
strategy, such as an emergency landing.
[0062] When micro hybrid generator system 10 is used for UAVs, the
following conditions can be met to operate the UAV effectively and
efficiently: 1) the total continuous power (watts) can be greater
than power required to sustain UAV flight, 2) the power required to
sustain a UAV flight is a function of the total weight of the
vehicle, the total weight of the hybrid engine, the total weight of
fuel, and the total weight of the payload), where:
Total Weight (gram)=vehicle dry weight+small engine 14 weight+fuel
weight+payload (4)
and, 3) based on the vehicle configuration and aerodynamics, a
particular lift motor will have an efficiency rating (grams/watt)
of 11, where:
Total Power Required to Fly=YJ.times.Weight (gram) (5)
[0063] In cases where the power required to sustain flight is
greater than the available continuous power, the available power or
total energy is preferably based on the size and configuration of
the rechargeable battery 20. A configuration of the rechargeable
battery 20 can be based on a cell configuration of the rechargeable
battery 20, a cell rating of the rechargeable battery 20, and/or
total mAh of the rechargeable battery 20. In one example, for a 6
S, 16000 mAh, 25 C battery pack, the total energy is determined by
the following equations:
Total Energy=Voltage.times.mAh=25 VDC (6 S).times.16000 mAh=400
Watt*Hours (6)
Peak Power Availability=Voltage.times.mAh.times.C Rating=25
VDC.times.16000 mAh.times.25 C=10,400 Watts (7)
Total Peak Time=400 Watt*Hours/10,400 Watts=138.4 secs (8)
Further in the one example, the rechargeable battery 20 will be
able to provide 10,400 Watts of power for 138.4 seconds in the
event of primary power failure from small engine 14. Additionally,
the rechargeable battery 20 may be able to provide up to 10,400
Watts of available power for flight or payload needs instantaneous
peak power for short periods of time needed for aggressive
maneuvers.
[0064] The result is micro hybrid generator system 10 when coupled
to a UAV efficiently and effectively provides power to fly and
maneuver the UAV for extended periods of time with higher payloads
than conventional multi-rotor UAVs. In one example, the micro
hybrid generator system 10 can provide a loaded (3 lb. load) flight
time of up to about 2 hours 5 mins, and an unloaded flight time of
about 2 hours and 35 mins Moreover, in the event that the fuel
source runs out or the small engine 14 and/or he generator motor 16
malfunctions, the micro hybrid generator system 10 can use the
rechargeable battery 20 to provide enough power to allow the UAV to
perform a safe landing. In various embodiments, the rechargeable
battery 20 can provide instantaneous peak power to a UAV for
aggressive maneuvers, for avoiding objects, or threats, and the
like.
[0065] In various embodiments, the micro hybrid generator system 10
can provide a reliable, efficient, lightweight, portable generator
system which can be used in both commercial and residential
applications to provide power at remote locations away from a power
grid and for a micro-grid generator, or an ultra-micro-grid
generator.
[0066] In various embodiments, the micro hybrid generator system 10
can be used for an applicable application, e.g. robotics, portable
generators, micro-grids and ultra-micro-grids, and the like, where
an efficient high energy density power source is required and where
a fuel source is readily available to convert hydrocarbon fuels
into useable electric power. The micro hybrid generator system 10
has been shown to be significantly more energy efficient than
various forms of rechargeable batteries (Lithium Ion, Lithium
Polymer, Lithium Sulfur) and even Fuel Cell technologies typically
used in conventional UAVs.
[0067] FIG. 6 depicts a graph comparing energy density of different
UAV power sources. In various embodiments, the micro hybrid
generator system 10 can use conventional gasoline which is readily
available at low cost and provide about 1,500 Wh/kg of power for
UAV applications, e.g., as indicated at 58 in FIG. 6. Conventional
UAVs which rely entirely on batteries can provide a maximum energy
density of about 1,000 Wh/kg when using an energy high density fuel
cell technology, indicated at 60 about 400 Wh/kg when using lithium
sulfur batteries, indicated at 62, and only about 200 Wh/kg when
using a LiPo battery, indicated at 64.
[0068] FIG. 7 depicts a graph of market potential for UAVs against
flight time for an example two plus hours of flight time micro
hybrid generator system 10 of one or more when coupled to a UAV is
able to achieve and an example of the total market potential vs.
endurance for the micro hybrid generator system 10 for UAVs of this
invention.
[0069] In various embodiments, the micro hybrid generator power
systems 10 can be integrated as part of a UAV or similar type
aerial robotic vehicle to perform as a portable flying generator
using the primary source of power to sustain flight of the UAV and
then act as a primary power source of power when the UAV has
reached its destination and is not in flight. For example, when a
UAV which incorporates micro hybrid system 10, e.g., UAV 150, FIG.
5, is not in flight, the available power generated by micro hybrid
system can be transferred to one or more of external loads 78, 90,
92, and/or 100 such that micro hybrid generator system 10 operates
as a portable generator. Micro hybrid system generator 10 can
provide continuous peak power generation capability to provide
power at remote and often difficult to reach locations. In the
"non-flight portable generator mode", micro hybrid system 10 can
divert the available power generation capability towards external
one or more of loads 78, 90, 92, and/or 100. Depending on the power
requirements, one or more of DC-to-AC inverters 84, 96 may be used
to convert DC voltage to standard AC power (120 VAC or 240
VAC).
[0070] In operation, micro hybrid generator system 10 coupled to a
UAV, such as UAV 150, FIG. 5, will be able to traverse from
location to location using aerial flight, land, and switch on the
power generator to convert fuel into power.
[0071] FIG. 8 shows an example flight pattern of a UAV with a micro
hybrid generator system 10. In the example flight pattern shown in
FIG. 8, the UAV 150, with micro hybrid system 10 coupled thereto,
begins at location A loaded with fuel ready to fly. The UAV 150
then travels from location A to location B and lands at location B.
The UAV 150 then uses micro hybrid system 10 to generate power for
local use at location B, thereby acting as a portable flying
generator. When power is no longer needed, the UAV 150 returns back
to location A and awaits instructions for the next task.
[0072] In various embodiments, the UAV 150 uses the power provided
by micro hybrid generator system 10 to travel from an initial
location to a remote location, fly, land, and then generate power
at the remote location. Upon completion of the task, the UAV 150 is
ready to accept commands for its new task. All of this can be
performed manually or through an autonomous/automated process. In
various embodiments, the UAV 150 with micro hybrid generator system
10 can be used in an applicable application where carrying fuel and
a local power generator are needed. Thus, the UAV 150 with a micro
hybrid generator system 10 eliminates the need to carry both fuel
and a generator to a remote location. The UAV 150 with a micro
hybrid generator system 10 is capable of powering both the vehicle
when in flight, and when not in flight can provide the same amount
of available power to external loads. This may be useful in
situations where power is needed for the armed forces in the field,
in humanitarian or disaster relief situations where transportation
of a generator and fuel is challenging, or in situations where
there is a request for power that is no longer available.
[0073] FIG. 9 depicts a diagram of another system for a micro
hybrid generator system 10 with detachable subsystems. FIG. 10a
depicts a diagram of a micro hybrid generator system 10 with
detachable subsystems integrated as part of a UAV. FIG. 10b depicts
a diagram of a micro hybrid generator system 10 with detachable
subsystems integrated as part of a ground robot. In various
embodiments, a tether line 201 is coupled to the DC output of bride
rectifier 18 and rechargeable battery 20 of a micro hybrid control
system 10. The tether line 201 can provide DC power output to a
tether controller 202. The tether controller 202 is coupled between
a tether cable 206 and a ground or aerial robot 208. In operation,
as discussed in further detail below, the micro hybrid generator
system 10 provides tethered power to the ground or aerial robot 208
with the similar output capabilities as discussed above with one or
more of the Figs. in this paper.
[0074] The system shown in FIG. 9 can include additional detachable
components 250 integrated as part of the system, e.g., data storage
equipment 252, communications equipment 254, external load sensors
256, additional hardware 258, and various miscellaneous equipment
260 that can be coupled via data tether 262 to tether controller
202.
[0075] In one example of operation of the system shown in FIG. 9,
the system may be configured as part of a flying robot or UAV, such
as flying robot or UAV 270, FIG. 10, or as ground robot 272.
Portable tethered robotic system 200 starts a mission at location
A. All or an applicable combination of the subsystems and ground,
the tether controller, ground/aerial robot 208 can be powered by
the micro hybrid generator system 10. The Portable tethered robotic
system 200 travels either by ground, e.g., using ground robot 272
powered by micro hybrid generator system 10 or by air using flying
robot or UAV 270 powered by micro hybrid generator system 10 to
desired remote location B. At location B, portable tethered robotic
system 200 configured as flying robot 270 or ground robot 272 can
autonomously decouple micro hybrid generator system 10 and/or
detachable subsystem 250, indicated at 274, which remain detached
while ground robot 272 or flying robot or UAV 270 are operational.
When flying robot or UAV 270 is needed at location B, indicated at
280, flying robot or UAV 270 can be operated using power provided
by micro hybrid generator system coupled to tether cable 206. When
flying robot or UAV 270 no longer has micro hybrid generator system
10 and/or additional components 250 attached thereto, it is
significantly lighter and can be in flight for a longer period of
time. In one example, flying robot or UAV 270 can take off and
remain in a hovering position remotely for extended periods of time
using the power provided by micro hybrid generator system 10.
[0076] Similarly, when ground robot 272 is needed at location B,
indicated at 290, it may be powered by micro hybrid generator
system 10 coupled to tether line 206 and will also be significantly
lighter without micro hybrid generator system 10 and/or additional
components 250 attached thereto. Ground robot 272 can also be used
for extended periods of time using the power provide by micro
hybrid generator system 10.
[0077] FIG. 11 shows a ground robot 300 with a detachable flying
pack in operation. The detachable flying pack 302 includes micro
hybrid generator system 10. The detachable flying pack is coupled
to the ground robot 300 of one or more embodiments. The micro
hybrid generator system 10 is embedded within the ground robot 300.
The ground robot 300 is detachable from the flying pack 302. With
such a design, a majority of the capability is embedded deep within
the ground robot 300 which can operate 100% independently of the
flying pack 302. When the ground robot 300 is attached to the
flying pack 302, the flying pack 302 is powered from micro hybrid
generator system 10 embedded in the ground robot 300 and the flying
pack 302 provides flight. The ground robot 300 platform can be a
leg wheel or threaded base motion.
[0078] In one embodiment, the ground robot 300 may include the
detachable flying pack 302 and the micro hybrid generator system 10
coupled thereto as shown in FIG. 11. In this example, the ground
robot 300 is a wheel-based robot as shown by wheels 304. In this
example, the micro hybrid generator system 10, includes fuel source
12, small engine 14, generator motor 16, bridge rectifier 18,
rechargeable battery 20, ECU 22, and optional inverters 84 and 96,
as discussed above with reference to one or more Figs. in this
paper. The micro hybrid generator system 10 also preferably
includes data storage equipment 252, communications equipment 254,
external load sensors 256, additional hardware 258, and
miscellaneous communications 260 coupled to data line 262 as shown.
The flying pack 302 is preferably, an aerial robotic platform such
as a fixed wing, single rotor or multi rotor, aerial device, or
similar type aerial device.
[0079] In one embodiment, the ground robot 300 and the aerial
flying pack 302 are configured as a single unit. Power is delivered
the from micro hybrid generator system 10 and is used to provide
power to flying pack 302, so that ground robot 300 and flying pack
302 can fly from location A to location B. At location B, ground
robot 304 detaches from flying pack 302, indicated at 310, and is
able to maneuver and operate independently from flying pack 302.
Micro hybrid generator system 10 is embedded in ground robot 300
such that ground robot 304 is able to be independently powered from
flying pack 302. Upon completion of the ground mission, ground
robot 300 is able to reattached itself to flying pack 302 and
return to location A. All of the above operations can be manual,
semi-autonomous, or fully autonomous.
[0080] In one embodiment, flying pack 302 can traverse to a remote
location and deliver ground robot 300. At the desired location,
there is no need for flying pack 302 so it can be left behind so
that ground robot 300 can complete its mission without having to
carry flying pack 302 as its payload. This may be useful for
traversing difficult and challenging terrains, remote locations,
and in situations where it is challenging to transport ground robot
300 to the location. Exemplary applications may include remote mine
destinations, remote surveillance and reconnaissance, and package
delivery services where flying pack 302 cannot land near an
intended destination. In these examples, a designated safe drop
zone for flying pack can be used and local delivery is completed by
ground robot 300 to the destination.
[0081] In various embodiments, then a mission is complete, ground
robot 272 or flying robot or UAV 270 can be autonomously coupled
back to micro hybrid generator system 10. Additional detachable
components 250 can auto be autonomously coupled back micro hybrid
generator system 10. Portable tethered robotic system 200 with a
micro hybrid generator system 10 configured a flying robot or UAV
270 or ground robot 272 then returns to location A using the power
provided by micro hybrid generator system 10.
[0082] The result is portable tethered robotic system 200 with a
micro hybrid generator system 10 is able to efficiently transport
ground robot 272 or flying robot or UAV 270 to remote locations,
automatically decouple ground robot 272 or flying robot or UAV 270,
and effectively operate the flying robot 270 or ground robot 272
using tether power where it may be beneficial to maximize the
operation time of the ground robot 270 or flying robot or UAV 272.
System 200 provides modular detachable tethering which may be
effective in reducing the weight of the tethered ground or aerial
robot thereby reducing its power requirements significantly. This
allows the aerial robot or UAV or ground robot to operate for
significantly longer periods of time when compared to the original
capability where the vehicle components are attached and the
vehicle needs to sustain motion. System 200 eliminates the need to
assemble a generator, robot and tether at remote locations and
therefore saves time, resources, and expense. Useful applications
of system 200 may include, inter alia, remote sensing, offensive or
defensive military applications and/or communications networking,
or multi-vehicle cooperative environments, and the like.
[0083] FIG. 12 shows a control system of a micro hybrid generator
system. The micro hybrid generator system includes a power plant
400 coupled to an ignition module 402. The ignition module 402
functions to start the power plant 400 by providing a physical
spark to the power plant 402. The ignition module 402 is coupled to
an ignition battery eliminator circuit (IBEC) 404. The IBEC 404
functions to power the ignition module 402.
[0084] The power plant 400 is configured to provide power. The
power plant 400 includes a small engine and a generator. The power
plant is controlled by the ECU 406. The ECU 406 is coupled to the
power plant through a throttle servo. The ECU 406 can operate the
throttle servo to control a throttle of a small engine to cause the
power plant 400 to either increase or decrease an amount of
produced power. The ECU 406 is coupled to a voltage divider 408.
Through the voltage divider 408, the ECU can determine an amount of
power the load/vehicle 414 is drawing to determine whether to
increase, decrease, or keep a throttle of a small engine
constant.
[0085] The power plant is coupled to a power distribution board
410. The power distribution board 410 can distribute power
generated by the power plant 400 to either or both a battery pack
412 and a load/vehicle 414. The power distribution board 410 is
coupled to a battery eliminator circuit (BEC) 416. The BEC 416
provides power to the ECU 406 and a receiver 418. The receiver 418
controls the IBEC 404 and functions to cause the IBEC 404 to power
the ignition module 402. The receiver 418 also sends information to
the ECU 406 used in controlling a throttle of a small engine of the
power plant 400. The receiver 418 to the ECU information related to
a throttle position of a throttle of a small engine and a mode in
which the micro hybrid generation system is operating.
[0086] FIG. 13 shows a top perspective view of a top portion 500 of
a drone powered through a micro hybrid generator system. The top
portion 500 of the drone shown in FIG. 13 includes six rotors 502-1
. . . 502-6 (hereinafter "rotors 502"). The rotors 502 are caused
to spin by corresponding motors 504-1 . . . 504-6 (hereinafter
"motors 504"). The motors 504 can be powered through a micro hybrid
generator system. The top portion 500 of a drone includes a top
surface 506. Edges of the top surface 506 can be curved to reduce
air drag and improve aerodynamic performance of the drone. The top
surface includes an opening 508 through which air can flow to aid
in dissipating heat away from at least a portion of a micro hybrid
generator system. In various embodiments, at least a portion of an
air filter is exposed through the opening 508.
[0087] FIG. 14 shows a top perspective view of a bottom portion 550
of a drone powered through a micro hybrid generator system 10. The
micro hybrid generator system 10 includes a small engine 14 and a
generator motor 16 to provide power to motors 504. The rotor motors
504 and corresponding rotors 502 are positioned away from a main
body of a bottom portion 550 of the drone through arms 552-1 . . .
552-6 (hereinafter "arms 552"). An outer surface of the bottom
portion of the bottom portion 550 of the drone and/or the arms 552
can have edges that are curved to reduce air drag and improve
aerodynamic performance of the drone.
[0088] FIG. 15 shows a top view of a bottom portion 550 of a drone
powered through a micro hybrid generator system 10. The rotor
motors 504 and corresponding rotors 502 are positioned away from a
main body of a bottom portion 550 of the drone through arms 552 An
outer surface of the bottom portion of the bottom portion 550 of
the drone and/or the arms 552 can have edges that are curved to
reduce air drag and improve aerodynamic performance of the
drone.
[0089] FIG. 16 shows a side perspective view of a micro hybrid
generator system 10. The micro hybrid generator system 10 shown in
FIG. 16 is capable of providing 1.8 kW of power. The micro hybrid
generator system 10 include a small engine 14 coupled to a
generator motor 16. The small engine 14 can provide approximately 3
horsepower. The generator motor 16 functions to generate AC output
power using mechanical power generated by the small engine 14.
[0090] FIG. 17 shows a side perspective view of a micro hybrid
generator system 10. The micro hybrid generator system 10 shown in
FIG. 17 is capable of providing 10 kW of power. The micro hybrid
generator system 10 include a small engine 14 coupled to a
generator motor. The small engine 14 can provide approximately
15-16.5 horsepower. The generator motor functions to generate AC
output power using mechanical power generated by the small engine
14.
[0091] 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.
* * * * *