KR20190026706A - Apparatus for hybrid series electrical power and its management method - Google Patents

Abstract

The present invention relates to an electric power operating system, and more specifically, to an electric power system of a quad tilt prop aircraft, including: a processor receiving a state of charge (SoC) level of a battery supplying electric power to a plurality of motors and determining the number of rotation of an engine supplying the electric power to a generator charging the battery and whether to operate the engine; and a control unit controlling output of the engine depending on the determined number of rotation or whether to operate the engine.

Description

TECHNICAL FIELD [0001] The present invention relates to a serial hybrid power device and a method for operating the hybrid hybrid power device,

To a device and method for providing power to a motor, and more particularly to an apparatus and method of operating a device that provides a serial hybrid power system that converts the power generated by the engine into electric power to operate the motor.

The hybrid system means a system that simultaneously provides an electric motor and an internal combustion engine as a power source. Compared with a general internal combustion engine, a hybrid system can use an internal combustion engine and an electric motor at the same time, so that the fuel consumption rate can be lowered.

There are serial, parallel, and hybrid systems in the hybrid power system. In the case of a distributed propulsion system that obtains propulsive force by using a plurality of propellers, a series hybrid system is mainly used.

Korean Patent No. 10-1667330 (Oct. 19, 2016) proposes a vertical takeoff and landing aircraft using a hybrid electric propulsion system. And determining the amount of power stored in the battery and the amount of power not stored in the battery.

According to one embodiment, a processor for receiving a state of charge (SoC) level of a battery that supplies power to a plurality of motors and determining the number of revolutions or the operation of the engine that supplies power to the generator charging the battery; And a control unit for controlling the output of the engine in accordance with the determined number of revolutions or the operation of the engine.

According to another embodiment, the processor may determine the number of revolutions of the engine to operate in a predetermined range, and the number of revolutions or operation of the engine so that the SoC level is maintained in a range of 50% to 100% It is also possible to determine whether.

According to another embodiment, a serial hybrid engine; A generator for generating electric power using power supplied from the engine; A battery for storing electric power produced by the generator; A plurality of motors rotated by power stored in the battery or power supplied from the generator; A processor for receiving an SoC (State of Charge) level of a battery that supplies power to the plurality of motors and determining the number of revolutions or the operation of the engine that supplies power to the generator charging the battery; And a controller for controlling the output of the engine according to the determined number of revolutions or the number of revolutions of the engine.

According to another embodiment, the processor determines whether the engine speed is in a predetermined range, or if the SoC level is within the range of 50% to 100% of the maximum level, A quad tilt prop aircraft is also disclosed.

According to an embodiment of the present invention, there is provided a quad tilt propulsion system further comprising a fuel tank for storing the fuel for driving the engine, the quad tilt prop aircraft including a fan for cooling any one of the generator, the processor, Prop aircraft is also available.

According to one aspect of the present invention, a processor for determining whether power is supplied to a first battery supplying electric power to a first motor group and a second battery supplying electric power to a second motor group according to a driving state; And a control unit for controlling power supply according to whether the first and second batteries are determined to be powered or not.

According to another aspect of the present invention, the processor determines that the first and second batteries supply power when the quad tilt prop aircraft is taken off or landing, and when either the cruise or the reuter, Lt; RTI ID = 0.0 > a < / RTI > quad tilt prop aircraft.

According to another aspect of the present invention, it is possible to determine whether or not to supply power to a first battery supplying electric power to the first motor group and a second battery supplying electric power to the second motor group according to the driving state, A processor for receiving the SoC (State of Charge) level and determining the number of revolutions or the operation of the engine for supplying power to the generator charging the battery; And a control unit for controlling power supply according to whether the first and second batteries are determined to be supplied with power and controlling the output of the engine according to the determined number of revolutions or the operation of the engine. It is possible.

According to another aspect, a processor receives a State of Charge (SoC) level of a battery that supplies power to a plurality of motors and determines whether the engine is operating at a rotational speed or operating to power a generator charging the battery ; And controlling the output of the engine in accordance with whether or not the number of revolutions of the engine is calculated.

According to another aspect of the present invention, there is also provided a method of operating a serial hybrid power device that determines the number of revolutions of the engine to be in a predetermined range when the processor determines the number of revolutions of the engine.

According to another aspect, the step of determining the number of revolutions or the operation of the engine includes determining whether the number of revolutions or the operation of the engine is controlled so that the SoC level is maintained in the range of 50% to 100% It may be a method of operating the power device.

According to one embodiment, the processor may determine whether power is supplied to the first battery supplying electric power to the first motor group and the second battery supplying electric power to the second motor group according to the driving state; And controlling the power supply according to whether or not the first and second batteries are supplied with power determined by the control unit.

1 is a block diagram illustrating a configuration of a serial hybrid power device according to an embodiment.
Figure 2 illustrates a quad tilt prop aircraft system including a serial hybrid power device in accordance with one embodiment.
FIG. 3 illustrates a serial hybrid quad tilt prop aircraft in accordance with one embodiment.
4 is a block diagram illustrating a configuration of a serial hybrid quad tilt prop aircraft according to an exemplary embodiment of the present invention.
5 shows the remaining capacity of the battery according to one embodiment.
6 shows the output range of the engine according to one embodiment.
7 is a flowchart illustrating a problem in which a motor according to an embodiment uses a high output for a long time.
FIG. 8 is a flowchart illustrating a solution when a motor according to an embodiment uses a high output power for a long time.
FIG. 9 illustrates a battery operation method of a quad tilt prop aircraft according to an embodiment.

Hereinafter, embodiments will be described in detail with reference to the accompanying drawings. However, the scope of the rights is not limited or limited by these embodiments. Like reference symbols in the drawings denote like elements.

The terms used in the following description are chosen to be generic and universal in the art to which they are related, but other terms may exist depending on the development and / or change in technology, customs, preferences of the technician, and the like. Accordingly, the terminology used in the following description should not be construed as limiting the technical thought, but should be understood in the exemplary language used to describe the embodiments.

Also, in certain cases, there may be a term chosen arbitrarily by the applicant, in which case the meaning of the detailed description in the corresponding description section. Therefore, the term used in the following description should be understood based on the meaning of the term, not the name of a simple term, and the contents throughout the specification.

1 is a block diagram illustrating a configuration of a serial hybrid power device according to an embodiment. The serial hybrid power device according to one embodiment may be comprised of a controller 130 and a processor 160 and may in some cases be coupled to the engine 110, the generator 120, the motor 140 and the battery 150 And may further include any one or more of them.

The engine 110 may be an internal combustion engine, specifically a reciprocating engine or a rotary engine. However, the present invention is not limited to this, and it may be an engine by generating power using fuel. The output of the engine may be expressed in RPM (Round Per Minute) and is controlled by the controller 130.

The generator 120 generates electrical power using the power transmitted from the engine 110. The generator 120 is directly connected to the drive shaft of the engine 110 using a coupling and is associated with starting and power generation of the engine 110. That is, the power generated when the engine 110 is started is transmitted to the generator 120 via the drive shaft, and the generator 120 operates.

The output of the generator 120 is also directly coupled to the controller 130. The output of the generator 120 may be a three-phase output.

The control unit 130 is connected to the engine 110, the generator 120, the motor 140, and the battery 150, and controls the respective components.

The processor 160 basically monitors the SOC (State Of Charge) level of the battery 150. The processor 160 continuously checks what percentage of the Maximum Charged State the SOC (residual capacity) level of the battery 150 corresponds to. The SOC level of the battery 150 is the most essential information for the control unit 130 to control other configurations. The processor 160 determines the number of revolutions or the operation of the engine corresponding to the SOC level based on the SOC level of the battery 150. [

For example, when the remaining capacity is 20% of the maximum storage capacity, it can be controlled in a direction to increase the output of the engine. More specifically, when the remaining capacity of the battery 150 is 20%, it is possible to increase the fuel injection to the engine and produce more power, so that the output of the engine can be determined to be 90%. In response to this, the output of the generator 120 is also determined to be high.

Conversely, when the remaining capacity of the battery 150 is 100%, it can be determined to stop the operation of the engine in accordance with the value. Alternatively, when the remaining capacity is 90%, it is also possible to determine that the output of the engine is maintained at 10%. The output of the engine corresponding to the present remaining capacity can be determined so that the remaining capacity does not exceed this range when the appropriate range of the remaining capacity is the remaining capacity from the minimum 50% to the maximum 100%.

The above values are exemplary values, but the present invention is not limited thereto, and the processor may determine the number of revolutions or the operation of the engine corresponding to the remaining capacity so that the remaining capacity may be a predetermined range or a predetermined value.

In addition, the control unit 130 may control the output of the engine 110 by using CAN (Controller Area Network) bus communication or wire.

In some cases, the motor 140 may be present, or may exist in plural. For example, if the proposed serial hybrid power unit is applied to a quad tilt prop aircraft, there can be four motors.

The motor 140 can utilize the electric power charged in the battery 150 or can directly use the electric power generated by the generator 120. Therefore, the motor 140 operates using the power of the generator 120 or the battery 150 without using the power of the engine 110 directly.

More specifically, the power generated by the engine 110 is converted into electric energy by the generator 120, and the electric energy may be stored in the battery 150 or transferred to the motor 140 and consumed.

The motor 140 may include a motor driver and may be connected to a thrust device to generate thrust. Illustratively but not exclusively, if the proposed serial hybrid power unit is a quad tilt prop aircraft, the motor 140 may be connected to a propeller so that the propeller generates thrust.

The battery 150 stores the power generated by the generator 120. The amount of power that can be stored in the battery 150 may vary depending on the size or type. The battery 150 may be a device capable of storing power regardless of its type. Illustratively, the battery may be any one of a lithium ion battery, a lithium polymer battery, and a nickel metal hydride battery, but is not limited thereto.

The battery 150 stores the electric power generated from the generator 120 and transfers it to the motor when necessary. DC converter (DC) for the motor when the reference voltage of the power generated by the power generator 120, the driving voltage of the motor 140, and the reference voltage of the battery 150 are all the same .

In addition, since the battery 150 is connected in series to the battery, it can continuously supply the required electric power of the motor 140, which varies in real time, and can transmit power even if the engine and the generator are broken or damaged.

Figure 2 illustrates a quad tilt prop aircraft system including a serial hybrid power device in accordance with one embodiment.

A quad tilt prop aircraft system including the proposed serial hybrid power system may be comprised of an engine 210, a generator 220, a controller 230, a battery 250 and a processor 260. Also shown is a quad tilt prop (QTP) aircraft 240 that includes a proposed serial hybrid power device.

1, the engine 210 generates power using fuel, and the power generator 220 receives the power to produce electric power. The generated power is directly connected to the controller 230, and the controller 230 transmits the received power to the quad tilt prop aircraft 240 or the battery 250. DC converter is not required when the power generated by the generator 220 and the reference voltage of the motor and the battery of the quad tilt prop aircraft 240 are the same.

The engine 210 and the control unit 230 may be connected using a CAN bus communication, and the control unit 230 and the battery 250 may be connected using a CAN bus communication.

The processor 260 is connected to the controller 230 to monitor the remaining capacity of the battery 250 and determine the appropriate number of revolutions or operation of the engine. The control unit 230 controls the engine in accordance with the determined number of revolutions or the operation of the engine.

FIG. 3 illustrates a serial hybrid quad tilt prop aircraft in accordance with one embodiment.

320, 330, and 340 in the case of a serial hybrid quad tilt prop aircraft 300. [ Each motor may further include a motor driver and a thrust device, and in the case of the quad tilt prop aircraft shown, the thrust device is a propeller. The present invention is not limited thereto.

Each of the motors 310, 320, 330, and 340 is connected in series with the battery 250, and is also connected to the controller 230 in series. The required power of each motor may be different from each other. The required power of the motors 330 and 340 located on the left side of the aircraft 300 when the quad tilt prop airplane 300 turns in the right direction is transmitted to the motors 310 and 320 located on the right side of the aircraft 300, Lt; / RTI > On the other hand, when the quad tilt prop airplane 300 turns leftward, the demanded power of the motors 310 and 320 located on the right side of the aircraft 300 is lower than the demand of the motors 330 and 340 located on the left side of the aircraft 300 Power. The difference in the required power is caused by the difference in the demanded power of the motor, which means that the greater the power consumption, the stronger the power can be generated. Also, since the motor is connected to the thrust device, strong power of the motor can generate strong thrust of the thrust device.

4 is a block diagram illustrating a detailed configuration of a serial hybrid quad tilt prop aircraft according to an exemplary embodiment of the present invention.

The serial hybrid quad tilt prop aircraft may comprise an engine 410, a generator 420, a controller 430, four motors 440, a battery 450 and a processor 460.

A fuel tank 411 is connected to the engine 410. The fuel tank 411 stores the fuel necessary for the operation of the engine, and transfers the fuel to the engine when the engine 410 operates.

The engine 410 generates power using fuel, and the power is transmitted to the generator to generate electric power.

The four motors 440 are connected to the thrust generator of the aircraft to generate thrust. Further, each of the motors 441 may be configured to further include a motor driver 442. [

5 shows the remaining capacity of the battery according to one embodiment. In Fig. 5, the battery is illustrated by way of example, and the shape of the battery is not limited as shown in the figure.

The remaining capacity (SOC) of the battery may be from 0% to 100%. When the remaining capacity is 100%, it means that it is full by the maximum charge capacity. Conversely, 0% means that no battery power remains.

In the proposed serial hybrid power device, the remaining capacity (SOC) of the battery is regulated by the processor and the control unit.

According to one embodiment, the remaining capacity of the battery can be set to 60% or more and 90% or less. If the quad tilt prop aircraft is used for long periods of time such as vertical takeoff and landing or hover flight, the remaining capacity may be reduced to less than 60%. At this time, the processor determines the number of revolutions of the engine corresponding to less than 60% of the remaining capacity, and the control unit controls the engine according to the determined number of revolutions of the engine. In this case, the control unit may increase the number of revolutions of the engine to increase the remaining capacity of the battery to more than 60% in the direction of increasing the power generation amount of the generator.

6 shows the output range of the engine according to one embodiment. The output of the engine is controlled by the control unit as well as the battery.

The output of the engine may vary depending on the type of engine used, but the output range of each engine is from zero output (no rotation) to maximum output (maximum rotation). If the zero output is 0% and the maximum output is 100%, the control unit can adjust the engine output range.

The output of the engine is directly connected to the number of revolutions of the engine. The higher the number of revolutions of the engine, the higher the output of the engine. On the contrary, when the operation of the engine is stopped or the revolution speed is low, the output of the engine is low or low.

By way of example, to increase the efficiency of the fuel, the engine output can be controlled to be maintained at around 70% of the maximum output. In FIG. 6, the output of the engine is shown to operate at about 70% of its maximum output to maintain fuel efficiency.

On the other hand, when a large amount of power is required in the motor, the output of the engine can be increased to 100% of the maximum output. If the remaining capacity of the battery is 100% and the motor requires only a small amount of power, 20%.

7 is a flowchart illustrating a problem in which a motor according to an embodiment uses a high output for a long time.

Step 710 is a step in which the motor uses a high output power for a long time. In this case, a problem may arise. When the motor uses high output for a long time, it may be an example of high-speed flight (or traveling), vertical takeoff and landing, hover flight, and the like.

Step 720 is a step of reducing the battery capacity (remaining capacity). Since the motor receives power directly from the battery or the generator, if the motor uses a high output for a long time, the remaining capacity of the battery decreases.

Step 730 is a step in which the power bus voltage drops. As the remaining capacity of the battery is rapidly reduced, the voltage of the power supply bus is lowered.

Step 740 is the step of increasing the output of the generator. The generators used in the serial hybrid method are all-position generators that increase the output of the generator when the power bus voltage is lower than the target voltage. Control of the output of the generator is performed by the control unit.

Step 750 is an engine speed reduction step. When the output of the generator is increased, the number of revolutions of the engine is reduced.

Step 760 is a step in which a stall occurs. As the output of the generator increases, the number of revolutions of the engine decreases, and when the number of revolutions of the engine falls below a certain level, stall may occur.

FIG. 8 is a flowchart illustrating a solution when a motor according to an embodiment uses a high output power for a long time.

Step 810 is a step in which the motor uses a high output power for a long time similarly to the step 710.

Step 820 is to keep the output of the engine at a maximum. In FIG. 7, a case where a problem occurs when a long time high output power is used has been described. As a solution, the controller and the processor perform step 820. FIG. When the motor uses high output for a long time, the remaining capacity of the battery is drastically reduced. If the processor that monitors the remaining capacity determines to keep the engine speed at the maximum, the control unit can control the engine to the maximum output (maximum engine speed) to prevent engine speed reduction and stall.

Step 830 is a step of preventing over-powering of the engine. The control unit maintains the engine at the vicinity of the maximum output and at the same time does not overload the engine. And there is a risk that the engine will run out of power and generate fire or breakdown when an output occurs.

FIG. 9 illustrates a battery operation method of a quad tilt prop aircraft according to an embodiment.

The quad tilt prop aircraft according to an embodiment includes a processor 960 for determining whether to supply power to the first and second batteries and a power supply controller 960 for supplying power to the first and second batteries 951 and 952 And a control unit 930 for controlling the control unit 930. The quad tilt prop aircraft may further include a first battery 951 for supplying power to the first motor group 941 and a second battery 952 for supplying power to the second motor group 942 .

More specifically, when a quad tilt prop aircraft is taking off or landing, all the propellers must be running and all the motors must be powered. Thus, the processor 960 may determine that both the first and second batteries 951 and 952 supply power.

On the other hand, when the quad tilt prop aircraft is cruising or loiter, since there is no need for much power, only one of the first motor group 941 and the second motor group 942 can be operated. Illustratively, when only the second motor group 942 is operated, the first motor group 941 may not operate. In addition, a propeller blade connected to the first motor group 941 is formed of a folding type and can reduce the air resistance of the quad tilt prop aircraft when it is not operated by folding, And the flight speed can be increased.

According to one embodiment, since the second motor group 941 operates in all situations such as take-off, landing, cruise, and Reuters, the engine is operated by the processor so that the SoC (remaining capacity) level of the second battery 952 is optimized And can be driven so as to be maintained at a point. Since all of the power generated by the engine is used for driving the motor, the capacity of the battery is not exhausted, and thus the second battery 952 can use a battery having a capacity smaller than that of the first battery 951.

The processor 960 can determine whether to supply power to the first and second batteries 951 and 952 and adjust the output of the engine corresponding to the SoC level of the first and second batteries 951 and 952 It is possible. Illustratively, but not exclusively, the SoC level of the second battery 952 may be maintained at 90% of the maximum level, and the SoC level of the first battery 951 may be determined to be 90% of the maximum level. The maximum SoC level of a battery may vary depending on the capacity of each battery.

The control unit 930 can control the power supply of each battery, whether or not the engine is operated, and the number of rotations according to the power supply of the battery and the SoC level determined by the processor 960.

The apparatus described above may be implemented as a hardware component, a software component, and / or a combination of hardware components and software components. For example, the apparatus and components described in the embodiments may be implemented within a computer system, such as, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, a microcomputer, a field programmable array (FPA) A programmable logic unit (PLU), a microprocessor, or any other device capable of executing and responding to instructions. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For ease of understanding, the processing apparatus may be described as being used singly, but those skilled in the art will recognize that the processing apparatus may have a plurality of processing elements and / As shown in FIG. For example, the processing unit may comprise a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as a parallel processor.

The software may include a computer program, code, instructions, or a combination of one or more of the foregoing, and may be configured to configure the processing device to operate as desired or to process it collectively or collectively Device can be commanded. The software and / or data may be in the form of any type of machine, component, physical device, virtual equipment, computer storage media, or device , Or may be permanently or temporarily embodied in a transmitted signal wave. The software may be distributed over a networked computer system and stored or executed in a distributed manner. The software and data may be stored on one or more computer readable recording media.

The method according to an embodiment may be implemented in the form of a program command that can be executed through various computer means and recorded in a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions to be recorded on the medium may be those specially designed and configured for the embodiments or may be available to those skilled in the art of computer software. Examples of computer-readable media include magnetic media such as hard disks, floppy disks and magnetic tape; optical media such as CD-ROMs and DVDs; magnetic media such as floppy disks; Magneto-optical media, and hardware devices specifically configured to store and execute program instructions such as ROM, RAM, flash memory, and the like. Examples of program instructions include machine language code such as those produced by a compiler, as well as high-level language code that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the embodiments, and vice versa.

Although the embodiments have been described with reference to the drawings, various modifications and variations may be made by those skilled in the art. For example, it is to be understood that the techniques described may be performed in a different order than the described methods, and / or that components of the described systems, structures, devices, circuits, Lt; / RTI > or equivalents, even if it is replaced or replaced.

Therefore, other implementations, other embodiments, and equivalents to the claims are also within the scope of the following claims.

110, 210, 410: engine
120, 220, 420: generator
130, 230, 430:
140, 240, 440: motor
150, 250, 450: Battery

Claims (3)

A processor for determining whether power is supplied to a first battery supplying electric power to the first motor group and a second battery supplying electric power to the second motor group according to the driving state; And
And a controller for controlling power supply according to whether the first and second batteries are supplied with power,
Lt; / RTI >
The processor comprising:
Wherein the first and second batteries are configured to supply power when the quad tilt prop aircraft is taking off or landing and to supply power to any one of the first and second batteries during cruise or re- The propeller connected to the power supply group determines to collapse,
Wherein the first motor group or the second motor group determines that the number of rotations of the engine operates at a maximum when using an output that is specified in advance for a predetermined time or more.
The method according to claim 1,
The processor comprising:
Wherein the first and second batteries are configured to supply power when the quad tilt prop aircraft is taking off or landing, and the quad tilt prop probe determines whether to supply power only to either the first or second battery when cruising or re- aircraft.
The first battery and the second battery supplying electric power to the first motor group and the second battery group are determined according to the driving state, and the State of Charge (SoC) of the first and second batteries ) Level to determine the number of revolutions or the operation of the engine that powers the generator charging the battery; And
And controls the power supply according to whether or not the first and second batteries are supplied with power, and controls the output of the engine according to the determined number of revolutions or the operation of the engine.
Lt; / RTI >
The processor comprising:
Wherein the first and second batteries are configured to supply power when the quad tilt prop aircraft is taking off or landing and to supply power to any one of the first and second batteries during cruise or re- The propeller connected to the power supply group determines to collapse,
Wherein the first motor group or the second motor group determines that the number of rotations of the engine operates at a maximum when using an output that is specified in advance for a predetermined time or more.

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