CN116639250A - Parallel type oil-electricity hybrid power system and aircraft - Google Patents
Parallel type oil-electricity hybrid power system and aircraft Download PDFInfo
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- CN116639250A CN116639250A CN202310343676.XA CN202310343676A CN116639250A CN 116639250 A CN116639250 A CN 116639250A CN 202310343676 A CN202310343676 A CN 202310343676A CN 116639250 A CN116639250 A CN 116639250A
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Abstract
The application provides a parallel type oil-electricity hybrid power system and an aircraft, wherein the power system comprises: the lithium battery pack comprises an engine, a driving motor, a lithium battery pack, a current conversion device, a voltage conversion device, a driving motor controller, an engine ECU, a battery management module and a mixed control module; the engine is connected with the hybrid control module through the engine ECU, the driving motor is connected with the hybrid control module through the driving motor controller, one end of the lithium battery pack is connected with the hybrid control module through the battery management module, the other end of the lithium battery pack is simultaneously connected with the current conversion device and the voltage conversion device, and the current conversion device is connected with the voltage conversion device. The application can reduce the consumption of fossil fuel by the aircraft, reduce the emission of greenhouse gases, improve the overall output power and the power-weight ratio of the power system of the aircraft and improve the integration level of the hybrid power system.
Description
[ field of technology ]
The application relates to the technical field of structural design and electrical design of an aircraft power system, in particular to a parallel type oil-electricity hybrid power system and an aircraft.
[ background Art ]
The energy density of the battery cell is far lower than that of fossil fuel due to the development limit of the prior battery technology, and the cruising ability and the power-weight ratio of the pure electric aircraft are far lower than those of the aircraft driven by the traditional power. Therefore, the hybrid electric powertrain is the optimal transition scheme in the process of converting the conventional power system to the pure electric power system. The conventional aircraft with the hybrid electric vehicle is a series hybrid electric vehicle, but the series hybrid electric vehicle outputs the same power with a greater weight cost than the parallel hybrid electric vehicle, which results in a reduced payload of the aircraft.
Accordingly, there is a need to develop a parallel hybrid electric power system and an aircraft that address the deficiencies of the prior art to solve or mitigate one or more of the problems described above.
[ application ]
In view of the above, the application provides a parallel type oil-electricity hybrid power system and an aircraft, which aim to reduce the consumption of fossil fuel by the aircraft, reduce the emission of greenhouse gases, improve the overall output power and the power-weight ratio of the power system of the aircraft and improve the integration level of the hybrid power system.
In one aspect, the present application provides a parallel hybrid electric power system, the power system comprising:
the engine is used for providing power for the aircraft and driving the motor to generate electricity;
the driving motor is used for providing power for the aircraft and outputting electric energy;
the lithium battery pack is used for storing the electric energy output by the driving motor and outputting the electric energy to the driving motor;
the current conversion device is used for converting direct current released by the lithium battery pack into alternating current;
the voltage conversion device is used for increasing or decreasing the direct-current voltage released by the lithium battery pack;
a driving motor controller for controlling the output power of the driving motor;
an engine ECU for controlling the output power of the engine;
the battery management module is used for detecting the state of the lithium battery pack;
the hybrid control module is used for outputting a driving motor operation mode, driving motor output power and generating driving motor output power;
the engine is connected with the hybrid control module through the engine ECU, the driving motor is connected with the hybrid control module through the driving motor controller, one end of the lithium battery pack is connected with the hybrid control module through the battery management module, the other end of the lithium battery pack is simultaneously connected with the current conversion device and the voltage conversion device, and the current conversion device is connected with the voltage conversion device.
In aspects and any one of the possible implementations described above, there is further provided an implementation, the voltage conversion device including a high-voltage DC-DC power supply module and a low-voltage DC-DC power supply module;
in a driving mode, the low-voltage conversion DC-DC power supply module is communicated with the current conversion device through the lithium battery pack, and the high-voltage conversion DC-DC power supply module is not communicated;
in the power generation mode, the current conversion device is simultaneously communicated with the high-voltage DC-DC power supply module and the low-voltage DC-DC power supply module, and the high-voltage power supply module is also simultaneously communicated with the lithium battery pack and the mixed motion control module.
In aspects and any one of the possible implementations described above, there is further provided an implementation, the current conversion device is an AC-DC power supply.
In accordance with aspects and any one of the possible implementations described above, there is further provided an implementation, the power system further including an on-board device connected to the transfer low voltage DC-DC power module.
In the aspect and any possible implementation manner as described above, there is further provided an implementation manner, wherein the power coupling manner of the engine and the driving motor is a parallel shaft structure.
In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the power system further includes a throttle control device, where the throttle control device is used for outputting a throttle opening command, and the throttle control device is connected to the hybrid control module.
In the aspect and any possible implementation manner described above, there is further provided an implementation manner, wherein the design withstand voltage values of the driving motor, the driving motor controller, the AC-DC power supply, the high-voltage DC-DC power supply module and the low-voltage DC-DC power supply module are all greater than 300V.
In the aspect and any possible implementation manner, there is further provided an implementation manner, in the power generation mode, alternating current generated by the driving motor is greater than 200V, and direct current voltage boosted by the high-voltage conversion DC-DC power supply module is greater than voltage when the lithium battery pack is full.
In the aspect and any possible implementation manner described above, there is further provided an implementation manner, where the lithium battery pack is a ternary system lithium battery, and a minimum voltage of the lithium battery pack is greater than 300V, and when the electric quantity of the lithium battery is sufficient, the engine and the driving motor will jointly drive the propeller to provide power for the aircraft.
In accordance with the above aspect and any possible implementation manner, there is further provided a parallel hybrid vehicle, where the parallel hybrid vehicle is equipped with a propeller and the power system, and the propeller is connected to an engine and a driving motor at the same time.
Compared with the prior art, the application can obtain the following technical effects:
the parallel type oil-electricity hybrid power aircraft power system is electrified and upgraded on the basis of traditional power, so that the power performance of an engine is effectively improved, the pollutant emission of the engine is reduced, the oil consumption of the engine is improved, and the fuel economy is improved.
Of course, it is not necessary for any of the products embodying the application to achieve all of the technical effects described above at the same time.
[ description of the drawings ]
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a parallel hybrid electric vehicle power system in a drive mode of the present application;
FIG. 2 is a schematic diagram of a parallel hybrid electric vehicle power system in a generating mode of the present application;
FIG. 3 is a block diagram of a parallel hybrid electric vehicle transmission system of the present application.
Wherein, in the figure:
1. a propeller; 2. a transmission system; 3. an engine; 4. an engine ECU; 5. a driving motor; 6. an AD-DC power supply; 7. a drive motor controller; 8. a hybrid control module HCU; 9. an accelerator opening command; 10. a high-voltage DC-DC power supply module; 11. a lithium battery pack; 12. a battery management system BMS; 13. a low-voltage DC-DC power supply module; 14. an onboard device; 16. a gear; 17. driving a motor spindle; 18. a gear; 19. an engine output shaft.
[ detailed description ] of the application
For a better understanding of the technical solution of the present application, the following detailed description of the embodiments of the present application refers to the accompanying drawings.
It should be understood that the described embodiments are merely some, but not all, embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
The terminology used in the embodiments of the application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used in this application and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise.
The application provides a parallel type oil-electricity hybrid power system, which comprises: the engine is used for providing power for the aircraft and driving the motor to generate electricity; the driving motor is used for providing power for the aircraft and outputting electric energy; the lithium battery pack is used for storing the electric energy output by the driving motor and outputting the electric energy to the driving motor; the current conversion device is used for converting direct current released by the lithium battery pack into alternating current; the voltage conversion device is used for increasing or decreasing the direct-current voltage released by the lithium battery pack; a driving motor controller for controlling the output power of the driving motor; an engine ECU for controlling the output power of the engine; the battery management module is used for detecting the state of the lithium battery pack; the hybrid control module is used for outputting a driving motor operation mode, driving motor output power and generating driving motor output power;
the engine is connected with the hybrid control module through the engine ECU, the driving motor is connected with the hybrid control module through the driving motor controller, one end of the lithium battery pack is connected with the hybrid control module through the battery management module, the other end of the lithium battery pack is simultaneously connected with the current conversion device and the voltage conversion device, and the current conversion device is connected with the voltage conversion device.
The voltage conversion device comprises a high-voltage DC-DC power supply module and a low-voltage DC-DC power supply module;
in a driving mode, the low-voltage conversion DC-DC power supply module is communicated with the current conversion device through the lithium battery pack, and the high-voltage conversion DC-DC power supply module is not communicated;
in the power generation mode, the current conversion device is simultaneously communicated with the high-voltage DC-DC power supply module and the low-voltage DC-DC power supply module, and the high-voltage power supply module is also simultaneously communicated with the lithium battery pack and the mixed motion control module.
The current conversion device is an AC-DC power supply. The power system also comprises an onboard device, and the onboard device is connected with the rotary low-voltage DC-DC power supply module. The engine is connected with the driving motor in a power coupling mode, the power coupling mode is of a parallel shaft structure, the power system further comprises an accelerator control device, the accelerator control device is used for outputting an accelerator opening instruction, and the accelerator control device is connected with the hybrid control module. The voltage withstand values of the driving motor, the driving motor controller, the AC-DC power supply, the high-voltage DC-DC power supply conversion module and the low-voltage DC-DC power supply conversion module are all larger than 300V. In the power generation mode, alternating current generated by the driving motor is larger than 200V, and direct current voltage boosted by the high-voltage DC-DC power supply module is larger than voltage when the lithium battery pack is full. The lithium battery pack is a ternary system lithium battery, the lowest voltage of the lithium battery pack is greater than 300V, and when the electric quantity of the lithium battery is sufficient, the engine and the driving motor drive the propeller together to provide power for the aircraft.
The application also provides a parallel type oil-electricity hybrid power aircraft, which is provided with a propeller and the power system, wherein the propeller is connected with an engine and a driving motor at the same time.
The power system comprises an engine capable of providing power for a propeller and driving a motor to generate power, a motor capable of providing power for the propeller and having power generation capacity, a lithium battery pack capable of providing electric energy for the motor, an AC-DC power module capable of converting direct current released by the lithium battery pack into alternating current, a motor controller capable of controlling output power of the motor, an engine ECU capable of controlling output power of the engine, a high-voltage conversion DC-DC power module capable of raising direct current voltage, a battery management system BMS capable of detecting the state of the lithium battery pack, a low-voltage conversion DC-DC power module capable of reducing high voltage of the lithium battery pack, the propeller, a hybrid control module HCU and airborne equipment.
The hybrid control module HCU8 needs to communicate with the engine ECU4, the driving motor controller 7, the battery management system 12, and the high-voltage DC-DC power module in real time.
The hybrid control module HCU8 has the functions of power-on and power-off control, heat management, communication interaction to an upper computer, energy flow analysis, output power and generation power decision, device state judgment, fault diagnosis and analysis and safety protection.
And after receiving the accelerator opening instruction, the hybrid control module judges the driving motor mode and distributes the output power according to the current lithium battery pack electric quantity state, the on-board equipment electric consumption state, the maximum output power of the engine and the maximum output power of the driving motor, and starts the calculated power distribution information to the engine ECU and the driving motor controller.
The battery management system BMS has the functions of battery voltage detection, battery current detection, battery electric quantity detection and battery temperature detection.
The output power of the high-voltage DC-DC power supply module can be adjusted in real time according to the power consumption requirement of the airborne equipment, and the lithium battery pack can be charged in a constant current or constant voltage mode.
The power coupling mode of the engine and the driving motor adopts a parallel shaft structure. The parallel shaft structure can utilize driving motor reverse dragging engine when the engine starts, helps the engine to start.
The driving motor is an outer rotor type air-cooled permanent magnet synchronous alternating current driving motor.
Example 1:
as shown in fig. 1, the application provides a parallel hybrid electric power system and an aircraft, wherein the aircraft comprises a propeller 1, a transmission system 2, an engine 3, an engine ECU4, a driving motor 5, an AC-DC power module 6, a driving motor controller 7, a hybrid control module HCU8, an accelerator opening instruction 9, a high-voltage-to-DC power module 10, a lithium battery pack 11, a battery management system BMS12, a low-voltage-to-DC power module 13 and an onboard device 14.
Specifically, as shown in fig. 1, when the electric quantity of the lithium battery pack 11 is sufficient (greater than 20%), the driving motor 5 is in a motor mode, the driving motor and the engine 3 jointly drive the propeller 1 through the transmission system 2, the lithium battery pack 11 is connected with the AC-DC power module 6, high-voltage direct current is converted into high-voltage alternating current to supply electric energy for the driving motor 5, and the lithium battery pack 11 is connected with the low-voltage DC-DC power module 13 to supply electric energy for the on-board equipment 14.
Specifically, as shown in fig. 1, when the driving motor 5 is in the motor mode and drives the propeller 1 together with the engine 3, after receiving the accelerator opening command 9, the hybrid control module HCU8 performs output power distribution according to the current state of charge of the lithium battery pack 11, the power consumption state of the on-board device 14, the maximum output power of the engine 3, and the maximum output power of the driving motor 5, and sends the calculated power value required to be output by the engine 3 to the engine ECU4, and uses the engine ECU4 to perform output power control on the engine 3, and sends the calculated power value required to be output by the driving motor 5 to the driving motor controller 7, and uses the driving motor controller 7 to perform output power control on the driving motor 5.
Specifically, as shown in fig. 2, when the electric quantity of the lithium battery pack 11 is insufficient (less than or equal to 20%), the driving motor 5 is switched to a power generation driving motor mode, the engine 3 drives the propeller 1 through the transmission system 2, meanwhile, the driving motor 5 is driven to generate power through the transmission system 2, high-voltage alternating current generated by the driving motor 5 is converted into high-voltage direct current through the AC-DC power supply module 6, a part of the electric energy is charged into the lithium battery pack 11 through the high-voltage DC-DC power supply module 10, and the other part of the electric energy is supplied to the on-board equipment 14 through the low-voltage DC-DC power supply module 13.
Specifically, as shown in fig. 2, when the driving motor 5 is in the power generation driving motor mode, the engine 3 needs to drive the propeller 1 and the driving motor 5 at the same time, after receiving the accelerator opening command 9, the hybrid control module HCU8 calculates the required output power of the engine 3 according to the current state of charge of the lithium battery pack 11, the power consumption state of the on-board device 14, the maximum output power of the engine 3, and the maximum power generation power of the driving motor 5, and sends the calculated value of the required output power of the engine 3 to the engine ECU4, the engine 3 is controlled by the engine ECU4, the value of the required power generation power of the driving motor 5 calculated by the hybrid control module HCU8 is sent to the driving motor controller 7, the driving motor 5 is controlled by the driving motor controller 7, and in order to meet the power consumption requirement of the on-board device 14, the hybrid control module HCU8 also needs to real-time computer-load the power consumption of the on-board device 14, and meets the power consumption of the device by adjusting the output power of the high-voltage DC-DC power supply module.
The CAN bus communication or serial communication CAN be used for transmitting the power information in the process.
The power coupling of the drive motor and the engine is achieved by a parallel shaft configuration as shown in fig. 3. The parallel shaft structure can utilize driving motor to reverse drag the engine when the engine starts, helps the engine start, and this structure can effectively realize driving motor and engine power output coupling, also can realize that driving motor becomes the load after, the power transmission of engine to driving motor. The lithium battery pack 11 can be charged at the ground level. The hybrid control module HCU8 needs to communicate with the engine ECU4, the driving motor controller 7, the battery management system 12, and the high-voltage DC-DC power module in real time. The hybrid control module HCU8 will perform energy flow analysis, device status determination, fault diagnosis and analysis on the power system.
Preferably, the driving motor 5 is an air-cooled outer rotor permanent magnet synchronous alternating current driving motor, which has the advantages of high output torque and high power density, and is more suitable for being applied to the field of aircrafts.
Preferably, the lithium battery 11 is a ternary system lithium battery, which has the advantages of high energy density, safety, reliability and mature system.
The parallel type oil-electricity hybrid power system and the aircraft provided by the embodiment of the application are described in detail. The above description of embodiments is only for aiding in the understanding of the method of the present application and its core ideas; meanwhile, as those skilled in the art will have variations in the specific embodiments and application scope in accordance with the ideas of the present application, the present description should not be construed as limiting the present application in view of the above.
Certain terms are used throughout the description and claims to refer to particular components. Those of skill in the art will appreciate that a hardware manufacturer may refer to the same component by different names. The description and claims do not take the form of an element differentiated by name, but rather by functionality. As referred to throughout the specification and claims, the terms "comprising," including, "and" includes "are intended to be interpreted as" including/comprising, but not limited to. By "substantially" is meant that within an acceptable error range, a person skilled in the art is able to solve the technical problem within a certain error range, substantially achieving the technical effect. The description hereinafter sets forth a preferred embodiment for practicing the application, but is not intended to limit the scope of the application, as the description is given for the purpose of illustrating the general principles of the application. The scope of the application is defined by the appended claims.
It should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a product or system that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such product or system. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a commodity or system comprising such elements.
It should be understood that the term "and/or" as used herein is merely one relationship describing the association of the associated objects, meaning that there may be three relationships, e.g., a and/or B, may represent: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.
While the foregoing description illustrates and describes the preferred embodiments of the present application, it is to be understood that the application is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the inventive concept as expressed herein, either as a result of the foregoing teachings or as a result of the knowledge or technology of the relevant art. And that modifications and variations which do not depart from the spirit and scope of the application are intended to be within the scope of the appended claims.
Claims (10)
1. A parallel hybrid electric power system for an aircraft, the power system comprising:
the engine is used for providing power for the aircraft and driving the motor to generate electricity;
the driving motor is used for providing power for the aircraft and outputting electric energy;
the lithium battery pack is used for storing the electric energy output by the driving motor and outputting the electric energy to the driving motor;
the current conversion device is used for converting direct current released by the lithium battery pack into alternating current;
the voltage conversion device is used for increasing or decreasing the direct-current voltage released by the lithium battery pack;
a driving motor controller for controlling the output power of the driving motor;
an engine ECU for controlling the output power of the engine;
the battery management module is used for detecting the state of the lithium battery pack;
the hybrid control module is used for outputting a driving motor operation mode, driving motor output power and generating driving motor output power;
the engine is connected with the hybrid control module through the engine ECU, the driving motor is connected with the hybrid control module through the driving motor controller, one end of the lithium battery pack is connected with the hybrid control module through the battery management module, the other end of the lithium battery pack is simultaneously connected with the current conversion device and the voltage conversion device, and the current conversion device is connected with the voltage conversion device.
2. The power system of claim 1, wherein the voltage conversion device comprises a high-voltage DC-DC power module and a low-voltage DC-DC power module;
in a driving mode, the low-voltage conversion DC-DC power supply module is communicated with the current conversion device through the lithium battery pack, and the high-voltage conversion DC-DC power supply module is not communicated;
in the power generation mode, the current conversion device is simultaneously communicated with the high-voltage DC-DC power supply module and the low-voltage DC-DC power supply module, and the high-voltage power supply module is also simultaneously communicated with the lithium battery pack and the mixed motion control module.
3. The power system of claim 2, wherein the current conversion device is an AC-DC power source.
4. The power system of claim 2, further comprising an on-board device coupled to the transfer low voltage DC-DC power module.
5. The power system of claim 1, wherein the engine and the drive motor are coupled by a power coupling, the power coupling being of a parallel shaft configuration.
6. The power system of claim 1, further comprising a throttle control device for outputting a throttle opening command, the throttle control device being coupled to the hybrid control module.
7. A power system according to claim 3, wherein the drive motor, drive motor controller, AC-DC power supply, high voltage DC-DC power supply module and low voltage DC-DC power supply module are all designed to withstand voltage values greater than 300V.
8. The power system of claim 2, wherein in the power generation mode, the ac power generated by the drive motor is greater than 200V, and the DC voltage boosted by the DC-DC power module is greater than the voltage of the lithium battery pack when full.
9. The power system of claim 1, wherein the lithium battery pack is a ternary system lithium battery, the lowest voltage of the lithium battery pack is greater than 300V, and the engine and the drive motor are driven together to power the aircraft when the lithium battery is sufficiently charged.
10. A parallel hybrid vehicle, characterized in that it is equipped with a propeller and a power system according to one of the preceding claims 1-9, said propeller being connected to both the engine and the drive motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310343676.XA CN116639250A (en) | 2023-03-31 | 2023-03-31 | Parallel type oil-electricity hybrid power system and aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310343676.XA CN116639250A (en) | 2023-03-31 | 2023-03-31 | Parallel type oil-electricity hybrid power system and aircraft |
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| CN116639250A true CN116639250A (en) | 2023-08-25 |
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| CN202310343676.XA Pending CN116639250A (en) | 2023-03-31 | 2023-03-31 | Parallel type oil-electricity hybrid power system and aircraft |
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