CN214112886U

CN214112886U - Electric propulsion electric system suitable for new energy airplane

Info

Publication number: CN214112886U
Application number: CN202023179945.4U
Authority: CN
Inventors: 樊馨月; 宋晓明; 康桂文; 孙金博; 王超越; 周喜东
Original assignee: LIAONING GENERAL AVIATION ACADEMY
Current assignee: LIAONING GENERAL AVIATION ACADEMY
Priority date: 2020-12-25
Filing date: 2020-12-25
Publication date: 2021-09-03
Anticipated expiration: 2030-12-25

Abstract

The utility model provides an electric propulsion electric system suitable for new forms of energy aircraft, include: the system comprises a motor, a motor controller, a lithium battery pack, a fuel cell system, a soft start device, a voltage reduction DCDC, a low-voltage power distribution device, a low-voltage emergency battery, an energy management unit and a comprehensive display instrument. In the high-voltage system part, a lithium battery is connected with a fuel cell system in parallel through a soft starting device to provide electric energy for the whole airplane, and a motor controller drives a motor to rotate to provide power for the airplane; and the low-voltage system part is connected with the low-voltage emergency battery in parallel by a step-down DCDC and supplies power for the low-voltage load of the whole machine through a low-voltage power distribution device. The utility model discloses zero carbon emission, environmental protection performance is good, uses through electric energy and two kinds of energy of hydrogen energy combine, on guaranteeing that the aircraft takes off the basis of climbing performance, has increased the voyage of aircraft and time of flight, makes the practicality of aircraft promote by a wide margin to it is various to carry the machine to carry the energy form, has also strengthened the reliability and the security of aircraft.

Description

Electric propulsion electric system suitable for new energy airplane

Technical Field

The invention relates to an electric propulsion system, in particular to an electric propulsion system suitable for a new energy airplane.

Background

With the increasing attention of people to the environmental problems and the stricter control of pollutants such as exhaust emission and the like in the aviation field, the next aviation must belong to new energy electric airplanes for one hundred years, and the electric airplanes and the aircrafts in various forms gradually replace and eliminate the traditional fuel oil type. The electric propulsion system is used as a core system of the electric airplane and plays a vital role in the development of the electric airplane. With the increasing variety of electric aircraft and the increasing performance of electric aircraft, new challenges are presented to electric propulsion systems.

At present, the new energy aviation field develops and forms two trends, namely a lithium battery and a fuel battery. In the prior art, the energy density of the lithium battery is still relatively low, which is a serious restriction on the improvement of the endurance mileage of the airplane. The energy of the fuel cell depends on the carried fuel, but the fuel cell has the problems of slow start, low power density and insufficient dynamic property.

Disclosure of Invention

According to the technical problems of energy density of a lithium battery, slow starting of a fuel battery and low power density in the electric propulsion system, the electric propulsion system suitable for the new energy airplane is provided. The utility model discloses regard as the energy jointly with lithium cell and fuel cell, not only be favorable to the further promotion of aircraft continuation of the journey mileage to adopt multiple machine to carry the energy form, also increased the reliability and the security of aircraft.

The utility model discloses a technical means as follows:

the utility model provides an electric propulsion electric system suitable for new forms of energy aircraft, include: the system comprises a motor, a motor controller, a lithium battery pack, a fuel cell system, a soft start device, a voltage reduction DCDC, a low-voltage power distribution device, a low-voltage emergency battery, an energy management unit and a comprehensive display instrument;

the lithium battery is electrically connected with the fuel battery system in parallel through the soft start device, the motor is driven to rotate through the motor controller, power is provided for the airplane, and the lithium battery pack comprises a battery management system for monitoring the working state;

the fuel cell system comprises a fuel cell stack, an air compressor, a water pump and a boosted DCDC, wherein the fuel cell stack, the air compressor and the water pump are all connected with the boosted DCDC, and the fuel cell stack comprises a fuel cell controller for monitoring the state of the fuel cell and controlling the fuel cell in real time;

the voltage-reducing DCDC is connected with a low-voltage emergency battery in parallel and supplies power to the energy management unit and the comprehensive display instrument through the low-voltage power distribution device;

the battery management system, the fuel battery controller, the motor controller, the boosting DCDC, the energy management unit and the comprehensive display instrument are all connected through a bus.

Further, the boost DCDC comprises a power conversion module, a contactor, a high-voltage bus bar and a fuse;

the lithium battery pack is connected with the high-voltage bus bar through the soft starting device;

the fuel cell stack is connected with the power supply conversion module through the contactor;

the power supply conversion module is connected with the high-voltage bus bar so as to realize parallel connection with the lithium battery pack;

the high-voltage bus bar provides high voltage electricity for the air compressor, the water pump, the voltage reduction DCDC and the motor controller through the fuse, and realizes overcurrent and short-circuit protection of a circuit.

Further, the soft start device comprises a fuse, a soft start relay, a soft start resistor and a main contactor;

the input end of the fuse is connected with the lithium battery pack, and the output end of the fuse is respectively connected with the soft start relay and the main contact input end of the main contactor;

the output end of the main contact of the soft start relay is connected with the soft start resistor in series and then is connected with the output end of the main contact of the main contactor in parallel, and the output end of the main contact of the soft start relay is connected to the boosting DCDC;

the soft start relay and the positive end of the main contactor coil are connected with a low-voltage power distribution device;

the negative end of the output of the soft start relay is connected with the lithium battery pack switch-on switch, and when the switch is closed, the soft start relay is attracted, so that the soft start function is realized, and the peak is prevented from being generated at the moment of power-on;

the negative terminal of the main contactor is connected with the boosting DCDC, when the voltage of a high-voltage bus bar in the boosting DCDC reaches a set value, the boosting DCDC sends a signal to switch on the main contactor, and the soft start circuit is bypassed.

Furthermore, the low-voltage distribution device comprises a step-down DCDC switch-on contactor, an emergency battery switch-on contactor, a low-voltage bus bar and a circuit breaker;

the positive end of the coil of the emergency battery switch-on contactor is connected with the low-voltage emergency battery, the negative end of the coil of the emergency battery switch-on contactor is connected with the ground through a main switch, when the emergency battery switch is switched on, the emergency battery switch-on contactor is actuated by a main contact, and the low-voltage emergency battery is connected with the low-voltage bus bar;

the positive end of the coil of the step-down DCDC switch-on contactor is connected with the low-voltage bus bar, the negative end of the coil of the step-down DCDC switch-on contactor is connected with the ground through a step-down DCDC switch and a main switch, and when the switches and the main switch are closed, the step-down DCDC is connected with the low-voltage bus bar;

the voltage reduction DCDC and the low-voltage emergency battery are connected in parallel to supply power for the low-voltage bus bar;

the low-voltage bus bar is connected with the energy management unit and the comprehensive display instrument through the circuit breaker and provides low-voltage electricity for the low-voltage bus bar.

Furthermore, the battery management system, the fuel battery controller, the motor controller, the energy management unit and the comprehensive display instrument are all connected through a bus;

the comprehensive display instrument receives and displays each state information through the bus.

Compared with the prior art, the utility model has the advantages of it is following:

1. the utility model discloses a lithium cell and fuel cell have compromise electric propulsion system high power density and high energy density's demand simultaneously as the energy jointly, under the condition of guaranteeing new forms of energy aircraft performance, are favorable to the increase of aircraft voyage and time of flight.

2. The utility model discloses a lithium cell and the different energy form of fuel cell have increased the redundancy for aircraft energy system, when an energy system breaks down, can not lead to the aircraft energy to lose completely, have increased the reliability and the security of aircraft.

For the above reasons, the present invention can be widely applied to the field of electric propulsion systems.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

FIG. 1 is an electrical diagram of an electric propulsion system suitable for a new energy aircraft in an embodiment.

Fig. 2 is an internal electrical diagram of the soft start device suitable for the new energy aircraft in the embodiment.

Fig. 3 is an internal electrical diagram of a boosted DCDC suitable for use in a new energy aircraft in an embodiment.

Fig. 4 is an electrical diagram of the interior of a low-voltage power distribution device suitable for a new energy aircraft in the embodiment.

In the figure: 1. a lithium battery pack; 2. a battery management system; 3. a fuel cell system; 4. an air compressor; 5. boosting the DCDC; 6. a water pump; 7. a fuel cell stack; 8. a fuel cell controller; 9. a soft start device; 10. a motor controller; 11. a motor; 12. a low voltage power distribution device; 13. reducing the voltage of DCDC; 14. a low-voltage emergency battery; 15. an energy management unit; 16. a comprehensive display instrument; 17. a first fuse; 18. soft starting the relay; 19. a main contactor; 20. a soft start resistor; 21. the lithium battery pack is connected with the switch; 22. a contactor; 23. a power conversion module; 24. a high voltage bus bar; 25. a second fuse; 26. a third fuse; 27. a fourth fuse; 28. a fifth fuse; 29. the emergency battery is connected with the contactor; 30. a low voltage bus bar; 31. a first circuit breaker; 32. a second circuit breaker; 33. a master switch; 34. a step-down DCDC switch.

Detailed Description

It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

The utility model provides an electric propulsion electric system suitable for new forms of energy aircraft comprises lithium cell group 1, fuel cell system 3, machine controller 10, motor 11, soft starting drive 9, step-down DCDC13, low pressure emergency battery 14, low pressure distribution device 12, energy management unit 15, comprehensive display instrument 16 etc. as shown in FIG. 1.

The lithium battery pack 1 includes a Battery Management System (BMS)2 for performing operation state monitoring. The high-voltage direct current output by the lithium battery pack 1 is connected with the soft start device 9. The internal electrical connections of the soft start device 9 are shown in fig. 2, and the fuse 17 therein is used for protecting the lines from overcurrent and short circuit. When the lithium battery pack switch-on switch 21 is turned on, the soft start relay 18 is switched on, the lithium battery pack 1 supplies power to the high-voltage bus bar 24 in the boost DCDC5 through a soft start circuit formed by the soft start relay 18 and the soft start resistor 20, and the situation that a peak is generated on a circuit at the moment when the lithium battery pack 1 is switched on is avoided; when the voltage on the high-voltage bus bar 24 is larger than 300V, which represents that the soft start is completed, the boosting DCDC5 outputs a signal to enable the main contactor 19 to be connected, the lithium battery pack 1 is directly connected through the high-voltage bus bar 24 of the main contactor 19, and the soft start circuit is bypassed.

The fuel cell system 3 comprises a fuel cell stack 7, an air compressor 4, a water pump 6, a boosting DCDC5 and the like, wherein the fuel cell stack 7 comprises a fuel cell controller (FCU)8 for monitoring the state of the fuel cell and controlling the fuel cell in real time, and the boosting DCDC5 integrates a high-voltage power distribution function besides realizing a power supply conversion function. As shown in fig. 3, the fuel cell stack 7 is connected to the power conversion module 23 through the contactor 22 in the step-up DCDC5, the output current of the fuel cell stack is large, the connection wire is thick, and the fuel cell stack 7 uses a bus bar as a high-voltage connector between the step-up DCDC 5. The power conversion module 23 is connected with the high-voltage bus bar 24 after being subjected to boost conversion, so that power supply in parallel with the lithium battery pack 1 is realized. The high-voltage bus bar 24 provides high voltage electricity for the air compressor 4, the water pump 6, the voltage reduction DCDC13 and the motor controller 10 through the fuses 25-28, and realizes overcurrent and short-circuit protection of a circuit.

The step-down DCDC13 is connected to the step-up DCDC5, converts the high-voltage dc power into low-voltage dc power, and then connects the low-voltage dc power to the low-voltage power distribution device 12. Included within the low voltage power distribution device 12 are a step-down DCDC make contactor 28, an emergency battery make contactor 29, a low voltage bus bar 30, and

circuit breakers

31, 32. When the main switch 33 on the airplane is switched on, the emergency battery is switched on by the contactor 29 for attraction, and the low-voltage emergency battery 14 is connected to the low-voltage bus bar 30; when the step-down DCDC switch 34 is switched on, the step-down DCDC switch-on contactor 28 is closed, and the step-down DCDC13 is connected to the low-voltage bus bar 30, so that parallel power supply with the low-voltage emergency battery 14 is realized. The low-voltage emergency battery 14 provides low-voltage electricity for the energy management unit 15 and the comprehensive display instrument 16, and realizes overcurrent and short-circuit protection of the line.

The battery management system 2, the fuel cell controller 8, the motor controller 10, the boost DCDC5, the energy management unit 15, and the integrated display instrument 16 are all connected by a bus. The battery management system 2, the fuel cell controller 8, the motor controller 10 and the boosting DCDC5 transmit the working state information of the lithium battery pack, the fuel cell stack, the boosting DCDC, the motor controller and the motor through a bus; the energy management unit 15 sends command commands to control the working states of the fuel cell stack 7 and the boosting DCDC5 in real time through the bus; the integrated display instrument 16 receives and displays the status information via the bus.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. An electrically propelled electrical system suitable for use with a new energy aircraft, comprising: the system comprises a motor, a motor controller, a lithium battery pack, a fuel cell system, a soft start device, a voltage reduction DCDC, a low-voltage power distribution device, a low-voltage emergency battery, an energy management unit and a comprehensive display instrument;

2. An electric propulsion system for a new energy aircraft according to claim 1, wherein the step-up DCDC comprises a power conversion module, contactors, high voltage bus bars and fuses;

3. An electric propulsion system for a new energy aircraft according to claim 1, wherein the soft start device comprises a fuse, a soft start relay, a soft start resistor and a main contactor;

4. An electric propulsion system for a new energy aircraft according to claim 1, characterized in that said low voltage distribution means comprises a step-down DCDC make contactor, an emergency battery make contactor, a low voltage bus bar and a circuit breaker;

the positive end of the coil of the step-down DCDC switch-on contactor is connected with the low-voltage bus bar, the negative end of the coil of the step-down DCDC switch-on contactor is connected with the ground through a step-down DCDC switch and a main switch, and when the step-down DCDC switch and the main switch are both closed, the step-down DCDC is connected with the low-voltage bus bar;

5. An electric propulsion system for a new energy aircraft according to claim 1, wherein the battery management system, the fuel cell controller, the motor controller, the energy management unit and the comprehensive display instrument are connected by a bus;