CN218877575U

CN218877575U - Power supply system for aircraft and aircraft

Info

Publication number: CN218877575U
Application number: CN202223540623.7U
Authority: CN
Inventors: 王丹博; 蔡普迪; 杨锋; 李勇亨; 王彦波
Original assignee: Shandong Guochuang Fuel Cell Technology Innovation Center Co ltd
Current assignee: Shandong Guochuang Fuel Cell Technology Innovation Center Co ltd
Priority date: 2022-12-29
Filing date: 2022-12-29
Publication date: 2023-04-18
Anticipated expiration: 2032-12-29

Abstract

The utility model belongs to the technical field of the aircraft, a power supply system and aircraft for aircraft is disclosed, this power supply system for aircraft, fuel cell pile and fuel cell auxiliary assembly all set up in the front deck of aircraft, first DC/DC converter sets up in the front deck, first DC/DC converter is connected with fuel cell pile electricity, first DC/DC converter passes through first circuit electricity with driving motor controller and is connected, machine controller is connected with the motor electricity, fuel cell auxiliary assembly is connected with first circuit electricity, the power battery power is connected with first circuit electricity, the battery passes through second circuit electricity with fuel cell auxiliary assembly and is connected, power battery power and battery all set up in the rear deck of aircraft, second DC/DC converter sets up in the front deck, second DC/DC converter one end is connected with first circuit electricity, the other end is connected with the second circuit electricity. The long endurance mileage can be realized, and the mass distribution of each part is uniform, thereby being beneficial to the flight of the airplane.

Description

Power supply system for aircraft and aircraft

Technical Field

The utility model relates to an aircraft technical field especially relates to power supply system and aircraft for aircraft.

Background

The general aviation aircraft is used for carrying out flight activities in aspects of rescue and relief work, flight training, scientific monitoring and the like. Most of the present airplanes use traditional fuel to provide power, and the tail gas discharged by airplanes using gasoline or diesel oil as the driving energy of the airplanes can cause serious pollution to air, and the energy conversion efficiency of the traditional gasoline/diesel oil engine is about 30 percent, namely the traditional energy conversion efficiency is low. Fuel cells are electrochemical devices that convert the chemical energy of a fuel and an oxidant directly into electrical energy (direct current), heat, and reaction products. Clean energy such as hydrogen energy gradually enters the global vision due to the advantages of huge reserves, high efficiency, no pollution, no emission and the like, so that pure electric aircrafts driven by pollution-free green energy such as hydrogen fuel cells are in operation. The pure electric aircraft has low noise and zero emission, and is very suitable for low-altitude flight, however, the pure electric aircraft in the prior art is restricted by energy density, long endurance mileage is difficult to realize, and the mass distribution uniformity of each part needs to be improved.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a power supply system and aircraft for aircraft to solve the restriction that pure electric aircraft among the prior art received energy density, difficult problem in order to realize long continuation of the journey mileage.

To achieve the purpose, the utility model adopts the following technical proposal:

a power supply system for an aircraft, comprising:

the fuel cell stack and the fuel cell auxiliary equipment are arranged in a front cabin of the airplane;

the first DC/DC converter is arranged in the front cabin and is electrically connected with the fuel cell stack, the first DC/DC converter is electrically connected with the motor controller through a first circuit, the motor controller is electrically connected with the driving motor, and the fuel cell auxiliary equipment is electrically connected with the first circuit;

the power battery power supply is electrically connected with the first circuit, and the storage battery is electrically connected with the fuel cell auxiliary equipment through a second circuit; the power battery power supply and the storage battery are both arranged in a rear cabin of the airplane;

and the second DC/DC converter is arranged in the front cabin, one end of the second DC/DC converter is electrically connected with the first circuit, and the other end of the second DC/DC converter is electrically connected with the second circuit.

As a preferable scheme of the above power supply system for an aircraft, the fuel cell system for an aircraft further includes two hydrogen storage structures, the two hydrogen storage structures are respectively disposed below the two wings, and the hydrogen storage structures are configured to supply hydrogen to the fuel cell stack.

As a preferable scheme of the above power supply system for aircraft, a nacelle is fixedly arranged below the wing, and the hydrogen storage structure is located in the nacelle.

As a preferable mode of the above power supply system for an aircraft, the front cabin is provided with a bracket, and the fuel cell stack, the fuel cell auxiliary device, the first DC/DC converter, and the second DC/DC converter are all fixedly provided to the bracket.

As a preferable aspect of the above power supply system for an aircraft, the power supply system for an aircraft further includes a first radiator, the first radiator is configured to radiate heat from the fuel cell auxiliary device, and the first radiator is disposed in the front cabin.

As a preferable scheme of the above power supply system for an aircraft, the power supply system for an aircraft further includes a second radiator, the second radiator is configured to radiate heat of the driving motor, and the second radiator is disposed in the front cabin.

As a preferable scheme of the above power supply system for an aircraft, a ventilation opening is provided in front of the front cabin, and the first radiator and the second radiator both correspond to the ventilation opening.

As a preferable scheme of the above power supply system for an aircraft, the power supply system for an aircraft further includes a third radiator, the third radiator is configured to radiate heat from the fuel cell stack, and the third radiator is disposed in the rear compartment and located above the power battery power supply and the storage battery.

As a preferable mode of the above power supply system for an aircraft, the third radiator is provided with a plurality of fans, and the plurality of fans are provided at intervals.

An aircraft comprising the above-described power supply system for an aircraft.

The utility model has the advantages that:

the utility model provides a power supply system and aircraft for aircraft, this power supply system for aircraft, before fuel cell pile does not start, pass through the second circuit by the battery and provide direct current low-voltage electricity to fuel cell auxiliary assembly, the power battery power is connected with first circuit electricity through the third circuit, fuel cell auxiliary assembly passes through the fourth circuit and is connected with first circuit electricity, the power battery power passes through the third circuit, first circuit and fourth circuit provide direct current high-voltage electricity for fuel cell auxiliary assembly, the power battery power can also be supplied power for machine controller through third circuit and first circuit, machine controller control driving motor work, driving motor drives the aircraft screw and rotates. After the fuel cell stack is started, the fuel cell stack generates lower direct-current high-voltage electricity, the first DC/DC converter can boost the lower direct-current high-voltage electricity into higher direct-current high-voltage electricity, the higher direct-current high-voltage electricity boosted by the first DC/DC converter can be supplied to a motor controller and can also supply power to auxiliary equipment of the fuel cell, meanwhile, the higher direct-current high-voltage electricity boosted by the first DC/DC converter can charge a power cell power supply through a first circuit and a third circuit, a storage battery can be charged after the direct-current high-voltage electricity is reduced into the direct-current low-voltage electricity by the second DC/DC converter, and the power cell power supply can also supply power to the motor controller. Thus, the battery and power cell power supply can provide power to the fuel cell auxiliary equipment when the fuel cell stack is not yet started, and the power cell power supply can also provide power to the motor controller. After the fuel cell stack is started, the motor controller and the fuel cell auxiliary equipment can be supplied with power, and a power battery power supply and a storage battery can be charged. The power supply system for the airplane can realize long endurance mileage, the fuel cell stack, the fuel cell auxiliary equipment, the first DC/DC converter and the second DC/DC converter are arranged in the front cabin, the power cell power supply and the storage battery are arranged in the rear cabin, the mass distribution of all parts is uniform, the center of mass of the airplane is located at the center of the airplane, and the airplane can fly more favorably.

Drawings

Fig. 1 is a schematic structural diagram of an aircraft power supply system according to an embodiment of the present invention;

fig. 2 is a schematic partial structural diagram of a power supply system for an aircraft according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a part of an aircraft power supply system according to an embodiment of the present invention;

fig. 4 is a schematic structural diagram of a part of a power supply system for an aircraft according to an embodiment of the present invention.

In the figure:

1. a fuel cell stack; 2. a first DC/DC converter; 3. a motor controller; 4. a drive motor; 5. a fuel cell auxiliary device; 6. a power cell power source; 7. a storage battery; 8. a second DC/DC converter; 9. a first circuit; 10. a second circuit; 11. an aircraft complete machine controller; 12. a fuel cell controller; 13. a fourth circuit; 14. a third circuit; 15. a hydrogen storage structure; 16. a dome; 17. a vent; 18. a first heat sink; 19. a second heat sink; 20. a third heat sink; 21. a fan; 22. an air inlet.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, detachably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "right", and the like are used in the orientation or positional relationship shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to be limiting.

The utility model provides a power supply system for aircraft, as shown in fig. 1, this power supply system for aircraft includes fuel cell galvanic pile 1, fuel cell auxiliary assembly 5, first DC/DC converter 2, power battery power 6, battery 7 and second DC/DC converter 8, fuel cell galvanic pile 1 and fuel cell auxiliary assembly 5 all set up in the front deck of aircraft, first DC/DC converter 2 sets up in the front deck, first DC/DC converter 2 is connected with fuel cell galvanic pile 1 electricity, first DC/DC converter 2 is connected through first circuit 9 electricity with motor controller 3, motor controller 3 is connected with driving motor 4 electricity, fuel cell auxiliary assembly 5 is connected with first circuit 9 electricity, power battery power 6 is connected with first circuit 9 electricity, battery 7 is connected through second circuit 10 electricity with fuel cell auxiliary assembly 5, power battery power 6 and battery 7 all set up in the rear deck of aircraft, second DC/DC converter 8 sets up in the front deck, second DC/DC converter 8 one end is connected with first circuit 9 electricity, the other end is connected with second circuit 10 electricity.

Before the fuel cell stack 1 is not started, the storage battery 7 provides direct current low voltage electricity for the fuel cell auxiliary equipment 5 through the second circuit 10, the power cell power supply 6 is electrically connected with the first circuit 9 through the third circuit 14, the fuel cell auxiliary equipment 5 is electrically connected with the first circuit 9 through the fourth circuit 13, the power cell power supply 6 provides direct current high voltage electricity for the fuel cell auxiliary equipment 5 through the third circuit 14, the first circuit 9 and the fourth circuit 13, the power cell power supply 6 can also provide power for the motor controller 3 through the third circuit 14 and the first circuit 9, the motor controller 3 controls the driving motor 4 to work, and the driving motor 4 drives the airplane propeller to rotate. After the fuel cell stack 1 is started, the fuel cell stack 1 generates lower direct-current high-voltage electricity, the first DC/DC converter 2 can boost the lower direct-current high-voltage electricity into higher direct-current high-voltage electricity, the higher direct-current high-voltage electricity boosted by the first DC/DC converter 2 can be supplied to the motor controller 3 and can also supply power to the fuel cell auxiliary equipment 5, meanwhile, the higher direct-current high-voltage electricity boosted by the first DC/DC converter 2 can charge the power cell power supply 6 through the first circuit 9 and the third circuit 14, the power cell power supply 6 can also charge the storage battery 7 after being reduced into the direct-current low-voltage electricity through the second DC/DC converter 8, and the power cell power supply 6 can also supply power to the motor controller 3. So that the battery 7 and the power cell power supply 6 can supply power to the fuel cell auxiliary equipment 5 and the power cell power supply 6 can also supply power to the motor controller 3 when the fuel cell stack 1 is not yet started. After the fuel cell stack 1 is started, the fuel cell stack 1 can supply power to the motor controller 3 and the fuel cell auxiliary equipment 5, and can also charge the power cell power supply 6 and the storage battery 7. The power supply system for the airplane can realize long endurance mileage, the fuel cell stack 1, the fuel cell auxiliary equipment 5, the first DC/DC converter 2 and the second DC/DC converter 8 are arranged in the front cabin, the power cell power supply 6 and the storage battery 7 are arranged in the rear cabin, the mass distribution of all parts is uniform, the center of mass of the airplane is located at the center of the airplane, and the flight of the airplane is facilitated.

The fuel cell auxiliary equipment 5 includes, among other things, a hydrogen gas supply system, an air supply system, and a water thermal management system. The hydrogen supply system is used for supplying hydrogen to the fuel cell stack 1, the air supply system is used for supplying air to the fuel cell stack 1, and the water heat management system is used for controlling the temperature of the fuel cell stack 1.

Optionally, the power supply system for the aircraft further comprises a fuel cell controller 12, the first DC/DC converter 2 and the second DC/DC converter 8 are all electrically connected with the aircraft complete machine controller 11, and the power battery power supply 6 and the storage battery 7 are all electrically connected with the second DC/DC converter 8.

Optionally, as shown in fig. 2, the power supply system for an aircraft further includes two hydrogen storage structures 15, where the two hydrogen storage structures 15 are respectively disposed below the two wings, and the hydrogen storage structures 15 are used for supplying hydrogen to the fuel cell stack 1. The hydrogen supply of the fuel cell system is ensured.

Optionally, a wind deflector 16 is fixedly arranged below the wing, and the hydrogen storage structure 15 is positioned in the wind deflector 16. The pod 16 may reduce drag of the air when the aircraft is in flight.

Optionally, the front cabin is provided with a bracket, and the fuel cell stack 1, the fuel cell auxiliary device 5, the first DC/DC converter 2 and the second DC/DC converter 8 are all fixedly arranged on the bracket. The space of the front cabin is limited and irregular, the support extends out on the basis of the airplane frame, the integration degree is high, and the space of the front cabin can be fully utilized.

Optionally, as shown in fig. 3 and 4, the power supply system for an aircraft further includes a first radiator 18, the first radiator 18 being used for radiating heat of the fuel cell auxiliary equipment 5, the first radiator 18 being provided in the front compartment. The first heat sink 18 can sufficiently dissipate heat from the fuel cell auxiliary equipment 5 by dissipating heat from the air flow during flight of the aircraft.

Optionally, the power supply system for aircraft further includes a second radiator 19, the second radiator 19 is used for radiating heat of the driving motor 4, and the second radiator 19 is disposed in the front cabin. The second heat sink 19 also dissipates heat through the airflow generated by the flight of the aircraft, and can sufficiently dissipate heat from the drive motor 4.

Optionally, a ventilation opening 17 is provided in front of the front compartment, and the first radiator 18 and the second radiator 19 both correspond to the ventilation opening 17. Enabling sufficient airflow to flush the first 18 and second 19 radiators. The first radiator 18 and the second radiator 19 do not need the fan 21 to radiate heat, and power loss can be reduced.

Optionally, as shown in fig. 3, the power supply system for aircraft further includes a third radiator 20, where the third radiator 20 is used for radiating heat to the fuel cell stack 1, and the third radiator 20 is disposed in the rear compartment above the power cell power supply 6 and the battery 7. The cooling water for cooling the fuel cell stack 1 flows to the third radiator 20 through the pipe, and is radiated by the third radiator 20 and is radiated in a long pipe and then is left around the fuel cell stack 1.

Alternatively, the third heat sink 20 is provided with a plurality of fans 21, and the plurality of fans 21 are arranged at intervals. The cooling water in the third radiator 20 is radiated by the fan 21.

Alternatively, as shown in fig. 4, the air inlet 22 of the air supply system of the fuel cell auxiliary equipment 5 is provided on the side of the front compartment. The air inlet 22 is formed at the side to prevent excessive air from entering the air supply system.

The utility model also provides an aircraft, this aircraft include foretell for the aircraft power supply system.

It is to be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. Numerous obvious variations, rearrangements and substitutions will now occur to those skilled in the art without departing from the scope of the invention. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A power supply system for an aircraft, comprising:

the fuel cell stack (1) and the fuel cell auxiliary equipment (5) are arranged in a front cabin of the airplane;

a first DC/DC converter (2), wherein the first DC/DC converter (2) is arranged in the front cabin, the first DC/DC converter (2) is electrically connected with the fuel cell stack (1), the first DC/DC converter (2) is electrically connected with a motor controller (3) through a first circuit (9), the motor controller (3) is electrically connected with a driving motor (4), and the fuel cell auxiliary equipment (5) is electrically connected with the first circuit (9);

a power cell power supply (6) and a storage battery (7), wherein the power cell power supply (6) is electrically connected with the first circuit (9), and the storage battery (7) is electrically connected with the fuel cell auxiliary equipment (5) through a second circuit (10); the power battery power supply (6) and the storage battery (7) are both arranged in the rear cabin of the airplane;

a second DC/DC converter (8), the second DC/DC converter (8) being disposed in the front compartment, the second DC/DC converter (8) being electrically connected to the first circuit (9) at one end and to the second circuit (10) at the other end.

2. The power supply system for aircraft according to claim 1, wherein the fuel cell system for aircraft further comprises two hydrogen storage structures (15), the two hydrogen storage structures (15) being respectively disposed below two wings, the hydrogen storage structures (15) being configured to supply hydrogen to the fuel cell stack (1).

3. A power supply system for aircraft according to claim 2, characterized in that a fairing (16) is fixedly arranged below the wing, and the hydrogen storage structure (15) is located in the fairing (16).

4. A power supply system for aircraft according to claim 1, characterized in that the front cabin is provided with a support, to which the fuel cell stack (1), the fuel cell auxiliary equipment (5), the first DC/DC converter (2) and the second DC/DC converter (8) are all fixedly arranged.

5. The power supply system for aircraft according to claim 1, further comprising a first radiator (18), the first radiator (18) being for radiating heat from the fuel cell auxiliary equipment (5), the first radiator (18) being provided to the front cabin.

6. The power supply system for aircraft as claimed in claim 5, characterized in that the power supply system for aircraft further comprises a second heat sink (19), the second heat sink (19) being used for dissipating heat from the drive motor (4), the second heat sink (19) being provided at the front cabin.

7. The power supply system for aircraft according to claim 6, characterized in that a ventilation opening (17) is provided in front of the front cabin, said first radiator (18) and said second radiator (19) each corresponding to said ventilation opening (17).

8. The power supply system for aircraft according to claim 1, further comprising a third radiator (20), the third radiator (20) being for radiating heat from the fuel cell stack (1), the third radiator (20) being provided in the rear compartment above the power cell power source (6) and the storage battery (7).

9. The power supply system for aircraft as claimed in claim 8, characterized in that the third radiator (20) is provided with a plurality of fans (21), and the plurality of fans (21) are arranged at intervals.

10. Aircraft, characterized in that it comprises a power supply system for aircraft according to any one of claims 1 to 9.