CN115009527A - Propeller - Google Patents

Abstract

The invention provides a propeller, and relates to the technical field of aircrafts. The scheme of the invention is as follows: the utility model provides a propeller, which comprises a housing body, the carry interface is installed in the outside of casing body, this internal reaction channel and heat dissipation channel of being provided with of casing, the propulsion subassembly is installed to one side of reaction channel, reaction channel's opposite side intercommunication has the compressor, the compressor is connected with the compressor motor, install a plurality of battery stack groups that are used for advancing the subassembly energy supply in the reaction channel, arbitrary one battery stack group includes a plurality of horizontal monocells that set gradually, all install the fin between arbitrary two adjacent monocells, and in the fin extended to heat dissipation channel, the casing body is provided with the opening of admitting air, the opening of admitting air all communicates with reaction channel and heat dissipation channel. The invention can improve the heat dissipation efficiency and realize better high-altitude flight performance.

Description

Propeller

Technical Field

The invention relates to the technical field of aircrafts, in particular to a propeller.

Background

The flight propeller is an auxiliary power device which enables the aircraft to increase thrust for a short time so as to rapidly increase the flying speed, and power is continuously provided in the flying process. The method is mainly used for shortening the takeoff running distance, and is also used for rapidly increasing the flying speed in flight in some cases. Aircraft propellers for takeoff are also called takeoff accelerators. Rocket engines are generally used as aircraft propellers, are arranged outside a fuselage or a wing, and can be thrown away after working.

At present, the flight propeller can produce more heat in its inside at the flight boosting in-process, if can not in time handle above-mentioned thermal problem and can seriously influence its flight performance at high-altitude, flight propeller structure on the market is more single, and the thermal method of flight in-process processing is generally for through the heat in the outside air with inside, and the relatively poor performance that influences the flight propeller of its radiating effect.

Disclosure of Invention

The invention aims to provide a propeller which can improve the heat dissipation efficiency and realize better high-altitude flight performance.

The embodiment of the invention is realized by the following steps:

the embodiment of the application provides a propeller, which comprises a housing body, the carry interface is installed in the outside of casing body, this internal reaction channel and the heat dissipation channel of being provided with of casing, the propulsion subassembly is installed to one side of reaction channel, reaction channel's opposite side intercommunication has the compressor, the compressor is connected with the compressor motor, install a plurality of battery pile groups that are used for advancing the energy supply of subassembly in the reaction channel, arbitrary one battery pile group includes a plurality of monocells that transversely set gradually, all install the fin between arbitrary two adjacent monocells, and the fin extends to in the heat dissipation channel, the casing body is provided with the opening of admitting air, the opening of admitting air all communicates with reaction channel and heat dissipation channel.

In some embodiments of the present invention, two heat dissipation channels are disposed in the casing body, the reaction channel is located between the two heat dissipation channels, and an air inlet port is disposed between any one of the heat dissipation channels and the reaction channel.

In some embodiments of the invention, the fins comprise graphite fins extending into the heat dissipation channel.

In some embodiments of the present invention, both ends of the graphite heat sink extend into the heat dissipation channel.

In some embodiments of the present invention, the plurality of cell stack assemblies are sequentially arranged in a longitudinal direction.

In some embodiments of the present invention, a heat pipe heat exchanger is installed between any two adjacent cell stack groups, and the heat pipe heat exchanger extends into the heat dissipation channel.

In some embodiments of the present invention, both ends of the heat pipe heat exchanger extend into the heat dissipation channel.

In some embodiments of the present invention, the propulsion assembly includes a propulsion motor and a propeller, the casing body is connected to the propulsion motor, and the propulsion motor is connected to the propeller.

In some embodiments of the invention, the intake port is fitted with an intake air flow rate adjuster.

In some embodiments of the invention, the intake flow rate adjuster includes an intake grill.

Compared with the prior art, the embodiment of the invention has at least the following advantages or beneficial effects:

the utility model provides a propeller, a serial communication port, which comprises a housing body, the carry interface is installed in the outside of casing body, this internal reaction channel and heat dissipation channel of being provided with of casing, the propulsion subassembly is installed to one side of reaction channel, reaction channel's opposite side intercommunication has the compressor, the compressor is connected with the compressor motor, install a plurality of battery stack groups that are used for advancing the energy supply of subassembly in the reaction channel, arbitrary one battery stack group includes a plurality of monocell pieces that transversely set gradually, all install the fin between arbitrary two adjacent monocell pieces, and the fin extends to in the heat dissipation channel, the casing body is provided with the opening of admitting air, the opening of admitting air all communicates with reaction channel and heat dissipation channel.

In the above embodiment, a propeller comprises a casing body, a propulsion assembly, a compressor motor and a battery stack assembly, wherein the propulsion assembly is installed on one side of the casing body, the compressor and the compressor motor are sequentially installed on the other side of the casing body, a reaction channel and a heat dissipation channel (the heat dissipation channel and the reaction channel are sealed with each other) are arranged in the casing body, the reaction channel is communicated with the compressor, the casing body is provided with a hydrogen supply pipeline, a hydrogen supply manifold (supplying hydrogen to the battery stack) is arranged in the reaction channel, the hydrogen supply manifold is communicated with the hydrogen supply pipeline, the casing body is provided with a heat dissipation exhaust port, a reaction exhaust port and a hydrogen exhaust port, the casing body is further connected with an output cable for supplying power to the whole body, a hanging interface is installed on the outer side of the casing body, and the propeller is fixedly connected with the wings through the hanging interface, specifically, the method comprises the following steps that a worker firstly installs a propeller on an aircraft through a mounting interface, a hydrogen supply pipeline and an output cable are both connected with the aircraft, outside air enters a reaction channel through an air inlet port, a gas compressor is driven by a gas compressor motor to rotate and pressurize, the air is pressurized by the gas compressor and then reacts with hydrogen in a battery stack in the reaction channel to generate electricity, and the electricity is generated to power a gas compressor motor to drive the gas compressor and power a propulsion assembly to propel the aircraft to fly; meanwhile, a plurality of cell stack groups for supplying energy to the propulsion assembly are arranged in the reaction channel, any one cell stack group comprises a plurality of single cell sheets which are sequentially and transversely arranged, radiating fins are arranged between any two adjacent single cell sheets and extend into the radiating channel, external air simultaneously enters the reaction channel and the radiating channel, the air entering the reaction channel not only serves as a reactant to generate electricity, but also can radiate the plurality of cell stack groups, radiating fins are arranged between any two adjacent single cell sheets and can also radiate the single cell sheets, so that the whole cell stack group can be cooled, the air entering the radiating channel can be used for cooling the radiating fins (the radiating fins are positioned in the reaction channel, one ends of the radiating fins extend into the radiating channel), and thus, a part of the radiating fins positioned in the reaction channel can be rapidly cooled, the flight performance can be prevented from being influenced by overhigh temperature of the cell stack group through double cooling, finally, the gas in the reaction channel is discharged from the reaction tail gas port, the gas in the heat dissipation channel is discharged from the heat dissipation tail gas port, and the hydrogen in the hydrogen supply pipeline is discharged from the hydrogen tail gas port; furthermore, the heat radiating fins can be graphite heat radiating fins which are a brand new heat conducting and radiating material, have unique crystal grain orientation, conduct heat uniformly along two directions, and can be well adapted to any surface due to a lamellar structure, so that the performance of the consumer electronic product is improved while a heat source and components are shielded. The product can provide heat insulation in the aspect of thickness while radiating uniformly, and the surface of the graphite radiating fin can be combined with other materials such as metal, plastic, adhesive sticker and the like to meet more design functions and requirements; the graphite radiating fin has 40 percent lower thermal resistance than aluminum and 20 percent lower thermal resistance than copper; the weight of the graphite radiating fin is 25% lighter than that of aluminum and 75% lighter than that of copper; the graphite heat sink can be smoothly attached to any plane and curved surface, and can be cut in any form according to the requirements of customers.

In this embodiment, in the reaction channel, part of the reaction heat of the cell stack assembly is conducted to the heat dissipation channel through the heat dissipation fins of the single cell interlayer, and part of the reaction heat is dissipated through the air flowing through the fuel cell stack. The air pressure in the reaction channel meets the requirement of the cell stack group reaction, the air pressure of the heat dissipation channel is the same as the ambient air pressure, and the contradiction between the reaction pressure and the heat dissipation of the aviation fuel cell is solved. The flight performance of the propeller at middle and high altitude is realized.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.

FIG. 1 is a schematic view of a propeller according to an embodiment of the present invention;

FIG. 2 is a perspective view of a propeller according to an embodiment of the present invention;

FIG. 3 is a right side view of the housing body according to the embodiment of the present invention;

FIG. 4 is a sectional view of a housing body according to an embodiment of the present invention;

fig. 5 is a schematic view of a cell stack assembly according to an embodiment of the present invention.

The following are marked in the figure: the method comprises the following steps of 1-a machine shell body, 2-a mounting interface, 3-a propulsion motor, 4-a propeller, 5-an output cable, 6-a hydrogen supply pipeline, 7-an air inlet port, 8-an air inlet grid, 9-a reaction tail gas port, 10-a heat dissipation tail gas port, 11-a hydrogen tail gas port, 12-a gas compressor, 13-a gas compressor motor, 14-a reaction channel, 15-a heat dissipation channel, 16-a battery stack group, 17-a graphite cooling fin and 18-a heat pipe exchanger.

Detailed Description

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 some, but not all, embodiments of the present invention. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. 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.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the embodiments of the present invention, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or the orientations or positional relationships that the products of the present invention are usually placed in when used, the orientations or positional relationships are only used for convenience of describing the present invention and simplifying the description, but the terms do not indicate or imply that the devices or elements indicated must have specific orientations, be constructed in specific orientations, and operate, and therefore, should not be construed as limiting the present invention.

Furthermore, the terms "horizontal", "vertical", "overhang" and the like do not require that the components be absolutely horizontal or overhang, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the embodiments of the present invention, "a plurality" represents at least 2.

In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed," "mounted," "connected," and "connected" should be broadly construed and interpreted as including, for example, fixed connections, detachable connections, or integral connections; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

Examples

Please refer to fig. 1-5. The embodiment provides a propeller, which is characterized in that, including casing body 1, carry interface 2 is installed in casing body 1's the outside, be provided with reaction channel 14 and heat dissipation channel 15 in the casing body 1, the propulsion subassembly is installed to one side of reaction channel 14, reaction channel 14's opposite side intercommunication has compressor 12, compressor 12 is connected with compressor motor 13, install a plurality of banks 16 that are used for the energy supply to propulsion subassembly in the reaction channel 14, arbitrary one bank 16 includes a plurality of horizontal monocells that set up in proper order, all install the fin between arbitrary two adjacent monocells, and the fin extends to in the heat dissipation channel 15, casing body 1 is provided with air inlet opening 7, air inlet opening 7 all communicates with reaction channel 14 and heat dissipation channel 15.

In the above embodiment, a propeller is composed of a casing body 1, a propulsion assembly, a compressor 12, a compressor motor 13 and a cell stack group 16, wherein the propulsion assembly is installed at one side of the casing body 1, the compressor 12 and the compressor motor 13 are sequentially installed at the other side of the casing body 1, a reaction channel 14 and a heat dissipation channel 15 (the heat dissipation channel 15 and the reaction channel 14 are sealed with each other) are arranged in the casing body 1, the reaction channel 14 is communicated with the compressor 12, the casing body 1 is provided with a hydrogen supply pipeline 6, a hydrogen supply manifold (the hydrogen supply manifold supplies gas to the cell stack) is arranged in the reaction channel 14, the hydrogen supply manifold is communicated with the hydrogen supply pipeline 6, the casing body 1 is provided with a heat dissipation tail gas port 10, a reaction tail gas port 9 and a hydrogen tail gas port 11, the casing body 1 is further connected with an output cable for supplying power to the whole body, a hanging interface 2 is installed at the outer side of the casing body 1, the propeller is fixedly connected with the wing through the mounting interface 2, specifically, a worker firstly installs the propeller on an aircraft through the mounting interface 2, the hydrogen supply pipeline 6 and the output cable are both connected with the aircraft, outside air enters the reaction channel 14 through the air inlet port 7, the compressor 12 is driven by the compressor motor 13 to rotate and pressurize, the air is pressurized by the compressor 12 and then reacts with hydrogen in the battery stack group 16 in the reaction channel 14 to generate electricity, and the electricity is generated to supply electricity to the compressor motor 13 to drive the compressor 12 and supply electricity to the propulsion assembly so as to propel the aircraft to fly; meanwhile, a plurality of cell stack groups 16 for supplying energy to the propulsion assembly are arranged in the reaction channel 14, any one cell stack group 16 comprises a plurality of single cells which are sequentially and transversely arranged, a radiating fin is arranged between any two adjacent single cells and extends into the radiating channel 15, external air simultaneously enters the reaction channel 14 and the radiating channel 15, the air entering the reaction channel 14 not only serves as a reactant to generate electricity, but also can radiate the plurality of cell stack groups 16, a radiating fin is arranged between any two adjacent single cells and can also radiate the single cells, so that the whole cell stack group 16 can be cooled, the radiating fin can be cooled in the radiating channel 15 (the radiating fin is arranged in the reaction channel 14, one end of the radiating fin extends into the radiating channel 15), and a part of the radiating fin in the reaction channel 14 can be rapidly cooled, the flight performance can be prevented from being influenced by overhigh temperature of the cell stack group 16 through double temperature reduction, finally, the gas in the reaction channel 14 is discharged from the reaction tail gas port 9, the gas in the heat dissipation channel 15 is discharged from the heat dissipation tail gas port 10, and the hydrogen in the hydrogen supply pipeline 6 is discharged from the hydrogen tail gas port 11; furthermore, the heat sink can be graphite heat sink 17, the graphite heat sink 17 is a brand new heat conducting and dissipating material, has unique crystal grain orientation, conducts heat uniformly along two directions, and the lamellar structure can be well adapted to any surface, thereby shielding heat source and assembly and improving the performance of consumer electronic products. The product can provide heat insulation in the aspect of thickness while radiating uniformly, and the surface of the graphite radiating fin 17 can be combined with other materials such as metal, plastic, adhesive sticker and the like to meet more design functions and requirements; the graphite radiating fins 17 have 40% lower thermal resistance than aluminum and 20% lower thermal resistance than copper; the graphite radiating fins 17 are 25% lighter than aluminum and 75% lighter than copper; the graphite fins 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to the customer's needs.

In this embodiment, part of the reaction heat generated in the stack assembly 16 in the reaction channel 14 is conducted to the heat dissipation channel 15 through the heat dissipation fins of the cell stack, and part of the reaction heat is dissipated by the air flowing through the fuel cell stack. The air pressure in the reaction channel 14 meets the reaction of the cell stack group 16, and the air pressure of the heat dissipation channel 15 is the same as the ambient air pressure, so that the contradiction between the reaction pressure and the heat dissipation of the aviation fuel cell is solved. The flight performance of the propeller at middle and high altitude is realized.

In some embodiments of the present invention, two heat dissipation channels 15 are disposed in the casing body 1, the reaction channel 14 is located between the two heat dissipation channels 15, and the air inlet 7 is disposed between any one of the heat dissipation channels 15 and the reaction channel 14.

In this embodiment, two heat dissipation channels 15 are provided in the casing body 1, and the two heat dissipation channels 15 can dissipate heat in the reaction channel 14, so that the heat dissipation efficiency can be improved.

In some embodiments of the invention, the fins comprise graphite fins 17, the graphite fins 17 extending into the heat dissipation channel 15.

In this embodiment, the graphite heat sink 17 is a completely new heat conducting and dissipating material, has unique grain orientation, conducts heat uniformly in two directions, and has a lamellar structure that can adapt to any surface well, shielding heat sources and components while improving the performance of consumer electronics. The product can provide heat insulation in the aspect of thickness while radiating uniformly, and the surface of the graphite radiating fin 17 can be combined with other materials such as metal, plastic, adhesive sticker and the like to meet more design functions and requirements; the graphite radiating fins 17 have 40% lower thermal resistance than aluminum and 20% lower thermal resistance than copper; the graphite radiating fins 17 are 25% lighter than aluminum and 75% lighter than copper; the graphite fins 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to the customer's needs.

In some embodiments of the invention, both ends of the graphite fins 17 extend into the heat dissipation channel 15.

In this embodiment, graphite fin 17 can dispel the heat to the single battery piece, thereby can cool down whole battery pile group 16, air admission heat dissipation channel 15 is interior can carry out cooling to graphite fin 17 (graphite fin 17 is located reaction channel 14, graphite fin 17's one end extends to in heat dissipation channel 15), thereby can make the partly rapid cooling who is located reaction channel 14 internal cooling fin, graphite fin 17's both ends all extend to in heat dissipation channel 15, not only can make graphite fin 17's upper portion and lower part homoenergetic enough obtain the cooling, and can improve the speed of cooling, can prevent battery pile group 16's the too high influence flight performance of temperature through rapid cooling.

In some embodiments of the present invention, a plurality of cell stack assemblies 16 are arranged sequentially in the longitudinal direction.

In this embodiment, the plurality of cell stack groups 16 are sequentially and longitudinally arranged, so that the space in the reaction channel 14 can be reasonably utilized, and resources are saved.

In some embodiments of the present invention, a heat pipe heat exchanger 18 is installed between any two adjacent cell stack groups 16, and the heat pipe heat exchanger 18 extends into the heat dissipation channel 15.

In this embodiment, the heat pipe heat exchanger 18 is installed between two adjacent cell stack groups 16, the heat pipe heat exchanger 18 can absorb heat of the cell stack groups 16 to keep a good state, the heat pipe heat exchanger 18 extends into the heat dissipation channel 15, air in the heat dissipation channel 15 can dissipate heat of the heat pipe heat exchanger 18, and overall heat dissipation efficiency is improved.

In some embodiments of the present invention, both ends of the heat pipe heat exchanger 18 extend into the heat dissipation channel 15.

In this embodiment, after the air is introduced into the heat dissipation channel 15, both sides of the heat pipe heat exchanger 18 can be dissipated, so that the overall heat dissipation efficiency is improved.

In some embodiments of the present invention, the propulsion assembly comprises a propulsion motor 3 and a propeller 4, the casing body 1 is connected with the propulsion motor 3, and the propulsion motor 3 is connected with the propeller 4.

In this embodiment, the battery stack assembly 16 generates electricity to power the compressor motor 13 to drive the compressor 12, to power the propulsion motor 3, and to drive the propeller 4 to propel the aircraft to fly.

In some embodiments of the invention, the intake port 7 is fitted with an intake flow rate adjuster.

In this embodiment, the intake air flow rate adjusting member can adjust the flow rate of air entering the reaction channel 14 and the heat dissipation channel 15, and control the overall flying efficiency and heat dissipation efficiency.

In some embodiments of the invention, the intake flow rate adjustment comprises an intake grille 8.

In this embodiment, the air inlet grille 8 can adjust the flow rate of the air entering the reaction channel 14 and the heat dissipation channel 15, and control the overall flying efficiency and heat dissipation efficiency.

In summary, an embodiment of the present invention provides a propeller, which is characterized by including a casing body 1, a mounting interface 2 is installed on an outer side of the casing body 1, a reaction channel 14 and a heat dissipation channel 15 are disposed in the casing body 1, a propulsion component is installed on one side of the reaction channel 14, a compressor 12 is communicated with the other side of the reaction channel 14, the compressor 12 is connected to a compressor motor 13, a plurality of cell stack groups 16 for supplying energy to the propulsion component are installed in the reaction channel 14, any one cell stack group 16 includes a plurality of single cells which are sequentially and transversely disposed, a heat dissipation fin is installed between any two adjacent single cells and extends into the heat dissipation channel 15, the casing body 1 is provided with an air inlet port 7, and the air inlet port 7 is communicated with both the reaction channel 14 and the heat dissipation channel 15.

In the above embodiment, a propeller is composed of a casing body 1, a propulsion assembly, a compressor 12, a compressor motor 13 and a cell stack group 16, wherein the propulsion assembly is installed at one side of the casing body 1, the compressor 12 and the compressor motor 13 are sequentially installed at the other side of the casing body 1, a reaction channel 14 and a heat dissipation channel 15 (the heat dissipation channel 15 and the reaction channel 14 are sealed with each other) are arranged in the casing body 1, the reaction channel 14 is communicated with the compressor 12, the casing body 1 is provided with a hydrogen supply pipeline 6, a hydrogen supply manifold (the hydrogen supply manifold supplies gas to the cell stack) is arranged in the reaction channel 14, the hydrogen supply manifold is communicated with the hydrogen supply pipeline 6, the casing body 1 is provided with a heat dissipation tail gas port 10, a reaction tail gas port 9 and a hydrogen tail gas port 11, the casing body 1 is further connected with an output cable for supplying power to the whole body, a hanging interface 2 is installed at the outer side of the casing body 1, the propeller is fixedly connected with the wing through the mounting interface 2, specifically, a worker firstly installs the propeller on an aircraft through the mounting interface 2, the hydrogen supply pipeline 6 and the output cable are both connected with the aircraft, outside air enters the reaction channel 14 through the air inlet port 7, the compressor 12 is driven by the compressor motor 13 to rotate and pressurize, the air is pressurized by the compressor 12 and then reacts with hydrogen in the battery stack group 16 in the reaction channel 14 to generate electricity, and the electricity is generated to supply electricity to the compressor motor 13 to drive the compressor 12 and supply electricity to the propulsion assembly so as to propel the aircraft to fly; meanwhile, a plurality of cell stack groups 16 for supplying energy to the propulsion assembly are arranged in the reaction channel 14, any one cell stack group 16 comprises a plurality of single cells which are sequentially and transversely arranged, a radiating fin is arranged between any two adjacent single cells and extends into the radiating channel 15, external air simultaneously enters the reaction channel 14 and the radiating channel 15, the air entering the reaction channel 14 not only serves as a reactant to generate electricity, but also can radiate the plurality of cell stack groups 16, a radiating fin is arranged between any two adjacent single cells and can also radiate the single cells, so that the whole cell stack group 16 can be cooled, the radiating fin can be cooled in the radiating channel 15 (the radiating fin is arranged in the reaction channel 14, one end of the radiating fin extends into the radiating channel 15), and a part of the radiating fin in the reaction channel 14 can be rapidly cooled, the flight performance can be prevented from being influenced by overhigh temperature of the cell stack group 16 through double temperature reduction, finally, the gas in the reaction channel 14 is discharged from the reaction tail gas port 9, the gas in the heat dissipation channel 15 is discharged from the heat dissipation tail gas port 10, and the hydrogen in the hydrogen supply pipeline 6 is discharged from the hydrogen tail gas port 11; further, the heat sink may be graphite heat sink 17, the graphite heat sink 17 being a brand new heat conducting and dissipating material having unique grain orientation and conducting heat uniformly in two directions, the lamellar structure being well adapted to any surface, shielding heat sources and components while improving the performance of consumer electronics. The product can provide heat insulation in the aspect of thickness while radiating uniformly, and the surface of the graphite radiating fin 17 can be combined with other materials such as metal, plastic, adhesive sticker and the like to meet more design functions and requirements; the graphite radiating fins 17 have 40% lower thermal resistance than aluminum and 20% lower thermal resistance than copper; the graphite radiating fins 17 are 25% lighter than aluminum and 75% lighter than copper; the graphite fins 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to the customer's needs.

In this embodiment, in reaction channel 14, part of the reaction heat generated in stack 16 is conducted to heat dissipation channel 15 through the heat sink fins of the cell stack sandwich, and part of the reaction heat is dissipated through the air flowing through the fuel cell stack. The air pressure in the reaction channel 14 meets the reaction of the cell stack group 16, and the air pressure of the heat dissipation channel 15 is the same as the ambient air pressure, so that the contradiction between the reaction pressure and the heat dissipation of the aviation fuel cell is solved. The flight performance of the propeller at middle and high altitude is realized.

The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims (10)

1. The utility model provides a propeller, a serial communication port, includes casing body, the carry interface is installed in casing body's the outside, this internal reaction channel and heat dissipation channel that is provided with of casing, the propulsion subassembly is installed to one side of reaction channel, reaction channel's opposite side intercommunication has the compressor, the compressor is connected with the compressor motor, it is right to install in the reaction channel a plurality of batteries that propulsion subassembly supplied energy pile the group, arbitrary one battery pile the group includes a plurality of horizontal monocells that set gradually, arbitrary adjacent two all install the fin between the monocell, just the fin extends to in the heat dissipation channel, casing body is provided with the opening of admitting air, the opening of admitting air with reaction channel with heat dissipation channel all communicates.

2. The propeller as claimed in claim 1, wherein two heat dissipation channels are provided in the casing body, the reaction channel is located between the two heat dissipation channels, and an air inlet port is provided between any one of the heat dissipation channels and the reaction channel.

3. A propeller as claimed in claim 2, wherein the fins comprise graphite fins which extend into the heat dissipation channel.

4. A propeller as claimed in claim 3, wherein both ends of the graphite fins extend into the heat dissipation channel.

5. A pusher according to claim 2, characterised in that a plurality of said cell stack assemblies are arranged longitudinally one after the other.

6. A propeller according to claim 5, wherein a heat pipe exchanger is mounted between any two adjacent cell stack groups, and the heat pipe exchanger extends into the heat dissipation channel.

7. A propeller as claimed in claim 6, wherein both ends of the heat pipe heat exchanger extend into the heat dissipation channel.

8. The propeller of claim 1, wherein the propulsion assembly comprises a propulsion motor and a propeller, the housing body is connected to the propulsion motor, and the propulsion motor is connected to the propeller.

9. A propeller as claimed in claim 1, wherein the inlet port is fitted with an inlet flow rate adjuster.

10. A propeller as claimed in claim 9, wherein the inlet flow rate adjustment member comprises an inlet grille.

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