A propeller
By designing reaction and heat dissipation channels in the flight thruster and using graphite heat sinks and heat pipe heat exchangers for dual cooling, the problem of untimely heat handling was solved, efficient heat dissipation was achieved, and the stability of flight performance at medium and high altitudes was ensured.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- CHONGQING RES INST OF HARBIN UNIV OF TECH
- Filing Date
- 2022-07-07
- Publication Date
- 2026-07-21
AI Technical Summary
Existing flight thrusters fail to handle the heat generated during flight boost in a timely manner, affecting mid-to-high altitude flight performance. Furthermore, their simple structure results in poor heat dissipation.
The design incorporates reaction and heat dissipation channels within the casing, utilizing graphite heat sinks and heat pipe heat exchangers for dual cooling. Combined with the air intake channel and compressor pressurization reaction for power generation, it achieves efficient heat dissipation.
This improved the heat dissipation efficiency of the thruster, ensuring the stability and reliability of flight performance at medium and high altitudes, and preventing excessively high battery stack temperatures from affecting flight performance.
Smart Images
Figure CN115009527B_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft technology, and more specifically, to a propulsion device. Background Technology
[0002] A flight thruster is an auxiliary power unit that provides a short-term increase in thrust to rapidly increase flight speed, continuously supplying power during flight. It is primarily used to shorten takeoff distances, and sometimes to rapidly increase flight speed during flight. Takeoff thrusters are also called takeoff accelerators. They typically use rocket engines as propulsion systems, mounted externally on the fuselage or wings, and can be jettisoned after use.
[0003] Currently, flight thrusters generate a lot of heat during flight boost. If this heat cannot be dealt with in time, it will seriously affect their flight performance at medium and high altitudes. The structure of flight thrusters on the market is relatively simple, and the method of dealing with heat during flight is generally to neutralize the internal heat through the outside air. This poor heat dissipation effect affects the performance of the flight thruster. Summary of the Invention
[0004] The purpose of this invention is to provide a thruster that can improve heat dissipation efficiency and achieve better high-altitude flight performance.
[0005] The embodiments of the present invention are implemented as follows:
[0006] This application provides a thruster, including a housing body. A mounting interface is installed on the outer side of the housing body. A reaction channel and a heat dissipation channel are provided inside the housing body. A propulsion component is installed on one side of the reaction channel, and a compressor is connected to the other side of the reaction channel. The compressor is connected to a compressor motor. Multiple battery stacks for powering the propulsion component are installed in the reaction channel. Each battery stack includes multiple single battery cells arranged horizontally in sequence. A heat sink is installed between any two adjacent single battery cells, and the heat sink extends into the heat dissipation channel. An air inlet is provided in the housing body, and the air inlet is connected to both the reaction channel and the heat dissipation channel.
[0007] In some embodiments of the present invention, two heat dissipation channels are provided in the housing body, the reaction channel is located between the two heat dissipation channels, and an air inlet is provided between any one of the heat dissipation channels and the reaction channel.
[0008] In some embodiments of the present invention, the heat sink includes a graphite heat sink that extends into the heat dissipation channel.
[0009] In some embodiments of the present invention, both ends of the graphite heat sink extend into the heat dissipation channel.
[0010] In some embodiments of the present invention, the above-mentioned plurality of battery stacks are arranged longitudinally in sequence.
[0011] In some embodiments of the present invention, a heat pipe heat exchanger is installed between any two adjacent battery stacks, and the heat pipe heat exchanger extends into the heat dissipation channel.
[0012] In some embodiments of the present invention, both ends of the heat pipe heat exchanger extend into the heat dissipation channel.
[0013] In some embodiments of the present invention, the propulsion assembly includes a propulsion motor and a propeller, with the housing body connected to the propulsion motor and the propulsion motor connected to the propeller.
[0014] In some embodiments of the present invention, the air inlet is equipped with an airflow rate regulator.
[0015] In some embodiments of the present invention, the above-mentioned airflow speed regulating member includes an air intake grille.
[0016] Compared with the prior art, the embodiments of the present invention have at least the following advantages or beneficial effects:
[0017] A thruster, characterized in that it includes a housing body, a mounting interface installed on the outer side of the housing body, a reaction channel and a heat dissipation channel disposed within the housing body, a propulsion component installed on one side of the reaction channel, a compressor connected to the other side of the reaction channel, the compressor being connected to a compressor motor, multiple battery stacks for powering the propulsion component being installed within the reaction channel, each battery stack comprising multiple single battery cells arranged laterally in sequence, a heat sink being installed between any two adjacent single battery cells, and the heat sink extending into the heat dissipation channel, the housing body being provided with an air inlet, the air inlet being connected to both the reaction channel and the heat dissipation channel.
[0018] In the above embodiments, a thruster comprises a housing body, a propulsion assembly, a compressor, a compressor motor, and a battery stack. The propulsion assembly is mounted on one side of the housing body, and the compressor and compressor motor are sequentially mounted on the other side. A reaction channel and a heat dissipation channel (the heat dissipation channel and the reaction channel are mutually sealed) are provided within the housing body, and the reaction channel is connected to the compressor. A hydrogen supply pipeline is provided within the housing body, and a hydrogen supply manifold (supplying gas to the battery stack) is provided within the reaction channel. The hydrogen supply manifold is connected to the aforementioned hydrogen supply pipeline. The housing body is provided with a heat dissipation exhaust port, a reaction exhaust port, and a hydrogen exhaust port. The housing body is also connected to… An output cable powers the entire system. A mounting interface is installed on the outer side of the fuselage. The thrusters are fixed to the wings via this interface. Specifically, the crew first installs the thrusters onto the aircraft via the mounting interface. The hydrogen supply lines and output cables are also connected to the aircraft. Outside air enters the reaction chamber through the air inlet. The compressor, driven by the compressor motor, rotates and pressurizes the air. The pressurized air then reacts with hydrogen in the battery stack within the reaction chamber to generate electricity. This electricity powers the compressor motor, which in turn powers the propulsion components, propelling the aircraft. Simultaneously, a device is installed within the reaction chamber to supply power to the propulsion components. The system comprises multiple battery stacks, each stack consisting of multiple horizontally arranged individual cells. A heat sink is installed between any two adjacent individual cells, extending into a heat dissipation channel. External air simultaneously enters both the reaction channel and the heat dissipation channel. The air entering the reaction channel not only acts as a reactant for power generation but also dissipates heat from the multiple battery stacks. The heat sink, located within the reaction channel, further cools the individual cells, thus lowering the overall temperature of the battery stack. One end of the heat sink extends into the heat dissipation channel, allowing a portion of the heat sink located within the reaction channel to cool down rapidly. This dual cooling prevents the battery stack from overheating and affecting flight performance. Finally, the gas in the reaction channel is discharged from the reaction exhaust port, the gas in the heat dissipation channel is discharged from the heat dissipation exhaust port, and the hydrogen in the hydrogen supply line is discharged from the hydrogen exhaust port. Furthermore, the heat sink can be made of graphite, a novel thermally conductive and heat-dissipating material with a unique grain orientation, conducting heat uniformly in two directions. Its layered structure can adapt well to any surface, shielding heat sources and components while improving the performance of consumer electronics. The product provides uniform heat dissipation while also offering thermal insulation in terms of thickness. The surface of the graphite heat sink can be combined with other materials such as metal, plastic, and adhesive to meet more design functions and needs. Graphite heat sinks have 40% lower thermal resistance than aluminum and 20% lower thermal resistance than copper; they are 25% lighter than aluminum and 75% lighter than copper; and they can be smoothly attached to any flat and curved surface and can be cut in any form according to customer requirements.
[0019] In this embodiment, within the reaction channel, part of the heat released by the battery stack reaction is conducted to the heat dissipation channel through the heat sinks of the individual cell sandwich layers, while a portion of the reaction heat is dissipated by the air flowing through the fuel cell stack. The air pressure within the reaction channel satisfies the reaction of the battery stack, while the air pressure in the heat dissipation channel is the same as the ambient air pressure, resolving the contradiction between reaction pressure and heat dissipation in aviation fuel cells. This enables the propulsion system to achieve high-altitude flight performance. Attached Figure Description
[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.
[0021] Figure 1 This is a schematic diagram of a thruster according to an embodiment of the present invention;
[0022] Figure 2 This is a perspective view of a thruster according to an embodiment of the present invention;
[0023] Figure 3 This is a right view of the housing body according to an embodiment of the present invention;
[0024] Figure 4 This is a cross-sectional view of the housing body according to an embodiment of the present invention;
[0025] Figure 5 This is a schematic diagram of a battery stack assembly according to an embodiment of the present invention.
[0026] The diagram shows: 1-Casing body, 2-Mount interface, 3-Propulsion motor, 4-Propeller, 5-Output cable, 6-Hydrogen supply line, 7-Inlet, 8-Inlet grille, 9-Reaction exhaust port, 10-Heat exhaust port, 11-Hydrogen exhaust port, 12-Compressor, 13-Compressor motor, 14-Reaction channel, 15-Heat dissipation channel, 16-Battery stack, 17-Graphite heat sink, 18-Heat pipe heat exchanger. Detailed Implementation
[0027] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.
[0028] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.
[0029] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.
[0030] In the description of the embodiments of the present invention, it should be noted that if terms such as "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer" are used to indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed during use, they are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.
[0031] Furthermore, the use of terms such as "horizontal," "vertical," and "sag" does not imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.
[0032] In the description of the embodiments of the present invention, "multiple" means at least two.
[0033] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.
[0034] Example
[0035] Please refer to Figures 1-5As shown. This embodiment provides a thruster, characterized in that it includes a housing body 1, a mounting interface 2 installed on the outer side of the housing body 1, a reaction channel 14 and a heat dissipation channel 15 disposed inside the housing body 1, a propulsion component installed on one side of the reaction channel 14, and a compressor 12 connected to the other side of the reaction channel 14. The compressor 12 is connected to a compressor motor 13. Multiple battery stacks 16 for powering the propulsion component are installed inside the reaction channel 14. Each battery stack 16 includes multiple single battery cells arranged horizontally in sequence. A heat sink is installed between any two adjacent single battery cells, and the heat sink extends into the heat dissipation channel 15. The housing body 1 is provided with an air inlet 7, which is connected to both the reaction channel 14 and the heat dissipation channel 15.
[0036] In the above embodiment, a thruster comprises a housing body 1, a propulsion assembly, a compressor 12, a compressor motor 13, and a battery stack 16. The propulsion assembly is installed on one side of the housing body 1, and the compressor 12 and compressor motor 13 are sequentially installed on the other side. A reaction channel 14 and a heat dissipation channel 15 are provided inside the housing body 1 (the heat dissipation channel 15 and the reaction channel 14 are mutually sealed), and the reaction channel 14 is connected to the compressor 12. A hydrogen supply pipeline 6 is provided in the housing body 1, and a hydrogen supply manifold (supplying gas to the battery stack) is provided inside the reaction channel 14. The hydrogen supply manifold is connected to the aforementioned hydrogen supply pipeline 6. The housing body 1 is provided with a heat dissipation exhaust port 10, a reaction exhaust port 9, and a hydrogen exhaust port. Port 11, the fuselage body 1 is also connected to an output cable for powering the entire system. A mounting interface 2 is installed on the outside of the fuselage body 1. The thruster is fixed to the wing via the mounting interface 2. Specifically, the operator first installs the thruster onto the aircraft via the mounting interface 2. The hydrogen supply line 6 and the output cable are both connected to the aircraft. Outside air enters the reaction channel 14 through the air intake 7. The compressor 12 rotates and is pressurized under the drive of the compressor motor 13. After being pressurized by the compressor 12, the air reacts with hydrogen in the battery stack 16 within the reaction channel 14 to generate electricity. This electricity powers the compressor motor 13, driving the compressor 12, which in turn powers the propulsion components, thus propelling the aircraft. Simultaneously, within the reaction channel 14... Multiple battery stacks 16 are installed to power the propulsion components. Each battery stack 16 includes multiple individual cells arranged horizontally in sequence. A heat sink is installed between any two adjacent individual cells, and the heat sink extends into the heat dissipation channel 15. External air simultaneously enters the reaction channel 14 and the heat dissipation channel 15. The air entering the reaction channel 14 not only generates electricity as a reactant but also dissipates heat from the multiple battery stacks 16. The heat sink, located between any two adjacent individual cells, also dissipates heat from the individual cells, thereby cooling the entire battery stack 16. The air entering the heat dissipation channel 15 further cools the heat sink (located in the reaction channel 14). 4. One end of the heat sink extends into the heat dissipation channel 15, thereby rapidly cooling a portion of the heat sink located in the reaction channel 14. This dual cooling prevents the battery stack 16 from overheating and affecting flight performance. Finally, the gas in the reaction channel 14 is discharged from the reaction exhaust port 9, the gas in the heat dissipation channel 15 is discharged from the heat dissipation exhaust port 10, and the hydrogen in the hydrogen supply line 6 is discharged from the hydrogen exhaust port 11. Furthermore, the heat sink can be a graphite heat sink 17, which is a novel thermally conductive and heat-dissipating material with a unique grain orientation. It conducts heat uniformly in two directions, and its layered structure can adapt well to any surface, shielding heat sources and components while improving the performance of consumer electronics.While providing uniform heat dissipation, the product also offers thermal insulation in terms of thickness. The surface of the graphite heat sink 17 can be combined with other materials such as metal, plastic, and self-adhesive to meet more design functions and needs. The thermal resistance of the graphite heat sink 17 is 40% lower than that of aluminum and 20% lower than that of copper. The graphite heat sink 17 is 25% lighter than that of aluminum and 75% lighter than that of copper. The graphite heat sink 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to customer requirements.
[0037] In this embodiment, within the reaction channel 14, part of the heat released by the reaction of the battery stack 16 is conducted to the heat dissipation channel 15 through the heat sink of the single cell interlayer, while part of the reaction heat is dissipated by the air flowing through the fuel cell stack. The air pressure within the reaction channel 14 satisfies the reaction of the battery stack 16, while the air pressure in the heat dissipation channel 15 is the same as the ambient air pressure, thus resolving the contradiction between reaction pressure and heat dissipation in aviation fuel cells. This enables the propulsion system to achieve high-altitude flight performance.
[0038] In some embodiments of the present invention, two heat dissipation channels 15 are provided inside the housing body 1, and the reaction channel 14 is located between the two heat dissipation channels 15. An air inlet 7 is provided between any one of the heat dissipation channels 15 and the reaction channel 14.
[0039] In this embodiment, two heat dissipation channels 15 are provided inside the casing body 1. Both heat dissipation channels 15 can dissipate heat from the reaction channel 14, thereby improving heat dissipation efficiency.
[0040] In some embodiments of the present invention, the heat sink includes a graphite heat sink 17 that extends into the heat dissipation channel 15.
[0041] In this embodiment, the graphite heat sink 17 is a novel thermally conductive and heat-dissipating material with a unique grain orientation, uniformly conducting heat in two directions. Its layered structure can adapt well to any surface, shielding heat sources and components while improving the performance of consumer electronics products. While providing uniform heat dissipation, the product also offers thermal insulation in terms of thickness. The surface of the graphite heat sink 17 can be combined with other materials such as metals, plastics, and adhesives to meet more design functions and needs. The thermal resistance of the graphite heat sink 17 is 40% lower than aluminum and 20% lower than copper. The graphite heat sink 17 is 25% lighter than aluminum and 75% lighter than copper. The graphite heat sink 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to customer requirements.
[0042] In some embodiments of the present invention, both ends of the graphite heat sink 17 extend into the heat dissipation channel 15.
[0043] In this embodiment, the graphite heat sink 17 can dissipate heat from individual cells, thereby cooling the entire battery stack 16. Air entering the heat dissipation channel 15 can cool the graphite heat sink 17 (the graphite heat sink 17 is located in the reaction channel 14, with one end of the graphite heat sink 17 extending into the heat dissipation channel 15). This allows a portion of the heat sink located in the reaction channel 14 to cool down rapidly. Since both ends of the graphite heat sink 17 extend into the heat dissipation channel 15, not only can the upper and lower parts of the graphite heat sink 17 be cooled, but the cooling rate can also be increased. Rapid cooling can prevent the battery stack 16 from overheating and affecting flight performance.
[0044] In some embodiments of the present invention, multiple battery stacks 16 are arranged longitudinally in sequence.
[0045] In this embodiment, the arrangement of multiple battery stacks 16 longitudinally in sequence can make reasonable use of the space within the reaction channel 14 and save resources.
[0046] In some embodiments of the present invention, a heat pipe heat exchanger 18 is installed between any two adjacent battery stacks 16, and the heat pipe heat exchanger 18 extends into the heat dissipation channel 15.
[0047] In this embodiment, the heat pipe heat exchanger 18 is installed between two adjacent battery stacks 16. The heat pipe heat exchanger 18 can absorb the heat of the battery stacks 16 to keep them in good condition. The heat pipe heat exchanger 18 extends into the heat dissipation channel 15, and the air in the heat dissipation channel 15 will dissipate heat to the heat pipe heat exchanger 18, thereby improving the overall heat dissipation efficiency.
[0048] In some embodiments of the present invention, both ends of the heat pipe heat exchanger 18 extend into the heat dissipation channel 15.
[0049] In this embodiment, air is introduced into the heat dissipation channel 15 to dissipate heat on both sides of the heat pipe heat exchanger 18, thereby improving the overall heat dissipation efficiency.
[0050] In some embodiments of the present invention, the propulsion assembly includes a propulsion motor 3 and a propeller 4, with the housing body 1 connected to the propulsion motor 3 and the propulsion motor 3 connected to the propeller 4.
[0051] In this embodiment, the battery stack 16 generates electricity to power the compressor motor 13 to drive the compressor 12, and powers the propulsion motor 3 to drive the propeller 4 to propel the aircraft.
[0052] In some embodiments of the present invention, the air inlet 7 is equipped with an airflow rate regulator.
[0053] In this embodiment, the intake airflow speed regulator can adjust the airflow speed entering the reaction channel 14 and the heat dissipation channel 15, thereby controlling the overall flight efficiency and heat dissipation efficiency.
[0054] In some embodiments of the present invention, the air intake speed regulating element includes an air intake grille 8.
[0055] In this embodiment, the air intake grille 8 can adjust the airflow rate into the reaction channel 14 and the heat dissipation channel 15, thereby controlling the overall flight efficiency and heat dissipation efficiency.
[0056] In summary, the embodiments of the present invention provide a thruster, characterized in that it includes a housing body 1, a mounting interface 2 installed on the outer side of the housing body 1, a reaction channel 14 and a heat dissipation channel 15 disposed inside the housing body 1, a propulsion component installed on one side of the reaction channel 14, a compressor 12 connected to the other side of the reaction channel 14, a compressor motor 13 connected to the compressor 12, a plurality of battery stacks 16 for powering the propulsion component installed inside the reaction channel 14, each battery stack 16 including a plurality of single battery cells arranged horizontally in sequence, a heat sink installed between any two adjacent single battery cells, and the heat sink extending into the heat dissipation channel 15, and an air inlet 7 disposed on the housing body 1, the air inlet 7 being connected to both the reaction channel 14 and the heat dissipation channel 15.
[0057] In the above embodiment, a thruster comprises a housing body 1, a propulsion assembly, a compressor 12, a compressor motor 13, and a battery stack 16. The propulsion assembly is installed on one side of the housing body 1, and the compressor 12 and compressor motor 13 are sequentially installed on the other side. A reaction channel 14 and a heat dissipation channel 15 are provided inside the housing body 1 (the heat dissipation channel 15 and the reaction channel 14 are mutually sealed), and the reaction channel 14 is connected to the compressor 12. A hydrogen supply pipeline 6 is provided in the housing body 1, and a hydrogen supply manifold (supplying gas to the battery stack) is provided inside the reaction channel 14. The hydrogen supply manifold is connected to the aforementioned hydrogen supply pipeline 6. The housing body 1 is provided with a heat dissipation exhaust port 10, a reaction exhaust port 9, and a hydrogen exhaust port. Port 11, the fuselage body 1 is also connected to an output cable for powering the entire system. A mounting interface 2 is installed on the outside of the fuselage body 1. The thruster is fixed to the wing via the mounting interface 2. Specifically, the operator first installs the thruster onto the aircraft via the mounting interface 2. The hydrogen supply line 6 and the output cable are both connected to the aircraft. Outside air enters the reaction channel 14 through the air intake 7. The compressor 12 rotates and is pressurized under the drive of the compressor motor 13. After being pressurized by the compressor 12, the air reacts with hydrogen in the battery stack 16 within the reaction channel 14 to generate electricity. This electricity powers the compressor motor 13, driving the compressor 12, which in turn powers the propulsion components, thus propelling the aircraft. Simultaneously, within the reaction channel 14... Multiple battery stacks 16 are installed to power the propulsion components. Each battery stack 16 includes multiple individual cells arranged horizontally in sequence. A heat sink is installed between any two adjacent individual cells, and the heat sink extends into the heat dissipation channel 15. External air simultaneously enters the reaction channel 14 and the heat dissipation channel 15. The air entering the reaction channel 14 not only generates electricity as a reactant but also dissipates heat from the multiple battery stacks 16. The heat sink, located between any two adjacent individual cells, also dissipates heat from the individual cells, thereby cooling the entire battery stack 16. The air entering the heat dissipation channel 15 further cools the heat sink (located in the reaction channel 14). 4. One end of the heat sink extends into the heat dissipation channel 15, thereby rapidly cooling a portion of the heat sink located in the reaction channel 14. This dual cooling prevents the battery stack 16 from overheating and affecting flight performance. Finally, the gas in the reaction channel 14 is discharged from the reaction exhaust port 9, the gas in the heat dissipation channel 15 is discharged from the heat dissipation exhaust port 10, and the hydrogen in the hydrogen supply line 6 is discharged from the hydrogen exhaust port 11. Furthermore, the heat sink can be a graphite heat sink 17, which is a novel thermally conductive and heat-dissipating material with a unique grain orientation. It conducts heat uniformly in two directions, and its layered structure can adapt well to any surface, shielding heat sources and components while improving the performance of consumer electronics.While providing uniform heat dissipation, the product also offers thermal insulation in terms of thickness. The surface of the graphite heat sink 17 can be combined with other materials such as metal, plastic, and self-adhesive to meet more design functions and needs. The thermal resistance of the graphite heat sink 17 is 40% lower than that of aluminum and 20% lower than that of copper. The graphite heat sink 17 is 25% lighter than that of aluminum and 75% lighter than that of copper. The graphite heat sink 17 can be smoothly attached to any flat and curved surface and can be cut in any form according to customer requirements.
[0058] In this embodiment, within the reaction channel 14, part of the heat released by the reaction of the battery stack 16 is conducted to the heat dissipation channel 15 through the heat sink of the single cell interlayer, while part of the reaction heat is dissipated by the air flowing through the fuel cell stack. The air pressure within the reaction channel 14 satisfies the reaction of the battery stack 16, while the air pressure in the heat dissipation channel 15 is the same as the ambient air pressure, thus resolving the contradiction between reaction pressure and heat dissipation in aviation fuel cells. This enables the propulsion system to achieve high-altitude flight performance.
[0059] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.
Claims
1. A thruster, characterized in that, The device includes a casing body with a mounting interface on its outer side. The casing body contains a sealed reaction channel and a heat dissipation channel. A propulsion assembly is mounted on one side of the reaction channel, and a compressor is connected to the other side. The casing body has a hydrogen supply pipeline, and a hydrogen supply manifold for supplying gas to the battery stack is located within the reaction channel. The hydrogen supply manifold is connected to the hydrogen supply pipeline. The casing body has a heat dissipation exhaust port, a reaction exhaust port, and a hydrogen exhaust port. The compressor is connected to a compressor motor. Multiple battery stacks for powering the propulsion assembly are installed within the reaction channel. Each battery stack includes multiple horizontally arranged individual battery cells. A heat dissipation fin is installed between any two adjacent individual battery cells, extending into the heat dissipation channel. The casing body has an air inlet connected to both the reaction channel and the heat dissipation channel. The casing body is provided with two heat dissipation channels, the reaction channel is located between the two heat dissipation channels, and an air inlet is provided between each heat dissipation channel and the reaction channel; The heat sink includes a graphite heat sink, with both ends of the graphite heat sink extending into the heat dissipation channel; Multiple battery stacks are arranged longitudinally in sequence; A heat pipe heat exchanger is installed between any two adjacent battery stacks, and both ends of the heat pipe heat exchanger extend into the heat dissipation channel.
2. A thruster according to claim 1, characterized in that, The propulsion assembly includes a propulsion motor and a propeller, with the housing body connected to the propulsion motor and the propulsion motor connected to the propeller.
3. A thruster according to claim 1, characterized in that, The air inlet is equipped with an airflow rate regulator.
4. A thruster according to claim 3, characterized in that, The air intake speed regulating component includes an air intake grille.