Aircraft outer surface natural heat dissipation system and aircraft

Abstract

The utility model belongs to the technical field of aircraft heat dissipation, and discloses an aircraft outer surface natural heat dissipation system and an aircraft, the aircraft outer surface natural heat dissipation system is installed on an aircraft body of the aircraft and is arranged in an exposed mode, the aircraft outer surface natural heat dissipation system comprises a plurality of radiators, and the radiators are sequentially connected to form a polygonal structure. The polygonal structure is provided with a liquid inlet and a liquid outlet, the liquid outlet is connected with a liquid cooling inlet of an engine of the aircraft, and the liquid inlet is connected with a liquid cooling outlet of the engine. The heat dissipation system is simple in structure, light in weight, high in cooling efficiency and capable of replacing exterior trimming parts of an engine compartment of an aircraft, the weight of an aircraft system is reduced, and materials are saved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a natural heat dissipation system for the outer surface of an aircraft and an aircraft. Background Technology

[0002] As multirotor aircraft become increasingly larger, pure electric propulsion can no longer meet flight requirements, necessitating the addition of engine systems. These additional engine systems require corresponding cooling systems to address the engine's heat dissipation issues. Traditional high-power internal combustion engine cooling devices are bulky, heavy, and require dedicated fans, making them unsuitable for multirotor aircraft. Utility Model Content

[0003] The first objective of this invention is to provide an aircraft external surface heat dissipation system that has a simple structure, light weight, high cooling efficiency, and can replace the aircraft engine compartment exterior trim, thereby reducing the weight of the aircraft system and saving materials.

[0004] The second objective of this invention is to provide an aircraft with improved engine cooling performance and relatively low system weight, thus saving on manufacturing materials.

[0005] To achieve this objective, the present invention adopts the following technical solution:

[0006] This utility model discloses an aircraft external surface natural heat dissipation system. The aircraft external surface natural heat dissipation system is installed on the aircraft fuselage and is exposed. The aircraft external surface natural heat dissipation system includes multiple radiators, which are connected in sequence to form a polygonal structure. The polygonal structure has a liquid inlet and a liquid outlet. The liquid outlet is connected to the liquid cooling inlet of the aircraft engine, and the liquid inlet is connected to the liquid cooling outlet of the engine.

[0007] In some embodiments, each heat sink includes a plurality of heat pipes, which are spaced apart in a vertical direction.

[0008] In some specific embodiments, multiple heat dissipation pipes are connected end to end in sequence so that multiple heat sinks are connected in series. In two adjacent heat sinks, the heat dissipation pipe at the end of the series connection of one heat sink is connected to the heat dissipation pipe at the beginning of the series connection of the other heat sink.

[0009] In some specific embodiments, multiple heat dissipation pipes are arranged at intervals along the vertical direction, and multiple heat sinks are located at the same height. The heat dissipation pipes are connected end to end to form a segmented ring structure, so that the polygonal structure includes multiple segmented ring structures arranged in parallel. The segmented ring structure has a liquid inlet and a liquid outlet. The liquid outlet is connected to the liquid cooling inlet, and the liquid inlet is connected to the liquid cooling outlet.

[0010] In some specific embodiments, the structures of the multiple heat pipes are identical.

[0011] In some specific embodiments, each heat sink is provided with a connecting pipe at both ends; the two heat sinks are connected by a connecting pipe inserted into the connecting pipe.

[0012] In some specific embodiments, each heat sink has a plurality of heat dissipation fins spaced apart along its length on its outer peripheral wall.

[0013] In some specific embodiments, each of the heat dissipation fins is formed as an annular heat dissipation fin surrounding the heat dissipation tube.

[0014] In some embodiments, the structures of the plurality of heat sinks are identical, and the polygonal structure is a regular polygonal structure.

[0015] This utility model discloses an aircraft, including a fuselage, a cantilever, an engine, a propeller, and the aforementioned aircraft external surface natural heat dissipation system. One end of the cantilever is connected to the fuselage, the engine and the propeller are mounted on the other end of the cantilever, and the aircraft external surface natural heat dissipation system is mounted on the fuselage and is exposed.

[0016] The beneficial effects of this invention are as follows: Because the aircraft's external surface natural heat dissipation system is installed on the aircraft fuselage and exposed, it replaces the original engine compartment exterior trim as a decorative component, which helps reduce the weight of the aircraft system and saves manufacturing materials. During actual operation, the engine coolant enters the radiator through the inlet. As the coolant flows within the radiator, it exchanges heat with the external environment, thus achieving heat dissipation. Since the entire heat dissipation system is exposed, it improves heat dissipation efficiency and speed, and eliminates the need for a cooling fan as in existing technologies, reducing the weight of the system, saving manufacturing costs, and improving reliability. Simultaneously, because multiple radiators are connected in sequence to form a polygonal structure, the fluid inside the cooling pipes undergoes approximately circular motion, resulting in a smooth change in fluid momentum direction, low flow resistance, and minimal cooling power loss, further improving the heat dissipation efficiency and effect of the system.

[0017] Additional aspects and advantages of this invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the structure of the natural heat dissipation system on the outer surface of an aircraft according to an embodiment of the present invention;

[0019] Figure 2This is a schematic diagram of the structure of the aircraft outer surface natural heat dissipation system in another direction according to an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the structure of a heat sink according to an embodiment of the present invention.

[0021] Figure 4 This is a schematic diagram of the structure of an aircraft according to an embodiment of the present invention.

[0022] Figure label:

[0023] 100. Radiator; 110. Heat sink tube; 120. Heat sink fins; 130. Connecting pipes; 101. Liquid outlet; 102. Liquid inlet;

[0024] 200, Engine; 210, Liquid cooling inlet; 220, Liquid cooling outlet; 230, Liquid outlet pipe; 240, Liquid return pipe;

[0025] 300, fuselage; 400, cantilever; 500, propeller. Detailed Implementation

[0026] The present invention will now be described in further detail with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and not intended to limit it. Furthermore, it should be noted that, for ease of description, the accompanying drawings show only the parts relevant to the present invention, not the entire structure.

[0027] In the description of this utility model, unless otherwise explicitly specified and limited, the terms "connected," "linked," and "fixed" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; 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; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0028] In the description of this embodiment, the terms "upper," "lower," "left," "right," "front," and "rear," etc., refer to the orientation or positional relationship shown in the accompanying drawings. They are used only for ease of description and simplification of operation, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0029] The following is for reference. Figures 1-3 This invention describes the specific structure of a natural heat dissipation system for the outer surface of an aircraft, according to a specific embodiment of the present invention.

[0030] This utility model discloses a natural heat dissipation system for the outer surface of an aircraft (hereinafter referred to as the heat dissipation system for ease of description), see reference. Figure 1 and Figure 3 As shown, in a specific embodiment of this utility model, the aircraft's external surface natural heat dissipation system is installed on the aircraft fuselage 300 and is exposed. The aircraft's external surface natural heat dissipation system includes multiple radiators 100, which are connected in sequence to form a polygonal structure. The polygonal structure has a liquid inlet 102 and a liquid outlet 101. The liquid outlet 101 is connected to the liquid cooling inlet 210 of the aircraft's engine 200 through a liquid outlet pipe 230, and the liquid inlet 102 is connected to the liquid cooling outlet 220 of the engine 200 through a liquid return pipe 240. It can be understood that, since the heat dissipation system in this embodiment is installed on the aircraft fuselage 300 and is exposed, the heat dissipation system replaces the original engine compartment exterior trim as a decorative component, which helps to reduce the weight of the aircraft system and save manufacturing materials. In actual operation, the coolant in the engine 200 enters the radiator 100 through the inlet 102. As the coolant flows within the radiator 100, it exchanges heat with the external environment, thus achieving heat dissipation. Because the entire cooling system is exposed, it improves heat dissipation efficiency and speed, and eliminates the need for a cooling fan, reducing the weight of the cooling system, saving manufacturing costs, and improving reliability. Simultaneously, since multiple radiators 100 are connected in sequence to form a polygonal structure, the fluid within the cooling pipes 110 undergoes approximately circular motion, resulting in a smooth change in fluid momentum direction, low flow resistance, and minimal cooling power loss, further enhancing the cooling efficiency and effectiveness of the cooling system.

[0031] refer to Figure 2 As shown, each radiator 100 includes multiple heat dissipation pipes 110, which are spaced apart in a vertical direction. It can be understood that the inclusion of multiple heat dissipation pipes 110 in the radiator 100 increases the heat exchange area of ​​the radiator 100, thereby accelerating the heat dissipation rate of the coolant within the radiator 100 and improving the heat dissipation efficiency of the cooling system.

[0032] refer to Figure 2As shown, multiple heat dissipation pipes 110 are arranged at intervals along the vertical direction. Multiple radiators 100 are located at the same height, and the heat dissipation pipes 110 are connected end-to-end to form a ring structure. This results in a polygonal structure comprising multiple parallel ring structures. Each ring structure has a liquid inlet and a liquid outlet. The liquid outlet is connected to the liquid cooling inlet 210, and the liquid inlet is connected to the liquid cooling outlet 220. Understandably, during actual operation, the coolant from the engine 200 is discharged from the liquid cooling outlet 220 and splits into multiple streams. These streams enter the ring structure formed by the multiple heat dissipation pipes 110 connected in series through multiple liquid inlets. After exchanging heat with the external environment within the multiple ring structures, the coolant enters the liquid cooling inlet 210 through multiple liquid outlets to cool the engine 200. The design of multiple ring structures helps to accelerate the heat dissipation of the coolant in the radiator 100, thereby improving the heat dissipation efficiency of the heat dissipation system. In addition, the parallel structure has good reliability. Even if one ring structure is damaged, it will not affect the normal operation of other ring structures for the time being, which helps to ensure the operational reliability of the entire heat dissipation system.

[0033] Optionally, the multiple heat dissipation pipes 110 may have identical structures. It is understood that having multiple heat dissipation pipes 110 of uniform specifications makes processing easier, reduces manufacturing costs, and facilitates installation. Of course, in other embodiments of this invention, the structure of the multiple heat dissipation pipes 110 can be adjusted according to their specific installation location to meet actual assembly needs.

[0034] Optional, see reference Figure 3 As shown, each heat sink 110 has connecting pipes at both ends; two heat sinks 110 are connected by connecting pipes 130 inserted into the connecting pipes. It is understood that in the actual assembly process, two adjacent heat sinks 110 in each ring structure can be connected via connecting pipes 130, simplifying the assembly process of the ring structure and facilitating the assembly of the entire heat dissipation system. To improve the connection sealing, the connecting pipes 130 and the connecting pipes are sealed together using sealants or other sealing materials, ensuring the overall airtightness of the radiator 100 and preventing coolant leakage.

[0035] Optional, see reference Figure 3 As shown, each heat dissipation pipe 110 has multiple heat dissipation fins 120 spaced apart along its length on its outer peripheral wall. It can be understood that the added heat dissipation fins 120 can further increase the heat dissipation area between the heat sink 100 and the external environment, thereby further improving the heat dissipation effect and efficiency of the heat sink 100.

[0036] Optionally, each heat dissipation fin 120 is formed as an annular heat dissipation fin surrounding the heat dissipation pipe 110. The annular heat dissipation fin can further increase the heat dissipation area between the heat sink 100 and the external environment, thereby further improving the heat dissipation effect and efficiency of the heat sink 100. Of course, in other embodiments of this invention, the shape of the heat dissipation fin 120 can be selected according to actual needs, and is not limited to the annular heat dissipation fin of this embodiment.

[0037] Alternatively, multiple radiators 100 may have identical structures, and the polygonal structure may be a regular polygon. It is understood that having multiple radiators 100 with identical structures and uniform specifications facilitates processing, reduces manufacturing costs, and makes installation convenient. The regular polygonal structure allows the fluid movement within the heat pipe 110 to approximate circular motion as closely as possible, resulting in a smooth change in fluid momentum direction, low flow resistance, and minimal cooling power loss. (Reference) Figure 1 and Figure 2 The heat dissipation system of this embodiment includes six identical heat sinks 100, which are assembled into a regular hexagonal structure. Of course, in other embodiments of this utility model, the number of heat sinks 100 and the number of heat dissipation pipes 110 in each heat sink 100 can be adjusted according to actual needs and are not limited to the number in this embodiment.

[0038] It should be noted that, in other embodiments of this utility model, the structure of the plurality of heat sinks 100 can be adjusted according to their specific installation positions to meet actual assembly needs.

[0039] In another specific embodiment of this utility model, multiple heat dissipation pipes 110 are connected end to end in sequence, so that multiple radiators 100 are arranged in series. In two adjacent radiators 100, the heat dissipation pipe 110 at the end of the series connection of one radiator 100 is connected to the heat dissipation pipe 110 at the beginning of the series connection of the other radiator 100. It can be understood that compared with the parallel structure described above, the connection method of the series structure is simpler. The liquid cooling inlet 210 and the liquid cooling outlet 220 of the engine 200 only need to be connected to one heat dissipation pipe 110, which facilitates the assembly of the cooling system.

[0040] This utility model discloses an aircraft, with reference to Figure 4As shown, the aircraft includes a fuselage 300, a cantilever 400, an engine 200, a propeller 500, and the aforementioned external surface natural cooling system. One end of the cantilever 400 is connected to the fuselage 300, and the engine 200 and propeller 500 are mounted on the other end of the cantilever 400. The external surface natural cooling system is mounted on the fuselage 300 and is exposed. It can be understood that the cooling system is mounted on the fuselage 300, the cantilever 400 is mounted on the fuselage 300, the engine 200 is mounted at the end of the cantilever 400, and the propeller 500 is mounted on the upper part of the engine 200. The propeller 500 generates a downward airflow when it operates. When propeller 500 is not working, engine 200 has low power and low heat dissipation requirements. It can remove the heat from engine 200 by exchanging heat with the air through the hexagonal heat dissipation system on the outer ring and dissipating the heat naturally. When propeller 500 is working at high power, engine 200 has high power and high heat dissipation requirements. The rotation of propeller 500 can generate high-speed airflow, which flows over the surface of heat dissipation pipe 110, greatly improving the heat dissipation power of heat dissipation pipe 110 and meeting the heat dissipation requirements of the aircraft.

[0041] In the description of this specification, references to terms such as "some embodiments," "other embodiments," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0042] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A natural heat dissipation system for the outer surface of an aircraft, characterized in that, The aircraft external surface natural heat dissipation system is installed on the aircraft fuselage (300) and is exposed. The aircraft external surface natural heat dissipation system includes multiple radiators (100), which are connected in sequence to form a polygonal structure. The polygonal structure has a liquid inlet (102) and a liquid outlet (101). The liquid outlet (101) is connected to the liquid cooling inlet (210) of the aircraft engine (200), and the liquid inlet (102) is connected to the liquid cooling outlet (220) of the engine (200).

2. The aircraft external surface natural heat dissipation system according to claim 1, characterized in that, Each of the heat sinks (100) includes a plurality of heat dissipation pipes (110) which are spaced apart in a vertical direction.

3. The aircraft external surface natural heat dissipation system according to claim 2, characterized in that, Multiple heat dissipation pipes (110) are connected end to end so that multiple heat sinks (100) are connected in series. In two adjacent heat sinks (100), the heat dissipation pipe (110) at the end of the series connection of one heat sink (100) is connected to the heat dissipation pipe (110) at the beginning of the series connection of the other heat sink (100).

4. The aircraft external surface natural heat dissipation system according to claim 2, characterized in that, Multiple heat dissipation pipes (110) are arranged at intervals in the vertical direction. Multiple heat sinks (100) are located at the same height. The heat dissipation pipes (110) are connected end to end to form a ring structure, so that the polygonal structure includes multiple ring structures arranged in parallel. The ring structure has a liquid inlet and a liquid outlet. The liquid outlet is connected to the liquid cooling inlet (210), and the liquid inlet is connected to the liquid cooling outlet (220).

5. The aircraft external surface natural heat dissipation system according to claim 3 or 4, characterized in that, The structures of the multiple heat pipes (110) are completely identical.

6. The aircraft external surface natural heat dissipation system according to claim 3 or 4, characterized in that, Each of the heat dissipation pipes (110) has a connecting pipe at both ends; the two heat dissipation pipes (110) are connected by a connecting pipe (130) inserted into the connecting pipe.

7. The aircraft external surface natural heat dissipation system according to claim 2, characterized in that, Each heat sink (110) has a plurality of heat sink fins (120) spaced apart along its length on its outer peripheral wall.

8. The aircraft external surface natural heat dissipation system according to claim 7, characterized in that, Each of the heat dissipation fins (120) is formed as an annular heat dissipation fin surrounding the heat dissipation tube (110).

9. The aircraft external surface natural heat dissipation system according to claim 1, characterized in that, The structures of the multiple heat sinks (100) are identical, and the polygonal structure is a regular polygonal structure.

10. An aircraft, characterized in that, The aircraft includes a fuselage (300), a cantilever (400), an engine (200), a propeller (500), and an aircraft external surface natural heat dissipation system as described in any one of claims 1-9. One end of the cantilever (400) is connected to the fuselage (300), the engine (200) and the propeller (500) are mounted on the other end of the cantilever (400), and the aircraft external surface natural heat dissipation system is mounted on the fuselage (300) and is exposed.

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