Hybrid power aircraft

Abstract

The invention provides a hybrid aircraft. The hybrid aircraft comprises a fan, a first pipeline, a second pipeline and a radiator, an air inlet is formed in the windward side of the nose part of the hybrid aircraft, an air inlet of the fan is opposite to the air inlet, and an air outlet of the fan is opposite to an air inlet port of the first pipeline and the windward side of radiating fins of the radiator. The air outlet port of the first pipeline is opposite to the heat dissipation component of the range extender, and the leeside of the heat dissipation fins is opposite to the air inlet port of the second pipeline. According to the hybrid power aircraft, external airflow can be introduced through the air inlet, the external airflow can be accelerated in combination with the fan, then heat dissipation is conducted on equipment in the range extending cabin through the radiator and the first pipeline, and the good heat dissipation effect is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a hybrid power aircraft. Background Art

[0002] In recent years, with the rapid development of the low-altitude economy, electric aircraft have become widely anticipated. However, purely electric aircraft suffer from a short range. Hybrid aircraft have been developed to address this issue. Compared to purely electric aircraft, hybrid aircraft utilize fuel engines or other auxiliary power sources to significantly extend flight time and range. However, due to the added power source, hybrid aircraft have higher heat dissipation requirements than purely electric aircraft. Currently, no hybrid aircraft equipped with dedicated thermal management systems exists on the market. Therefore, a hybrid aircraft is presented. Summary of the Invention

[0003] In order to overcome the above-mentioned drawbacks, the present invention aims to provide a hybrid power aircraft.

[0004] According to one aspect of the present invention, a hybrid aircraft is provided, wherein a range extender cabin is provided at the nose portion of the hybrid aircraft, a range extender is provided in the range extender cabin, the hybrid aircraft includes a fan, a first duct, a second duct and a radiator, an air inlet is provided on the windward surface of the nose portion, the air inlet of the fan is opposite to the air inlet, the air outlet of the fan is opposite to the air inlet port of the first duct and the windward surface of the cooling fins of the radiator, the air outlet port of the first duct is opposite to the heat dissipation component of the range extender, the leeward surface of the cooling fin is opposite to the air inlet port of the second duct, the air outlet port of the second duct is provided on the side surface of the nose portion, and the flow channel of the radiator is connected to the flow channel of at least one cooling system configured in the range extender cabin.

[0005] Furthermore, the air inlet of the first pipe is closer to the air outlet of the fan than the windward side of the heat dissipation fins, and the area of ​​the air inlet of the second pipe is greater than or equal to the area of ​​the leeward side of the heat dissipation fins.

[0006] Furthermore, the air outlet end of the second pipe is in a "Y" shape, and the air outlet port of the second pipe includes a first air outlet port and a second air outlet port, and the first air outlet port and the second air outlet port are respectively arranged on both side surfaces of the head portion.

[0007] Furthermore, a plurality of cooling systems are configured in the range-extending cabin, and the number of flow channels of the radiator corresponds to the number of cooling systems in the range-extending cabin so as to be connected to the plurality of cooling systems in the range-extending cabin respectively.

[0008] Furthermore, the plurality of cooling systems include one or a combination of any multiple of a generator water cooling system, an engine water cooling system, and an oil cooling system.

[0009] Furthermore, the range extender is provided with a plurality of heat dissipation components, the air outlet port of the first duct includes a plurality of air outlet ports corresponding one-to-one to the plurality of heat dissipation components, and the plurality of air outlet ports are respectively arranged opposite to the plurality of heat dissipation components.

[0010] Furthermore, the range extender includes an engine, and the air outlet port of the first pipe further includes an engine branch port, which is communicated with the air inlet of the engine.

[0011] Furthermore, the range extender includes an engine, an exhaust port is provided on the surface of the range extender cabin, an exhaust pipe of the engine passes through the exhaust port and is connected to the outside, and an area of ​​the exhaust port is larger than a cross-sectional area of ​​the exhaust pipe.

[0012] Furthermore, a fuselage cabin is provided in the fuselage portion of the hybrid aircraft. Based on any of the aforementioned embodiments, the hybrid aircraft also includes a fuselage heating pipe, the air inlet port of the fuselage heating pipe is connected to the downstream pipe of the second pipe, and the air outlet port of the fuselage heating pipe is connected to the fuselage cabin.

[0013] Furthermore, the surface of the fuselage cabin is also provided with a plurality of air inlets and a plurality of air outlets. The air inlets are provided at the front or middle of the fuselage cabin, and the air outlets are provided at the rear of the fuselage cabin.

[0014] Furthermore, the air inlet is arranged on the side surface of the fuselage cabin, and the air inlet is also provided with a waterproof component, which includes a first grille, a second grille and a deposition area. The first grille, the deposition area and the second grille are arranged in sequence from the surface of the fuselage cabin inward. The position of the second grille relative to the fuselage cabin is higher than the first grille, and the deposition area connects at least the bottom of the second grille and the bottom of the first grille.

[0015] The hybrid aircraft provided by the present invention combines active cooling by a fan with passive cooling by utilizing oncoming airflow, achieving improved heat dissipation. Furthermore, the passive cooling method utilizing oncoming airflow reduces energy consumption, further increasing the range of the range extender. High-temperature gas downstream of the radiator is further collected as a heating medium for the fuselage compartment, and external airflow is introduced as a cooling medium for the fuselage compartment. Dampers are used to control the amount of heating and cooling medium entering the compartment, respectively, to maintain the equipment within the compartment, such as the battery pack and other components, operating within a suitable temperature range. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above features and advantages of the present invention will be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings.

[0017] Figure 1 A schematic diagram of the regional division of a hybrid aircraft is shown.

[0018] Figure 2 A side perspective view of the nose portion of a hybrid aircraft is shown in accordance with one embodiment.

[0019] Figure 3a-3b Two approaches to effective relative are shown.

[0020] Figure 4 A top perspective view of the nose portion of a hybrid aircraft in a specific embodiment is shown.

[0021] Figure 5 A perspective view of the nose section of a hybrid aircraft including fuselage heating ducts is shown.

[0022] Figure 6 The structure of the waterproof component in a specific embodiment is shown.

[0023] For the sake of clarity, a brief description of the reference numerals is given below:

[0024] 21 air intakes;

[0025] 23 exhaust port;

[0026] 24 radiators;

[0027] 25 fans;

[0028] 26 first pipeline;

[0029] 27 second pipeline;

[0030] 28 exhaust pipes;

[0031] 271 air outlet port of the second duct;

[0032] 261 air outlet port of the first pipe;

[0033] 262 engine branch port;

[0034] 41 first air outlet port;

[0035] 42 second air outlet port;

[0036] 51 fuselage heating pipe;

[0037] 52 second pipeline;

[0038] 61 first grid;

[0039] 62 sedimentary area;

[0040] 63 Second grid. DETAILED DESCRIPTION

[0041] The following description is provided to enable those skilled in the art to make and use the present invention and to incorporate it into a specific application context. Various modifications and uses in different applications will be readily apparent to those skilled in the art, and the general principles defined herein are applicable to a wide range of embodiments. Thus, the present invention is not limited to the embodiments set forth herein, but should be accorded the broadest scope consistent with the principles and novel features disclosed herein.

[0042] In the following detailed description, many specific details are set forth to provide a more thorough understanding of the present invention. However, it will be apparent to those skilled in the art that the practice of the present invention need not be limited to these specific details. In other words, known structures and devices are shown in block diagram form without detailed display to avoid obscuring the present invention.

[0043] The reader's attention is drawn to all documents and materials filed concurrently with this specification and open to public inspection, and the contents of all such documents and materials are incorporated herein by reference. Unless otherwise expressly stated, all features disclosed in this specification (including any accompanying claims, abstracts, and drawings) may be replaced by alternative features serving the same, equivalent, or similar purpose. Therefore, unless expressly stated otherwise, each feature disclosed is merely an example of a group of equivalent or similar features.

[0044] Note that where used, the terms first, second, left, right, front, back, top, bottom, forward, reverse, clockwise, and counterclockwise are used for convenience only and do not imply any specific fixed direction. Instead, they are used to reflect the relative position and / or orientation of various parts of an object. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0045] In the description of the present invention, it should be noted that, unless otherwise clearly stipulated and limited, the terms "setting", "connection" and "configuration" should be understood in a broad sense. For example, the setting can be a fixed setting, a detachable setting, or an integrated setting; "connection" can be direct connection, indirect connection through an intermediate medium, or connection between two components; "configuration" can be a separate configuration or a combined configuration. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood in combination with specific circumstances.

[0046] Note that, where used, "further," "preferably," "further," and "more preferably" are simply prefaces for describing another embodiment based on the preceding embodiment. The contents of the "further," "preferably," "further," or "more preferably" combined with the preceding embodiment constitute a complete configuration of another embodiment. Multiple "further," "preferably," "more preferably," or "more preferably" clauses appended to the same embodiment can be arbitrarily combined to form yet another embodiment.

[0047] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments. Note that the various aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention.

[0048] A hybrid aircraft is one that uses two or more power sources. Compared to purely electric aircraft, hybrid aircraft incorporate a range extender, which consists of two power units: an electric motor and a range extender. A range extender is a power-assisted device used to extend the flight endurance of a drone. By providing additional energy, it addresses issues such as short flight time and insufficient range caused by battery capacity limitations.

[0049] A range extender typically consists of an engine and a generator. Typical engines include fuel-powered engines such as two-stroke and four-stroke engines or micro-turbines, as well as new energy engines such as proton exchange membrane fuel cells or methanol reforming fuel cells. Typical generators include synchronous generators such as rare earth permanent magnet synchronous generators or brushless synchronous generators, as well as asynchronous generators such as squirrel cage asynchronous generators or wound rotor asynchronous generators.

[0050] According to one aspect of the present invention, a hybrid aircraft equipped with a heat dissipation device is provided.

[0051] In some embodiments, a range extender cabin is provided at the nose of the hybrid aircraft, and a range extender is provided in the range extender cabin.

[0052] The nose of a hybrid aircraft refers to the area at the front end of the aircraft that points in the direction of flight when the aircraft is in level flight. Figure 1 A schematic diagram of the regional division of the hybrid aircraft is shown. Figure 1 In the embodiment shown, area I in the figure is the head portion.

[0053] The range extender cabin is the cabin on the hybrid aircraft where the range extender is installed. The range extender, cooling system, control system and other related components are usually installed in the range extender cabin.

[0054] In some embodiments, an air inlet is provided on the windward side of the nose portion.

[0055] The windward surface of the nose refers to the surface area of ​​the aircraft's nose that is first directly exposed to the airflow during level flight. Air inlets are located on the windward surface of the nose. There can be one or more air inlets, through which external air enters the extended-range cabin. It is understood that while this application does not require the number of air inlets, the overall area of ​​the air inlets must match the air intake efficiency required by the aircraft during heat dissipation.

[0056] Figure 2 A side perspective view of the nose of a hybrid aircraft in accordance with an embodiment of the present invention is shown. Figure 2 In the embodiment shown, the air inlet 21 is provided on the windward side of the nose portion, and external air can enter the range-extending cabin through the air inlet 21 .

[0057] refer to Figure 2 The heat dissipation device of the hybrid aircraft may include a radiator 24 , a fan 25 , a first pipe 26 and a second pipe 27 .

[0058] A radiator is a heat exchange device used to dissipate heat within an aircraft. The radiator transfers heat from the equipment to be dissipated to the cooling medium in the radiator through heat exchange between the cooling medium and the equipment to be dissipated. The cooling medium in the radiator then dissipates heat to the outside world through cooling fins, heat pipes or other common heat dissipation structures.

[0059] The fan is used to accelerate the gas entering the range extender cabin. The gas accelerated by the fan flows to the first pipe and the radiator as a cooling medium to dissipate heat from the corresponding components.

[0060] In some embodiments, the air inlet of the fan is opposite to the air inlet, the air outlet of the fan is opposite to the air inlet port of the first pipe and the windward side of the heat sink fins of the radiator, and the leeward side of the heat sink fins is opposite to the air inlet port of the second pipe.

[0061] It can be understood that the area where external air enters the fan is the air inlet of the fan, and the area where the air flows out after passing through the fan is the air outlet of the fan.

[0062] The windward side of the heat sink fins refers to the side of the heat sink fins that first contacts the cooling airflow (such as the air blown by a fan). The leeward side of the heat sink fins refers to the side of the heat sink fins where the cooling airflow leaves the heat sink fins.

[0063] It should be noted that the air inlet of the fan is opposite to the air inlet, which means that the air flow can reach the fan air inlet smoothly and with low loss from the air inlet, that is, effectively opposite. Figure 3a and Figure 3b Two effective relative modes are shown, including the air inlet 31 and the fan air inlet 32, referring to Figure 3a and Figure 3b It is understood that the relative in the present invention can be as follows Figure 3a The direction shown is relative, and can also be as follows Figure 3b The indirect relative or offset relative methods such as the spatial offset relative shown can be called relative even if there is an offset or offset, and are not limited to strict oppositeness.

[0064] by Figure 2 Taking the illustrated embodiment as an example, in some embodiments, the air outlet port 271 of the second duct 27 is disposed on the side surface of the head portion.

[0065] The side surface of the nose portion refers to any surface other than the front windward surface of the aircraft, such as the left side surface, right side surface, top side surface, or bottom side surface. The outlet port of the second duct discharges the air after the heat is dissipated by the radiator out of the aircraft.

[0066] by Figure 2 Taking the illustrated embodiment as an example, in some embodiments, the air outlet port 261 of the first duct 26 is opposite to the heat dissipation component of the range extender.

[0067] Those skilled in the art will appreciate that, to achieve better heat dissipation, the range extender is also provided with heat dissipation components, such as cylinder head heat sinks, air shrouds, metal heat sinks, heat coils, or other common heat dissipation components. The air outlet of the first duct is opposite to the heat dissipation component of the range extender, and the gas entering through the air inlet dissipates heat from the heat dissipation component of the range extender. In some specific embodiments, the range extender may include multiple heat dissipation components, and the air outlet of the first duct may be provided with multiple air outlet ports corresponding to the multiple heat dissipation components, and the multiple air outlet ports are respectively provided opposite to the multiple heat dissipation components.

[0068] In some embodiments, a cooling system is further configured in the range-extending cabin, and a flow channel of the radiator is connected to a flow channel of at least one cooling system configured in the range-extending cabin.

[0069] The cooling system is a heat dissipation system that absorbs the heat generated by the range extender during operation through a circulating cooling medium (such as coolant) and exchanges heat with the outside world. The cooling medium in the cooling system's flow channels, located within the range extender's cabin, exchanges heat with the equipment within the cabin that requires heat dissipation (such as the range extender), removing heat from the equipment. The cooling medium then flows through the cooling system's flow channels into the radiator, where it exchanges heat with an external medium (such as air from a fan) at the radiator's cooling fins to dissipate heat.

[0070] In some specific embodiments, the range extender cabin is equipped with multiple cooling systems. The number of flow channels in the radiator corresponds to the number of cooling systems in the range extender cabin, thereby connecting to each of the cooling systems in the range extender cabin. The cooling systems may include a generator water cooling system, an engine water cooling system, an oil cooling system, or other cooling systems that achieve heat exchange through a cooling medium in the flow channels. The radiator is provided with at least one flow channel corresponding to each cooling system, and each flow channel is connected to its corresponding cooling system to direct the cooling medium flowing through the cooling system to the heat sink fins for heat exchange.

[0071] In some specific embodiments, the air inlet of the first duct is closer to the air outlet of the fan than the windward surface of the heat sink fins, so that the air entering the first duct is low-temperature gas that has not passed through the heat sink fins, which can better dissipate heat for the heat sink components of the range extender.

[0072] by Figure 2 Taking the engine head as an example, in some specific embodiments, the outlet port of the first duct also includes an engine branch port 262, which is connected to the engine's air intake to provide the engine with working gas. It will be appreciated that connecting one outlet port of the first duct to the engine's air intake simplifies the piping design. In other embodiments, a separate intake duct may be provided for the engine's air intake.

[0073] by Figure 2 Taking the nose part shown as an example, in some specific embodiments, an exhaust port 23 is provided on the surface of the range extender cabin. The area of ​​the exhaust port 23 is larger than the cross-sectional area of ​​the engine exhaust pipe 28. The engine exhaust pipe 28 passes through the exhaust port 23 to communicate with the outside world.

[0074] The surface of the range extender cabin refers to the shell surface of the aircraft excluding the windward surface of the nose. The exhaust port is provided on the surface of the range extender cabin to discharge the air in the aircraft to the outside. It is understood that the number of the exhaust ports can be one or more. The area of ​​the exhaust port is larger than the cross-sectional area of ​​the exhaust pipe, which means that the diameter of the exhaust port is larger than the outer diameter of the exhaust pipe, so that the exhaust pipe of the engine can pass through the exhaust port to discharge the exhaust gas of the engine. It is understood that setting the diameter of the exhaust port to be larger than the outer diameter of the exhaust pipe so that the exhaust pipe of the engine can pass through the exhaust port to communicate with the outside world simplifies the pipeline design while ensuring the strength of the fuselage. In other embodiments, the exhaust pipe of the engine can also be provided separately from the exhaust port.

[0075] In some specific embodiments, the area of ​​the air inlet port of the second duct is greater than or equal to the area of ​​the leeward side of the heat sink fins. It is understood that the function of the second duct is at least to discharge the air that has completed heat exchange with the heat sink fins to the outside. Therefore, the area of ​​the air inlet port of the second duct must be greater than or equal to the leeward side of the heat sink fins so that it can cover the leeward side of the heat sink fins, collect the air blown out of the leeward side of the heat sink fins after completing heat exchange with the heat sink fins, and discharge it to the outside through the second duct.

[0076] In some specific embodiments, the second pipe may be in a "Y" shape. Figure 4 A top perspective view of the nose portion of a hybrid aircraft in a specific embodiment is shown. Figure 4 The second pipe can be bifurcated into two branches at the air outlet port, namely the first air outlet port 41 and the second air outlet port 42. The first air outlet port 41 and the second air outlet port 42 of the second pipe can be respectively arranged on the two side surfaces of the head part, so as to achieve better exhaust and simplify the pipe arrangement. It can be understood that Figure 4 In the illustrated embodiment, the first outlet port 41 and the second outlet port 42 are respectively located on the left and right sides of the nose; in other embodiments, the first outlet port 41 and the second outlet port 42 may also be located on the upper and lower sides of the nose or on other surfaces of the fuselage. It will be appreciated that configuring the second duct in a "Y" shape facilitates symmetrical exhaust distribution to both sides of the nose, reducing airflow separation or vortex generation caused by exhaust from a single outlet, thereby better integrating the exhaust into the streamlines surrounding the fuselage. Furthermore, in actual use, the total cross-sectional area of ​​the two branch ducts is typically set slightly smaller than that of the main duct. This reduction in total flow area increases the flow rate, thereby accelerating exhaust.

[0077] Those skilled in the art will appreciate that hybrid aircraft typically include a fuselage compartment in addition to the range extender compartment, which often houses the battery pack and its operating components. Compared to the range extender within the range extender compartment, the battery pack and its operating components within the fuselage compartment have more stringent temperature requirements. To maintain a stable temperature within the fuselage compartment, the present invention also provides a temperature control device for a hybrid aircraft.

[0078] In some embodiments, a fuselage compartment is provided in a fuselage portion of the hybrid aircraft.

[0079] The fuselage of a hybrid aircraft refers to the area behind the nose of the aircraft and in front of the tail of the aircraft. Figure 1 In the embodiment shown, the fuselage regions of the aircraft are Zone II, Zone III, Zone IV and Zone V.

[0080] Figure 5 A perspective view of the nose section of a hybrid aircraft including fuselage heating ducts is shown. Figure 5Taking the nose portion as an example, the hybrid aircraft may also include a fuselage heating pipe 51. When the fuselage cabin temperature is too low, the fuselage heating pipe introduces the warm air after heat exchange with the range-extending cabin into the fuselage cabin to heat the fuselage cabin. Figure 5 The air inlet port of the fuselage heating duct 51 is connected to the downstream duct of the second duct 52, thereby collecting the warm air in the second duct after heat exchange with the radiator; the air outlet port of the fuselage heating duct is connected to the fuselage cabin, thereby guiding the warm air to the fuselage cabin to heat the fuselage cabin and prevent the temperature in the fuselage cabin from being too low.

[0081] In some specific embodiments, the surface of the fuselage cabin is further provided with a plurality of air inlets and a plurality of air outlets. The air inlets are provided on the side surface of the front or middle part of the fuselage cabin, and the air outlets are provided at the tail part of the fuselage cabin.

[0082] The air inlets provided on the surface of the fuselage cabin can be used to introduce a cooling medium (such as outside air) to prevent the temperature inside the fuselage cabin from being too high. The air outlets provided on the surface of the fuselage cabin can be used to discharge the warm or cold air entering the fuselage cabin out of the fuselage cabin.

[0083] When the temperature inside the fuselage cabin is low, the fuselage heating duct introduces warm air; when the temperature inside the fuselage cabin is high, the air inlet introduces outside air; the air inlet and the fuselage heating duct work together to ensure that the equipment in the fuselage cabin, such as batteries and other components, operate within the optimal operating temperature range.

[0084] In some specific embodiments, the air inlet is further provided with a waterproof component. Figure 6 The structure of the waterproof component in a specific embodiment is shown. Figure 6 The waterproof component includes a first grid 61, a deposition area 62 and a second grid 63. The first grid 61, the deposition area 62 and the second grid 63 are arranged in sequence from the surface of the fuselage cabin to the inside. The position of the second grid 63 relative to the fuselage cabin is higher than the first grid 61. The deposition area 62 at least connects the bottom of the second grid 63 and the bottom of the first grid 61.

[0085] The first grille acts as the first barrier and can be made of hard plastic, metal, or other common grille materials. The first grille can block impurities that exceed the grid spacing, such as mud, sand, fallen leaves, etc., without affecting air circulation.

[0086] The sedimentation area is a baffle connecting the bottom of the first grille and the second grille. When rainwater passes through the first grille, it is deposited in the sedimentation area, and the inclination angle of the sedimentation area is used to divert the water flow to prevent it from flowing into the fuselage compartment.

[0087] The second grille is positioned higher on the fuselage than the first, meaning it is offset from the first. The force of gravity prevents rainwater from passing through the first grille from passing through the second grille, and it settles in the settling area before flowing out of the fuselage. In some embodiments, the second grille can have a smaller grid spacing than the first grille, and can be made of other common grille materials, such as rigid plastic or metal. The second grille can block impurities, such as dust, that are larger than its grid spacing.

[0088] In some specific embodiments, the air outlet port of the fuselage heating duct may be provided with a hot air damper, and the air inlet provided on the surface of the fuselage cabin may be provided with a cold air damper, so as to respectively adjust the state and opening degree of the air outlet port and the air inlet and thereby control the amount of heating medium or cooling medium entering the fuselage cabin, so as to keep the temperature in the fuselage cabin within an ideal temperature range.

[0089] The foregoing description is provided to enable any person skilled in the art to practice the various aspects described herein. However, it should be understood that the scope of protection of the present invention is subject to the appended claims and is not limited to the specific structures and components of the above-illustrated embodiments. Those skilled in the art may make various changes and modifications to the various embodiments within the spirit and scope of the present invention, and such changes and modifications are also within the scope of protection of the present invention.

Claims

1. A hybrid aircraft, characterized in that: The hybrid aircraft is provided with a range extender cabin at the nose portion, and a range extender is provided in the range extender cabin. The hybrid aircraft includes a fan, a first pipe, a second pipe and a radiator. The windward surface of the nose portion is provided with an air inlet, the air inlet of the fan is opposite to the air inlet, the air outlet of the fan is opposite to the air inlet port of the first pipe and the windward surface of the heat dissipation fins of the radiator, the air outlet port of the first pipe is opposite to the heat dissipation component of the range extender, the leeward surface of the heat dissipation fin is opposite to the air inlet port of the second pipe, the air outlet port of the second pipe is provided on the side surface of the nose portion, and the flow channel of the radiator is connected to the flow channel of at least one cooling system configured in the range extender cabin.

2. The hybrid aircraft according to claim 1, wherein: The air inlet port of the first pipe is closer to the air outlet of the fan than the windward surface of the heat dissipation fins, and the area of ​​the air inlet port of the second pipe is greater than or equal to the area of ​​the leeward surface of the heat dissipation fins.

3. The hybrid aircraft according to claim 2, characterized in that: The air outlet end of the second pipe is in a "Y" shape, and the air outlet port of the second pipe includes a first air outlet port and a second air outlet port, and the first air outlet port and the second air outlet port are respectively arranged on the two side surfaces of the head part.

4. The hybrid aircraft according to claim 1, wherein: Several cooling systems are configured in the range-extended cabin. The number of flow channels of the radiator corresponds to the cooling systems in the range-extended cabin so as to be respectively connected to the several cooling systems in the range-extended cabin. The several cooling systems include one or a combination of any multiple of the generator water cooling system, the engine water cooling system and the oil cooling system.

5. The hybrid aircraft according to claim 1, wherein: The range extender is provided with a plurality of heat dissipation components, and the air outlet port of the first duct includes a plurality of air outlet ports corresponding one-to-one to the plurality of heat dissipation components, and the plurality of air outlet ports are respectively arranged to be opposite to the plurality of heat dissipation components.

6. The hybrid aircraft according to any one of claims 1 to 5, characterized in that: The range extender includes an engine, and the air outlet port of the first duct further includes an engine branch port, which is communicated with an air inlet of the engine.

7. The hybrid aircraft according to any one of claims 1 to 5, characterized in that: The range extender includes an engine, an exhaust port is provided on the surface of the range extender cabin, an exhaust pipe of the engine passes through the exhaust port and is connected to the outside, and an area of ​​the exhaust port is larger than a cross-sectional area of ​​the exhaust pipe.

8. The hybrid aircraft according to claim 1, wherein: The fuselage portion of the hybrid aircraft is provided with a fuselage cabin, and the hybrid aircraft further includes a fuselage heating pipe, an air inlet port of the fuselage heating pipe is connected to a downstream pipe of the second pipe, and an air outlet port of the fuselage heating pipe is connected to the fuselage cabin.

9. The hybrid aircraft according to claim 8, characterized in that: The surface of the fuselage cabin is further provided with a plurality of air inlets and a plurality of air outlets. The air inlets are arranged at the front or middle part of the fuselage cabin, and the air outlets are arranged at the tail part of the fuselage cabin.

10. The hybrid aircraft according to claim 9, characterized in that: The air inlet is arranged on the side surface of the fuselage cabin, and the air inlet is also provided with a waterproof component, which includes a first grille, a second grille and a deposition area. The first grille, the deposition area and the second grille are arranged in sequence from the surface of the fuselage cabin inward. The position of the second grille relative to the fuselage cabin is higher than that of the first grille, and the deposition area at least connects the bottom of the second grille and the bottom of the first grille.

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