Aircraft cabin air conditioning system flow channel, aircraft cabin air conditioning system and aircraft

Abstract

The present invention discloses an aircraft cabin air conditioning system flow channel, an aircraft cabin air conditioning system, and an aircraft, and relates to the field of aircraft, and is used to optimize the structure of the aircraft cabin air conditioning system flow channel. The aircraft cabin air conditioning system flow channel includes a first flow channel and a second flow channel. The first flow channel includes a first air inlet and a first air outlet. The second flow channel and the first flow channel are independent of each other, and the second flow channel is fixed to the first flow channel. The second flow channel includes a second air inlet and a second air outlet, the first air inlet and the second air inlet are arranged adjacent to each other, and the first air outlet and the second air outlet are arranged adjacent to each other. In the above technical solution, the two flow channels are relatively independent, so that the structure of the aircraft cabin air conditioning system flow channel is more flexible, and there is no pressure loss due to mixed airflow, and there is no need to use a fan with high delivery capacity to compensate for the pressure loss, which makes the fan selection design more flexible.

Description

Technical Field

[0001] The present invention relates to the field of aircraft, and in particular to a flow channel of an aircraft cabin air conditioning system, an aircraft cabin air conditioning system, and an aircraft. Background Art

[0002] The onboard air conditioning system consists of a main air conditioning system and an auxiliary refrigeration and air conditioning system. The main air conditioning system regulates the temperature and humidity of external ram air. Specifically, the main air conditioning system draws in ram air from the aircraft's engines, expands it, and regulates it through the environmental control system to achieve the desired temperature. The auxiliary refrigeration and air conditioning system regulates the air inside the aircraft. The two systems generate two different air streams, which are conditioned to produce air with different temperatures, humidities, and flow rates. These two air streams are then mixed and delivered to the aircraft's passenger cabin, cargo hold, and associated areas requiring air conditioning.

[0003] The inventors have discovered that there are at least the following problems in the prior art: In the related art, the two streams will cause huge pressure loss at the mixing point, which makes the airflow encounter too much resistance during transportation and makes transportation difficult. Summary of the Invention

[0004] The present invention provides an aircraft cabin air conditioning system flow passage, an aircraft cabin air conditioning system, and an aircraft, for optimizing the structure of the aircraft cabin air conditioning system flow passage.

[0005] An embodiment of the present invention provides a flow channel of an aircraft cabin air conditioning system, comprising:

[0006] a first flow channel, comprising a first air inlet and a first air outlet; and

[0007] The second flow channel, the flow channel of the second flow channel is independent of the flow channel of the first flow channel; the second flow channel is fixed together with the first flow channel; the second flow channel includes a second air inlet and a second air outlet, the first air inlet and the second air inlet are arranged adjacent to each other, and the first air outlet and the second air outlet are arranged adjacent to each other.

[0008] In some embodiments, there is one first air inlet, and the number of the first air outlets is two or more, and the first air outlets are dispersedly arranged.

[0009] In some embodiments, there is one second air inlet, and the number of the second air outlets is two or more, and the second air outlets are dispersedly arranged.

[0010] In some embodiments, the first flow channel includes a first air inlet duct, and the second flow channel includes a second air inlet duct; the air inlet end of the first air inlet duct and the air inlet end of the second air inlet duct are separated, and the air outlet end of the first air inlet duct and the air outlet end of the second air inlet duct are fixed together and are not fluidically connected.

[0011] In some embodiments, the aircraft cabin air conditioning system flow channel further comprises:

[0012] A connecting pipe is provided with a first partition plate inside, and the first partition plate extends along the axial direction of the connecting pipe to divide the internal space of the connecting pipe into a relatively independent first pipe section and a second pipe section; the first pipe section is part of the first flow channel, and the second pipe section is part of the second flow channel; wherein, the first pipe section is connected to the first air inlet pipe, and the second pipe section is connected to the second air inlet pipe.

[0013] In some embodiments, the connecting pipe further comprises:

[0014] The first branch pipe assembly includes at least one first branch pipe, and each first branch pipe is connected to a different circumferential and / or axial position of the first pipe segment.

[0015] In some embodiments, the connecting pipe further comprises:

[0016] The second branch pipe assembly includes at least one second branch pipe, and each second branch pipe is connected to a different circumferential and / or axial position of the second pipe segment.

[0017] In some embodiments, the connecting pipe further comprises:

[0018] The first diverter plate is arranged inside the first pipe segment and extends along the axis of the first pipe segment to divert the airflow in the first pipe segment and guide it to the first branch pipes located at different circumferential positions of the first pipe segment.

[0019] In some embodiments, the connecting pipe further comprises:

[0020] The second diverter plate is arranged inside the second pipe segment and extends along the axis of the second pipe segment to divert the airflow in the second pipe segment and guide it to the second branch pipes located at different circumferential positions of the second pipe segment.

[0021] In some embodiments, the air outlet end of the first air inlet duct is provided with a first guide slope; and / or the air outlet end of the second air inlet duct is provided with a second guide slope.

[0022] In some embodiments, the first flow channel further comprises:

[0023] a first tail pipe assembly, arranged downstream of the first flow channel and provided with at least one first air outlet; and / or

[0024] The second tail pipe assembly is arranged downstream of the second flow channel and is provided with at least one second air outlet.

[0025] In some embodiments, the first tail pipe assembly includes:

[0026] a first tail pipe, connected to the first pipe section; and

[0027] The third branch pipe is connected to the first tail pipe, and the outlet of the third branch pipe serves as the first air outlet.

[0028] In some embodiments, the third branch pipe includes at least one, and each of the third branch pipes is distributed at different circumferential and / or axial positions of the first tail pipe.

[0029] In some embodiments, the second tailpipe assembly comprises:

[0030] a second tail pipe, communicating with the second pipe section; and

[0031] The fourth branch pipe is connected to the second tail pipe, and the outlet of the fourth branch pipe serves as the second air outlet.

[0032] In some embodiments, the fourth branch pipe includes at least one, and each of the fourth branch pipes is distributed at different circumferential and / or axial positions of the second tail pipe.

[0033] In some embodiments, the first tail pipe of the first tail pipe assembly and the second tail pipe of the second tail pipe assembly are fixedly connected.

[0034] An embodiment of the present invention further provides an aircraft cabin air conditioning system, comprising the aircraft cabin air conditioning system flow channel provided by any technical solution of the present invention.

[0035] An embodiment of the present invention further provides an aircraft, comprising the aircraft cabin air conditioning system provided by any technical solution of the present invention.

[0036] The aircraft cabin air conditioning system flow channel provided by the above technical solution has a relatively independent first flow channel and a second flow channel. The airflow in the first flow channel and the airflow in the second air channel will not mix, thus avoiding the huge pressure loss caused by the collision, mixing, and interweaving of two airflows with different flow rates (flow velocities). Moreover, the two airflows with different temperatures and humidity will not mix, so water mist, liquid water condensation, or ice and snow will not form. The above structure not only reduces the wind resistance of the airflow in the first flow channel and the second air channel, but also eliminates the need to design additional water diversion or defrosting and de-icing devices for the first and second flow channels. It also makes the aircraft cabin air conditioning system flow channel compact and lightweight, thereby increasing the effective use space of the aircraft. The structure of the aircraft cabin air conditioning system flow channel is relatively flexible, and there is no pressure loss caused by mixed airflow, nor is there a need to use a high-capacity fan to compensate for the pressure loss, making the fan selection design more flexible. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The drawings described herein are used to provide a further understanding of the present invention and constitute a part of this application. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0038] Figure 1 A schematic diagram of the three-dimensional structure of a flow channel in an aircraft cabin air conditioning system according to an embodiment of the present invention;

[0039] Figure 2 A partial cross-sectional schematic diagram of a first air inlet duct and a second air inlet duct of an aircraft cabin air conditioning system flow channel according to an embodiment of the present invention;

[0040] Figure 3 for Figure 2 AA cross-sectional view of ;

[0041] Figure 4 for Figure 2 BB cross-sectional diagram. DETAILED DESCRIPTION

[0042] The following combination Figures 1 to 4 The technical solution provided by the present invention is described in more detail.

[0043] See also Figures 1 to 4An embodiment of the present invention provides an aircraft cabin air conditioning system flow channel for delivering airflow to a passenger cabin, a cargo hold, and other parts of a manned aircraft. The aircraft cabin air conditioning system flow channel includes a first flow channel 1 and a second flow channel 2. The first flow channel 1 includes a first air inlet 11 and a first air outlet 12. The flow channel of the second flow channel 2 is independent of the flow channel of the first flow channel 1. The second flow channel 2 is fixed to the first flow channel 1. The second flow channel 2 includes a second air inlet 21 and a second air outlet 22, and the first air inlet 11 and the second air inlet 21 are arranged adjacent to each other, and the first air outlet 12 and the second air outlet 22 are arranged adjacent to each other.

[0044] From the perspective of airflow, the first and second flow channels 1 and 2 are completely independent, and the fluids in the first and second flow channels 1 and 2 do not contact each other. This means that airflow does not flow from the first flow channel 1 to the second flow channel 2, nor does it flow from the second flow channel 2 to the first flow channel 1. Physically, the first and second flow channels 1 and 2 are integral, fixedly connected to form a single unit. Specifically, this can be achieved through integral molding or by bolts. The first flow channel 1 serves as the flow channel for transporting air for the environmental control system, while the second flow channel 2 serves as the flow channel for transporting air for the auxiliary refrigeration system.

[0045] By preventing direct contact between two airflows of different velocities and flow rates, this technical solution avoids uneven mixing and pressure loss, particularly when the airflows differ significantly. This significantly reduces the pressure differential in the duct system, lowering the static pressure and power requirements of the fan, reducing fan costs, and significantly lowering energy consumption.

[0046] See also Figure 1 In some embodiments, there is one first air inlet 11 and two or more first air outlets 12, and the first air outlets 12 are dispersedly arranged. The first air outlets 12 are positioned to correspond to the desired air outlet locations, and the number of first air outlets 12 is set based on the desired air outlet locations.

[0047] See also Figure 1 In some embodiments, there is one second air inlet 21 and two or more second air outlets 22, and each second air outlet 22 is dispersedly arranged. The second air outlets 22 are positioned to correspond to the desired air outlet locations, and the number of second air outlets 22 is set based on the desired air outlet locations.

[0048] In some embodiments, the first flow channel 1 includes a first air inlet duct 13, and the second flow channel 2 includes a second air inlet duct 23. The air inlet end of the first air inlet duct 13 and the air inlet end of the second air inlet duct 23 are separate, and the air outlet end of the first air inlet duct 13 and the air outlet end of the second air inlet duct 23 are fixed together and not in fluid communication. The overall shape formed by the first air inlet duct 13 and the second air inlet duct 23 is generally V-shaped. The air inlet ends of the first air inlet duct 13 and the second air inlet duct 23 are separate, and the tail ends are fixed together.

[0049] See also Figure 1 and Figure 2 In some embodiments, the outlet end of the first air inlet pipe 13 is provided with a first guide slope 131. The first guide slope 131 is used to guide the airflow into the first flow channel 1. And / or, the outlet end of the second air inlet pipe 23 is provided with a second guide slope 132. The second guide slope 132 is used to guide the airflow into the second flow channel 2.

[0050] See also Figure 1 and Figure 2 In some embodiments, the flow path of the aircraft cabin air conditioning system further includes a connecting pipe 3. A partition plate 4 is disposed within the connecting pipe 3. The partition plate 4 extends along the axis of the connecting pipe 3 to divide the internal space of the connecting pipe 3 into a first pipe section 31 and a second pipe section 32, which are relatively independent. The first pipe section 31 is part of the first flow channel 1, and the second pipe section 32 is part of the second flow channel 2. The first pipe section 31 is connected to the first air inlet duct 13, and the second pipe section 32 is connected to the second air inlet duct 23.

[0051] The windward surface of the partition plate 4 can adopt a V-shaped surface with a smooth transition, and the tip faces the windward surface, so as to minimize the influence of the partition plate 4 on the air duct resistance.

[0052] The connecting pipe 3 can be designed as a standard part, and the number of sections and the length of the connecting pipe 3 can be selected as needed. Each connecting pipe has a smooth transition at the joint to allow the air flow to flow smoothly.

[0053] See also Figure 1 and Figure 2 In some embodiments, the connecting pipe 3 further includes a first branch pipe assembly 33, the first branch pipe assembly 33 includes at least one first branch pipe 331, and each first branch pipe 331 is connected to a different circumferential and / or axial position of the first pipe section 31. Each section of the connecting pipe 3 includes, for example, four first branch pipes 331. Figure 1In the orientation shown, two of the four first branch pipes 331 are allocated on each side. The connecting pipe 3 is a standard component. This allows for the desired length of connecting pipe 3 to be assembled from multiple sections of connecting pipe 3 as needed. The flow area of ​​the first pipe section 31 is greater than the flow area of ​​a single first branch pipe 331. The relationship between the two depends on the nacelle length, the nacelle spatial distribution, and the fan static pressure. Optionally, the flow area of ​​the first pipe section 31 can be equal to the sum of the flow areas of all first branch pipes 331 in that section of connecting pipe 3 to increase the airflow velocity.

[0054] See also Figure 1 and Figure 2 In some embodiments, the connecting pipe 3 further includes a second branch pipe assembly 34, which includes at least one second branch pipe 341. Each second branch pipe 341 is connected to a different position of the second pipe section 32 in the circumferential direction and / or axial direction. The first branch pipe assembly 33 and the second branch pipe assembly 34 are fixedly assembled to form a whole. Specifically, the first branch pipe assembly 33 and the second branch pipe assembly 34 are arranged at intervals. Figure 1 On the M side shown, the pipes are arranged downwards in the order of the first branch pipe 331, the second branch pipe 341, the first branch pipe 331, the second branch pipe 341, and so on. Figure 1 The N side shown in the figure also has the same arrangement. The flow area of ​​the second pipe segment 32 is larger than the flow area of ​​a single second branch pipe 341. The relationship between the two depends on the nacelle length, the nacelle spatial distribution, and the fan static pressure. Optionally, the flow area of ​​the second pipe segment 32 can be equal to the sum of the flow areas of all second branches 341 in the connecting pipe 3 to increase the air outlet velocity.

[0055] See also Figure 1 and Figure 2 In some embodiments, the connecting pipe 3 further includes a first diverter plate 35. The first diverter plate 35 is disposed within the first pipe segment 31 and extends along the axis of the first pipe segment 31 to divert the airflow within the first pipe segment 31 and direct it to the first branch pipes 331 located at different circumferential positions of the first pipe segment 31. The first diverter plate 35 is relatively short and does not divide the first pipe segment 31 into two independent flow channels. The first diverter plate 35 diverts the airflow within the first pipe segment 31, directing the airflow to the first branch pipes 331 on the M and N sides.

[0056] See also Figure 1 and Figure 3 The first diverter plate 35 is positioned so that the first pipe section 31 of the connecting pipe 3 is symmetrically located on both sides of M and N. The windward surface of the first diverter plate 35 can be V-shaped with a smooth transition, and the tip is facing the windward surface, thereby minimizing the impact of the first diverter plate 35 on the air duct resistance.

[0057] See also Figure 1 and Figure 3In some embodiments, the connecting pipe 3 further includes a second diverter plate 36, which is disposed inside the second pipe section 32 and extends along the axis of the second pipe section 32 to divert the airflow in the second pipe section 32 and direct it to the second branch pipes 341 located at different circumferential positions of the second pipe section 32. The height of the second diverter plate 36 is relatively short, and there is no need to divide the second pipe section 32 into two independent flow channels. The second diverter plate 36 serves to divert the airflow in the second pipe section 32, so that the airflow can be diverted to the second branch pipes 341 on the M side and the N side. The second diverter plate 36 is disposed in a position such that the structure of the second pipe section 32 of the connecting pipe 3 on both sides A and B is symmetrical.

[0058] The windward surface of the second splitter plate 36 may adopt a V-shaped surface with a smooth transition, and the tip thereof may face the windward surface, thereby minimizing the effect of the second splitter plate 36 on the air duct resistance.

[0059] See also Figure 3 The partition plate 4, the first diverter plate 35, and the second diverter plate 36 form a cross-shaped structure as a whole.

[0060] See also Figure 1 and Figure 2 In some embodiments, the first flow channel 1 further includes a first tail pipe assembly 5 and / or a second tail pipe assembly 6. In some embodiments, the first tail pipe assembly 5 and the second tail pipe assembly 6 are provided simultaneously as an example. Of course, only one of them can also be provided as needed. The first tail pipe assembly 5 is arranged downstream of the first flow channel 1 and is provided with at least one first air outlet 12. The first tail pipe assembly 5 is part of the first flow channel 1. The second tail pipe assembly 6 is arranged downstream of the second flow channel 2 and is provided with at least one second air outlet 22. The second tail pipe assembly 6 is part of the second flow channel 2.

[0061] See also Figure 1 In some embodiments, the first tail pipe assembly 5 includes a first tail pipe 51 and a third branch pipe 52. The first tail pipe 51 is connected to the first pipe section 31. The third branch pipe 52 is connected to the first tail pipe 51, and the outlet of the third branch pipe 52 serves as the first air outlet 12. The first tail pipe 51 is a closed-end pipe, and air flows out of the first tail pipe assembly 5 only through the third branch pipe 52.

[0062] The number and placement of the third branch pipes 52 are determined based on the desired air outlet locations. In some embodiments, there is at least one third branch pipe 52, and each third branch pipe 52 is distributed at different circumferential and / or axial locations on the first tail pipe 51. Both the first branch pipe 331 and the third branch pipe 52 serve as the first air outlet 12 of the first flow channel 1, and their number is determined by the desired number of air outlet locations in the first flow channel 1. The number of third branch pipes 52 is relatively fixed, as the number of first branch pipes 331 is determined by the desired number of sections in the connecting pipe 3.

[0063] See also Figures 1 to 4 The flow areas of the first tail pipe 51 and the first pipe section 31 are the same, and there is no need to use a conical surface or other structural transition between the two, thereby increasing the reliability of the air duct system and reducing the cost of the air duct system.

[0064] A smooth transition is achieved between the first air inlet duct 13 and the first pipe section 31, as well as between the first pipe section 31 and the first tail pipe 51, minimizing their impact on wind resistance. The connections between the air ducts are smooth and reliable, and there are no bosses or other obstructions within the air duct that could impede air flow. The first flow channel 1 is symmetrical with respect to the first diverter plate 35.

[0065] See also Figure 1 In some embodiments, the second tail pipe assembly 6 includes a second tail pipe 61 and a fourth branch pipe 62. The second tail pipe 61 is connected to the second pipe section 32. The fourth branch pipe 62 is connected to the second tail pipe 61, and the outlet of the fourth branch pipe 62 serves as the second air outlet 22. The second branch pipe 341 and the fourth branch pipe 62 both serve as the second air outlet 22 of the second flow channel 2. The number of the second branch pipe 341 and the fourth branch pipe 62 is determined by the number of required air outlet positions of the second flow channel 2. The number of fourth branch pipes 62 is relatively fixed, while the number of second branch pipes 341 is determined by the required number of sections of the connecting pipe 3.

[0066] See also Figures 1 to 4 The flow areas of the second tail pipe 61 and the second pipe section 32 are the same, and there is no need to use a conical surface or other structural transition between the two, thereby increasing the reliability of the air duct system and reducing the cost of the air duct system.

[0067] The transition between the second air inlet duct 23 and the second duct section 32 is smooth, as is the transition between the second duct section 32 and the second tail pipe 61, minimizing their impact on wind resistance. The connections between the ducts are smooth and reliable, and there are no bosses or other obstructions within the air duct that could impede air flow. The second flow channel 2 is symmetrical with respect to the second diverter plate 36.

[0068] See also Figure 1 and Figure 2 In some embodiments, the fourth branch pipe 62 includes at least one, and each fourth branch pipe 62 is distributed at different circumferential and / or axial positions of the second tail pipe 61. Figure 1 In the illustrated embodiment, there are four fourth branch pipes 62 , two of which are installed at different circumferential positions corresponding to the same axial position, and the other two fourth branch pipes 62 are installed at different circumferential positions corresponding to another axial position.

[0069] See also Figure 1In some embodiments, the first tail pipe 51 of the first tail pipe assembly 5 and the second tail pipe 61 of the second tail pipe assembly 6 are fixedly connected. The first tail pipe 51 and the second tail pipe 61 both have a semi-cylindrical structure and are fixed together to form a cylindrical structure.

[0070] In some embodiments, the exterior of the aircraft cabin air conditioning system flow channel is insulated with thermal insulation materials, and the partition plate 4 is insulated with thermal insulation materials. Treatment methods include but are not limited to sponging, applying an insulation layer, etc.

[0071] An embodiment of the present invention further provides an aircraft cabin air conditioning system, comprising the aircraft cabin air conditioning system flow channel provided by any technical solution of the present invention.

[0072] Fresh air conditioned by the aircraft's environmental control system remains in the upper level of the cabin air conditioning system's flow path, namely, first flow path 1. Fresh air is then delivered to various locations in the cabin. Recirculated air conditioned by the aircraft's auxiliary cooling and air conditioning system remains in the lower level of the cabin air conditioning system's flow path, namely, second flow path 2. The airflows in first flow path 1 and second flow path 2 are completely independent and do not cross-flow.

[0073] The aircraft cabin air conditioning system provided in an embodiment of the present invention, because it includes the aircraft cabin air conditioning system flow passage provided by the above-described technical solution, can also achieve the various beneficial technical effects described above, and indirectly reduces the structural size of the aircraft cabin air conditioning system flow passage, reduces the weight of the aircraft cabin air conditioning system flow passage, and reduces the energy consumption of the aircraft cabin air conditioning system flow passage.

[0074] An embodiment of the present invention further provides an aircraft, comprising the aircraft cabin air conditioning system provided by any technical solution of the present invention.

[0075] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the protection content of the present invention.

[0076] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims

1. An aircraft, characterized in that: The invention comprises an aircraft environmental control system, an aircraft auxiliary refrigeration and air conditioning system, an aircraft cabin air conditioning system, and a cabin; the aircraft cabin air conditioning system comprises an aircraft cabin air conditioning system flow channel, and the aircraft cabin air conditioning system flow channel comprises: A first flow channel (1) comprising a first air inlet (11) and a first air outlet (12); and a second flow channel (2), wherein the flow channel of the second flow channel (2) is independent of the flow channel of the first flow channel (1); the second flow channel (2) is fixed to the first flow channel (1); the second flow channel (2) comprises a second air inlet (21) and a second air outlet (22), the first air inlet (11) and the second air inlet (21) are arranged adjacent to each other, and the first air outlet (12) and the second air outlet (22) are arranged adjacent to each other; There is no need to additionally design water receiving and diversion devices or defrosting and deicing devices for the first flow channel (1) and the second flow channel (2); The fresh air conditioned by the aircraft environmental control system is always located in the first flow channel (1), and then the fresh air is delivered to the cabin; the circulating air conditioned by the aircraft auxiliary refrigeration and air conditioning system is always located in the second flow channel (2), and then the circulating air is delivered to the cabin.

2. The aircraft according to claim 1, characterized in that There is one first air inlet (11), and the number of the first air outlets (12) is two or more, and the first air outlets (12) are dispersedly arranged.

3. The aircraft according to claim 1, characterized in that There is one second air inlet (21), and the number of the second air outlets (22) is two or more, and the second air outlets (22) are dispersedly arranged.

4. The aircraft according to claim 1, characterized in that The first flow channel (1) includes a first air inlet pipe (13), and the second flow channel (2) includes a second air inlet pipe (23); the air inlet end of the first air inlet pipe (13) and the air inlet end of the second air inlet pipe (23) are separated, and the air outlet end of the first air inlet pipe (13) and the air outlet end of the second air inlet pipe (23) are fixed together and are not fluidically connected.

5. The aircraft according to claim 4, characterized in that The aircraft cabin air conditioning system flow channel further comprises: A connecting pipe (3) is provided with a partition plate (4) therein, wherein the partition plate (4) extends along the axial direction of the connecting pipe (3) to divide the internal space of the connecting pipe (3) into a relatively independent first pipe section (31) and a second pipe section (32); the first pipe section (31) is a part of the first flow channel (1), and the second pipe section (32) is a part of the second flow channel (2); wherein the first pipe section (31) is connected to the first air inlet pipe (13), and the second pipe section (32) is connected to the second air inlet pipe (23).

6. The aircraft according to claim 5, characterized in that The connecting pipe (3) further comprises: The first branch pipe assembly (33) comprises at least one first branch pipe (331), each first branch pipe (331) being connected to the first pipe section (31) at different circumferential and / or axial positions.

7. The aircraft according to claim 5, characterized in that The connecting pipe (3) further comprises: The second branch pipe assembly (34) comprises at least one second branch pipe (341), each second branch pipe (341) being connected to a different circumferential and / or axial position of the second pipe section (32).

8. The aircraft according to claim 5, characterized in that The connecting pipe (3) further comprises: A first splitter plate (35) is disposed inside the first pipe section (31), and the first splitter plate (35) extends along the axis of the first pipe section (31) to split the airflow in the first pipe section (31) and guide it to first branch pipes (331) located at different circumferential positions of the first pipe section (31).

9. The aircraft according to claim 5, characterized in that The connecting pipe (3) further comprises: A second splitter plate (36) is disposed inside the second pipe section (32), and the second splitter plate (36) extends along the axis of the second pipe section (32) to split the airflow in the second pipe section (32) and guide it to second branch pipes (341) located at different circumferential positions of the second pipe section (32).

10. The aircraft according to claim 4, characterized in that The air outlet end of the first air inlet pipe (13) is provided with a first guiding inclined surface (131); and / or the air outlet end of the second air inlet pipe (23) is provided with a second guiding inclined surface (132).

11. The aircraft according to claim 5, characterized in that The aircraft cabin air conditioning system flow channel further comprises: a first tail pipe assembly (5), arranged downstream of the first flow channel (1) and provided with at least one first air outlet (12); and / or The second tail pipe assembly (6) is arranged downstream of the second flow channel (2) and is provided with at least one second air outlet (22).

12. The aircraft according to claim 11, characterized in that The first tail pipe assembly (5) comprises: a first tail pipe (51) communicating with the first pipe section (31); and The third branch pipe (52) is connected to the first tail pipe (51), and the outlet of the third branch pipe (52) serves as the first air outlet (12).

13. The aircraft according to claim 12, characterized in that The third branch pipe (52) includes at least one, and each of the third branch pipes (52) is distributed at different circumferential and / or axial positions of the first tail pipe (51).

14. The aircraft according to claim 11, characterized in that The second tail pipe assembly (6) comprises: a second tail pipe (61) communicating with the second pipe section (32); and The fourth branch pipe (62) is connected to the second tail pipe (61), and the outlet of the fourth branch pipe (62) serves as the second air outlet (22).

15. The aircraft according to claim 14, characterized in that The fourth branch pipe (62) includes at least one, and each of the fourth branch pipes (62) is distributed at different circumferential and / or axial positions of the second tail pipe (61).

16. The aircraft according to claim 11, characterized in that The first tail pipe (51) of the first tail pipe assembly (5) and the second tail pipe (61) of the second tail pipe assembly (6) are fixedly connected.

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