Ventilation device for aircraft cockpit

Abstract

A ventilation device for an aircraft cockpit. The aircraft cockpit comprises a heat-insulating and sound-insulating layer (1) and an interior trim structure (10); the interior trim structure (10) is arranged on the inner side of the heat-insulating and sound-insulating layer (1), and the interior trim structure (10) and the heat-insulating and sound-insulating layer (1) define a cavity (11); the cavity (11) has an air outlet side (12); and the air outlet side (12) is provided with airflow outlets (121) communicated with the interior of the cavity (11). The ventilation device comprises a main ventilation pipe (2) used for guiding airflow from an air conditioning system of an aircraft to the ventilation device; distribution pipes (3) each having one end communicated with the main ventilation pipe (2) and the other end communicated with an internal space defined by the interior trim structure (10); diversion pipes (4) each having one end communicated with the main ventilation pipe (2) and the other end communicated with the cavity (11); and regulation valves (5) provided on the diversion pipes (4).

Description

Aircraft cockpit ventilation system

[0001] This disclosure claims priority to Chinese Patent Application No. 202411467512.9, filed on October 21, 2024, entitled "Ventilation Device for Aircraft Cockpit", the entire contents of which are incorporated herein by reference. Technical Field

[0002] This disclosure relates to, but is not limited to, the field of aircraft-related technologies, such as a ventilation device for an aircraft cockpit. Background Technology

[0003] The cockpits of current commercial airliners are cramped and subject to uneven heat loads, often resulting in large temperature gradients and excessively rapid airflow in some areas, leading to a poor pilot experience. Furthermore, insufficient airflow within the cockpit results in low heat exchange efficiency in areas with lower airflow velocity, causing a slow temperature regulation rate. Particularly during periods of high temperatures, the heat generated by ground and solar radiation on the interior structure is difficult to eliminate using traditional cockpit air supply systems, and the heat radiation from the hot walls exacerbates the thermal discomfort experienced by the crew.

[0004] Therefore, there is an urgent need to design a ventilation device to solve the above-mentioned technical problems. Summary of the Invention

[0005] The following is an overview of the subject matter described in detail herein. This overview is not intended to limit the scope of the claims.

[0006] This disclosure provides a ventilation device for an aircraft cockpit.

[0007] To achieve the above objectives, the present disclosure provides a ventilation device for an aircraft cockpit, wherein the cockpit includes an interior structure and a heat-insulating and sound-insulating layer, the interior structure being disposed inside the heat-insulating and sound-insulating layer and enclosing it to form a cavity, the cavity having an air outlet side, the air outlet side being provided with an airflow outlet communicating with the interior of the cavity, wherein the ventilation device includes:

[0008] A ventilation duct is used to direct airflow from the aircraft's air conditioning system to the ventilation system in the aircraft cockpit.

[0009] The distribution pipe has one end connected to the main ventilation pipe and the other end connected to the interior space defined by the interior structure;

[0010] A branch pipe, one end of which is connected to the main ventilation pipe, and the other end of which is connected to the cavity; and

[0011] A regulating valve is located on the diversion pipeline.

[0012] In some embodiments of this disclosure, the interior structure is used to form the interior space of the cockpit, and is provided with a main air outlet communicating with the interior space and the distribution pipe. The end of the distribution pipe away from the main ventilation pipe extends into the cavity and communicates with the main air outlet. The main air outlet is capable of guiding airflow into the interior space.

[0013] In some embodiments of this disclosure, the airflow outlet is connected to an electronics compartment located below the cockpit.

[0014] In some embodiments of this disclosure, the number of main air outlets is equal to the number of distribution pipes, and the main air outlets are connected to the distribution pipes accordingly.

[0015] In some embodiments of this disclosure, the interior structure has a central reference plane, the cavity has an air intake side, and the diversion pipes include at least one pair, with the two connections of each pair of diversion pipes to the air intake side arranged symmetrically with respect to the central reference plane.

[0016] In some embodiments of this disclosure, the diversion pipe has multiple branches, each branch pipe is connected to the cavity, and each branch pipe is provided with the regulating valve;

[0017] The ventilation system for the aircraft cockpit also includes:

[0018] The controller is electrically connected to the regulating valve and is used to control the opening and closing of the regulating valve.

[0019] In some embodiments of this disclosure, the ventilation system for the aircraft cockpit further includes:

[0020] The control unit is located on the air conditioning system control panel in the cockpit and is electrically connected to the controller;

[0021] When the controller receives the first flow air supply mode command from the control element, it controls the regulating valve to close to disconnect the diversion pipeline, so that all airflow in the main ventilation pipe flows to the distribution pipeline;

[0022] When the controller receives the second flow air supply mode command from the control element, it controls the regulating valve to open to open the diversion pipeline, so that part of the airflow in the main ventilation pipe flows to the distribution pipeline and the other part of the airflow flows to the diversion pipeline;

[0023] Wherein, the gas flow rate entering the internal space in the first flow gas supply mode is greater than the gas flow rate entering the internal space in the second flow gas supply mode.

[0024] In some embodiments of this disclosure, the cavity has an air outlet side and an air inlet side arranged opposite to each other, and a flow guiding structure is provided in the cavity for guiding the airflow entering from the air inlet side to the airflow outlet on the air outlet side and discharging it.

[0025] In some embodiments of this disclosure, the airflow guiding structure includes a plurality of airflow guiding plates disposed between the thermal insulation and sound insulation layer and the interior structure to divide the cavity into a plurality of gas flow channels, one end of which is close to the air outlet side and the other end is close to the air inlet side.

[0026] In some embodiments of this disclosure, the airflow outlets are multiple, and the flow area of ​​each airflow outlet is equal.

[0027] In this technical solution, a portion of the airflow from the main ventilation duct is directed to the distribution duct, while another portion is directed to the diversion duct, thus achieving airflow diversion from the main ventilation duct. Specifically, a portion of the airflow introduced through the main ventilation duct can be directed into the interior space via the distribution duct, while the remaining portion can be selectively directed into the cavity via the diversion duct through the regulating valve. This reduces, on the one hand, the gas velocity at the end of the distribution duct away from the main ventilation duct, preventing excessive airflow noise at that end. Simultaneously, reducing the airflow into the interior space lowers the overall airflow velocity, reducing the draft felt by the crew. On the other hand, the airflow into the cavity flows through the interior structure near the cavity, achieving convective heat exchange between the interior structure and the air inside the cavity. This helps lower the temperature of the interior structure and avoids the problem of intense heat radiation from the interior structure walls causing discomfort to the driver under strong solar radiation.

[0028] After reading and understanding the accompanying diagrams and detailed descriptions, the other aspects can be understood. Attached Figure Description

[0029] To more clearly illustrate the technical solutions in the embodiments of this disclosure, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this disclosure. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 is a schematic diagram of the ventilation device in the aircraft cockpit according to an embodiment of this disclosure;

[0031] Figure 2 is a bottom view of the ventilation system in the cockpit of an aircraft according to an embodiment of this disclosure.

[0032] The main reference numerals in the accompanying drawings of this disclosure are explained as follows:

[0033] 1-Insulation and soundproofing layer; 10-Interior structure; 101-Main air outlet; 11-Cavity; 12-Air outlet side; 121-Airflow outlet; 13-Air inlet side;

[0034] 2-Ventilation main pipe;

[0035] 3-Distribution piping;

[0036] 4-Diversion piping;

[0037] 5-Regulating valve. Embodiments of the present invention

[0038] The technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this disclosure, and not all embodiments. Based on the embodiments of this disclosure, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this disclosure.

[0039] In the description of this disclosure, it should be understood that the terms “center,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” and “outer,” etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this disclosure and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure.

[0040] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this disclosure, unless otherwise stated, "a plurality of" means two or more.

[0041] In the description of this disclosure, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, a direct connection, or an indirect connection through an intermediate medium; or they can refer to the internal connection between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure based on the specific circumstances.

[0042] This disclosure provides a ventilation device for an aircraft cockpit, which will be described in detail below. It should be noted that the order of description of the following embodiments is not intended to limit the preferred order of the embodiments of this disclosure. Furthermore, in the following embodiments, the descriptions of each embodiment have their own emphasis; parts not described in detail in a certain embodiment can be referred to in the relevant descriptions of other embodiments.

[0043] The cockpit is the cabin where pilots control the aircraft, typically located at the front. Except for some earlier aircraft, most modern aircraft have enclosed cockpits. The cockpit generally houses various flight instruments, aircraft control systems, and the pilot's seat. In most commercial airliners, the cockpit and passenger cabin are separated by a door.

[0044] The cockpit is the most important component of an aircraft, designed to provide pilots with maximum comfort during flight. The pilot is positioned in the cockpit. To ensure a better experience for the pilot, this disclosure presents a novel ventilation system for the aircraft cockpit. This system not only prevents excessive airflow noise caused by high air velocity within the cockpit but also allows airflow to pass through one side wall of the interior structure located inside the cavity, achieving convective heat transfer and reducing discomfort caused by interior heat radiation to the pilot.

[0045] Referring to Figures 1 and 2, the cockpit includes a thermal insulation and soundproof layer 1 and an interior structure 10. The interior structure 10 is located inside the thermal insulation and soundproof layer 1 and encloses it to form a cavity 11. The cavity 11 has an air outlet side 12, which has an air outlet 121 communicating with the interior of the cavity 11. The ventilation device for the aircraft cockpit provided in this disclosure includes a main ventilation pipe 2, a distribution pipe 3, a diversion pipe 4, and a regulating valve 5. The cavity 11 is formed by the thermal insulation and soundproof layer 1 and the interior structure 10. The thermal insulation and soundproof layer 1 is located inside the cockpit skin, and the interior structure 10 is fixed by brackets mounted on the skin frame. One end of the distribution pipe 3 is connected to the main ventilation pipe 2, and the other end is connected to the interior space defined by the interior structure 10. One end of the diversion pipe 4 is connected to the main ventilation pipe 2, and the other end is connected to the cavity 11. The regulating valve 5 is located on the diversion pipe 4 and is used to control the on / off state of the diversion pipe 4.

[0046] In this technical solution, a portion of the airflow from the ventilation main duct 2 is directed to the distribution pipe 3, and another portion is directed to the diversion pipe 4, thus achieving the diversion operation of the airflow from the ventilation main duct 2. Specifically, a portion of the airflow introduced through the ventilation main duct 2 can be directed into the internal space via the distribution pipe 3, while another portion of the airflow introduced through the ventilation main duct 2 can selectively enter the cavity 11 via the diversion pipe 4 through the on / off control of the regulating valve 5. This reduces the gas velocity at the port of the distribution pipe 3 away from the ventilation main duct 2, preventing excessive airflow noise caused by excessive gas velocity at that port. Simultaneously, by reducing the air supply flow into the internal space, the overall flow velocity of the internal space is reduced, thus reducing the draft sensation for the crew. Furthermore, the airflow flowing into the cavity 11 flows through the side of the interior structure 10 closest to the cavity 11, achieving convective heat exchange between the interior structure 10 and the air inside the cavity 11. This helps reduce the temperature of the interior structure 10, preventing the driver from experiencing discomfort due to intense heat radiation from the high-temperature walls of the interior structure 10 under strong solar radiation.

[0047] Based on the above embodiments, the interior structure 10 is provided with a main air outlet 101 that communicates with the interior space and the distribution pipe 3. The end of the distribution pipe 3 away from the main ventilation pipe 2 extends into the cavity 11 and communicates with the main air outlet 101. The main air outlet 101 can guide airflow into the interior space, regulate the temperature of the interior space, and achieve the ventilation function of the interior space. Furthermore, the above arrangement also allows the portion of the structure connecting the distribution pipe 3 and the main air outlet 101 to be hidden within the cavity 11, ensuring the aesthetics of the aircraft cockpit structure. For example, the main air outlet 101 may be provided with a grille, which can adjust the direction of airflow into the cockpit. The main air outlet 101 is located on the top or side of the interior structure 10.

[0048] Furthermore, the airflow outlet 121 is connected to the electronics compartment located below the cockpit, enabling airflow to be directed into the electronics compartment to prevent excessive gas pressure within the cavity 11, which could damage the structure of the cavity 11. Simultaneously, directing airflow from the airflow outlet 121 into the electronics compartment ensures adequate air intake, effectively preventing overheating and damage to the electronic components within the electronics compartment.

[0049] The distribution pipe 3 in this disclosure has multiple pipes, and the number of main air outlets 101 is equal to the number of distribution pipes 3, and the two are connected one-to-one to achieve multi-point cooling or ventilation of the interior space, improve the cooling or ventilation effect, and help improve the driver's experience.

[0050] In some embodiments of this disclosure, the interior structure 10 has a central reference plane X, the cavity 11 has an air inlet side 13, and the diversion pipes 4 include at least one pair. The two connections of each pair of diversion pipes 4 and the air inlet side 13 are symmetrically arranged relative to the central reference plane to ensure that the airflow entering the cavity 11 is relatively uniform.

[0051] Furthermore, the interior structure 10 is symmetrical with respect to the intermediate reference plane. The connection between the distribution pipe 3 and the air intake side is closer to the intermediate reference plane than the connection between the diversion pipe 4 and the air intake side. For example, there are two distribution pipes 3 and two diversion pipes 4, and the four pipes are symmetrically and evenly arranged with respect to the intermediate reference plane. Of course, in some embodiments not shown in the accompanying drawings, the connection between the diversion pipe 4 and the air intake side may be closer to the intermediate reference plane than the connection between the distribution pipe 3 and the air intake side. Alternatively, in other embodiments not shown in the accompanying drawings, there are multiple diversion pipes 4 and distribution pipes 3 located on the same side of the intermediate reference plane; at least one diversion pipe 4 is provided on at least one side of the distribution pipe 3 along a direction perpendicular to the intermediate reference plane.

[0052] In some embodiments of this disclosure, the diversion pipe 4 has multiple branches, each branch pipe 4 is connected to the cavity 11, and each branch pipe 4 is provided with a regulating valve 5. The ventilation device of the aircraft cockpit also includes a controller, which is electrically connected to all the regulating valves 5 and is used to control the opening and closing of the regulating valves 5 to regulate the gas flow rate entering the branch pipe 4. With the total gas flow rate of the ventilation main pipe 2 remaining unchanged, the above arrangement can indirectly regulate the gas flow rate and gas velocity in the distribution pipe 3.

[0053] Specifically, when the controller closes all regulating valves 5, all airflow from the main ventilation duct 2 is directed to the distribution duct 3, resulting in the highest airflow velocity at the main air outlet 101. When the controller opens all regulating valves 5, some airflow from the main ventilation duct 2 is directed to the distribution duct 3, and the remaining airflow is directed to the branch duct 4, resulting in the lowest airflow velocity at the main air outlet 101. Alternatively, the controller can open some regulating valves 5 and close others, achieving a moderate airflow velocity at the main air outlet 101. For example, the regulating valve 5 can be an electrically operated regulating valve.

[0054] To achieve automated adjustment of the aforementioned diversion duct 4, the ventilation system in the aircraft cockpit also includes a control unit. The control unit is located on the air conditioning system control panel in the cockpit and is electrically connected to the controller to input air supply commands of different flow rates. When the controller receives a first flow rate air supply mode command from the control unit, it can control the regulating valve 5 to close, disconnecting the diversion duct 4, so that all airflow in the main ventilation duct 2 flows to the distribution duct 3. When the controller receives a second flow rate air supply mode command from the control unit, it can control the regulating valve 5 to open, opening the diversion duct 4, so that part of the airflow in the main ventilation duct 2 flows to the distribution duct 3, and the other part flows to the diversion duct 4. The gas flow rate entering the internal space under the first flow rate air supply mode is greater than that under the second flow rate air supply mode. The control unit can be set with multiple levels, controlling the flow rate entering the distribution duct 3 and the diversion duct 4 by controlling the number and degree of opening of the regulating valve 5.

[0055] For example, the aforementioned control component can be a control button. When the driver presses the control button, a first flow mode command is sent to the controller; when the driver releases the control button, a second flow mode command is sent to the controller. Alternatively, the aforementioned control component can be a control button. When the driver touches the control button, a first flow mode command is sent to the controller; when the driver touches the control button again, a command to end the second flow mode is sent to the controller.

[0056] In some embodiments of this disclosure, the cavity 11 has an air outlet side 12 and an air inlet side 13 arranged opposite to each other. A flow guiding structure is provided in the cavity 11. The flow guiding structure is used to guide the airflow entering from the air inlet side 13 to the air outlet 121 of the air outlet side 12 and discharge it, so as to ensure that the airflow flows evenly over the side wall of the interior structure 10 facing the cavity 11, which is beneficial to further ensure the cooling effect of the interior structure 10.

[0057] For example, the airflow guiding structure includes multiple guide plates disposed between the thermal insulation and soundproof layer 1 and the interior structure 10 to divide the cavity 11 into multiple gas flow channels. One end of each gas flow channel is close to the air outlet side 12, and the other end is close to the air inlet side 13, ensuring that the airflow can flow evenly across the side wall of the interior structure 10 facing the cavity 11. The flow area of ​​the gas flow channels can also be controlled by the shape of the guide plates. Furthermore, throttling elements can be provided on the gas flow channels to enhance heat exchange. For example, the throttling element is an electronic expansion valve or a capillary tube.

[0058] To ensure the uniformity of the airflow discharged from the outlet side, there are multiple airflow outlets 121, and each airflow outlet 121 has an equal flow area. It should be noted that the multiple airflow outlets 121 are arranged at equal intervals, and the flow area of ​​each airflow outlet 121 can be limited by the size of the airflow outlet. Alternatively, the flow area of ​​the airflow outlet 121 can be achieved by a resistance module provided at the airflow outlet 121. For example, by controlling the resistance of the resistance module, the equal flow area of ​​each airflow outlet 121 is indirectly ensured, i.e., the equal gas flow rate. For example, the airflow outlet 121 described in this disclosure is circular in shape. Of course, it can also be elliptical, waist-shaped, or other shapes.

[0059] In summary, the ventilation device provided in this disclosure, by adding a diversion design and setting a flow channel in the cavity 11 between the interior structure 10 and the heat insulation and sound insulation layer 1, optimizes the original pure heat conduction in this area into convective heat exchange, significantly improving the heat exchange efficiency between the air inside the cavity 11 and the interior structure 10, while creating a low-wind-feel air supply in the cabin, forming a cockpit environment with high thermal efficiency and thermal comfort.

[0060] The ventilation system supports switching between high and low flow air supply modes in the cockpit (first flow air supply mode and second flow air supply mode), which allows the driver to increase the air supply flow to achieve a cooler feeling on hot ground.

[0061] Meanwhile, the thermal insulation and soundproofing layer 1 in this ventilation system, as its name suggests, is made of thermal insulation and soundproofing material. A distribution pipe 3 and a regulating valve 5 are added to the main ventilation pipe 2 of the cockpit to introduce a portion of the cockpit ventilation flow into the cavity 11, which ultimately enters the electronics bay through the airflow outlet 121 of the cavity 11. Furthermore, by adjusting the regulating valve 5, the large flow of cockpit ventilation can be diverted, reducing local flow velocity and the pilot's feeling of being blown by the wind, and further reducing cockpit air conditioning noise. On the other hand, by optimizing the pure thermal conduction between the interior structure 10 and the thermal insulation and soundproofing layer 1 into convective heat transfer, the temperature of the interior structure 10 can be quickly adjusted to the target temperature, avoiding the intense heat radiation from the high temperature of the interior walls to the crew, thus preventing thermal discomfort caused by strong solar radiation from the interior walls under strong ground radiation. The regulating valve 5 is linked to the cockpit control panel. When the weather is hot and the pilot wants to increase the airflow to improve the cooling effect, the opening of the regulating valve 5 can be reduced to increase the airflow in the cockpit air outlet. Under normal operating conditions, the opening of the regulating valve 5 can be increased to increase the air supply to the cavity 11, thereby reducing the crew's feeling of being blown by the wind and the noise of the cockpit air supply, and improving the cockpit heat exchange efficiency.

[0062] The specific working process of the ventilation device disclosed herein is as follows: Air supplied from the upstream cockpit enters the cockpit through the ventilation main pipe 2, distribution pipe 3, and main air outlet 101, thereby supplying air to the cockpit. When the regulating valve 5 is opened, a portion of the airflow enters the cavity 11 through the diversion pipe 4 and enters the electronic equipment compartment below the cockpit through the airflow outlet 121.

[0063] In order to ensure uniform airflow inside the cavity 11, there are multiple branch pipes 4 connected to the cavity 11, which are evenly connected to the cavity 11. Each branch pipe 4 is equipped with a regulating valve 5. The airflow outlet 121 of the air outlet side 12 of the cavity 11 consists of several circular openings of the same size, which are evenly arranged on the wall surface where the air outlet side 12 is located.

[0064] When the pilot selects the high-flow mode in the cockpit, the regulating valve 5 shuts off the connection between the diversion pipe 4 and the main ventilation pipe 2. All the air supply to the cockpit enters the distribution pipe 3 directly through the main ventilation pipe 2 and is delivered into the cockpit through the main air outlet 101, giving the pilot a cooler feeling on hot ground.

[0065] When the aircraft is operating normally, or when the pilot exits the high-flow cockpit mode, the regulating valve 5 actuates, connecting the diversion pipe 4 to the main ventilation pipe 2. A pre-set portion of the cockpit air supply is then delivered through the diversion pipe 4 into the cavity 11, reducing the amount of air directly entering the cockpit through the main air vent 101. This reduces the crew's draft and cockpit noise, while simultaneously enabling rapid temperature regulation of the interior structure 10. This avoids thermal discomfort caused by heat radiation from the interior walls under strong solar radiation, thus improving overall cockpit thermal comfort. The cavity 11 is connected to the electronics bay below the cockpit via the airflow outlet 121, preventing excessive pressure in the cavity 11 from causing structural damage, while ensuring sufficient air intake for the electronics bay to prevent overheating.

[0066] In the description of this specification, specific features, structures, materials, or characteristics may be combined in any suitable manner in one or more embodiments or examples.

[0067] The above description is merely a specific embodiment of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims. Furthermore, specific examples have been used in the specification to illustrate the principles and implementation methods of this disclosure. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this disclosure, and the content of this specification should not be construed as a limitation of this disclosure.

Claims

1. A ventilation device for an aircraft cockpit, the aircraft cockpit comprising a heat-insulating and sound-insulating layer and an interior structure, the interior structure being disposed inside the heat-insulating and sound-insulating layer and enclosing it to form a cavity, the cavity having an air outlet side, the air outlet side being provided with an airflow outlet communicating with the interior of the cavity, wherein, The ventilation device includes: A ventilation duct is used to direct airflow from the aircraft's air conditioning system to the ventilation device. The distribution pipe has one end connected to the main ventilation pipe and the other end connected to the interior space defined by the interior structure; A branch pipe, one end of which is connected to the main ventilation pipe, and the other end of which is connected to the cavity; and A regulating valve is located on the diversion pipeline.

2. The ventilation system for the aircraft cockpit according to claim 1, wherein, The interior structure is provided with a main air outlet that communicates with the interior space and the distribution pipe. The end of the distribution pipe away from the main ventilation pipe extends into the cavity and communicates with the main air outlet. The main air outlet can guide airflow into the interior space.

3. The ventilation system for the aircraft cockpit according to claim 2, wherein, The airflow outlet is connected to the electronics compartment located below the cockpit.

4. The ventilation system for the aircraft cockpit according to claim 2, wherein, The number of main air outlets is equal to the number of distribution pipes, and the main air outlets are connected to the corresponding distribution pipes.

5. The ventilation system for the aircraft cockpit according to claim 1, wherein, The interior structure has a central reference plane, the cavity has an air intake side, and the diversion pipes include at least one pair, with the two connections of each pair of diversion pipes to the air intake side arranged symmetrically with respect to the central reference plane.

6. The ventilation system for an aircraft cockpit according to any one of claims 1 to 5, wherein, The diversion pipeline has multiple branches, each of which is connected to the cavity, and each of the diversion pipelines is equipped with the regulating valve; The ventilation system for the aircraft cockpit also includes: The controller is electrically connected to all of the regulating valves and is used to control the on / off state of the regulating valves.

7. The ventilation system for an aircraft cockpit according to claim 6, wherein, Also includes: The control unit is located on the air conditioning system control panel in the cockpit and is electrically connected to the controller; When the controller receives the first flow air supply mode command from the control element, it controls the regulating valve to close to disconnect the diversion pipeline, so that all airflow in the main ventilation pipe flows to the distribution pipeline; When the controller receives the second flow air supply mode command from the control element, it controls the regulating valve to open to open the diversion pipeline, so that part of the airflow in the main ventilation pipe flows to the distribution pipeline and the other part of the airflow flows to the diversion pipeline; Wherein, the gas flow rate entering the internal space in the first flow gas supply mode is greater than the gas flow rate entering the internal space in the second flow gas supply mode.

8. The ventilation system for an aircraft cockpit according to claim 1, wherein, The cavity has an air outlet side and an air inlet side arranged opposite to each other. A flow guiding structure is provided inside the cavity. The flow guiding structure is used to guide the airflow entering from the air inlet side to the airflow outlet on the air outlet side and discharge it.

9. The ventilation system for an aircraft cockpit according to claim 8, wherein, The airflow guiding structure includes multiple airflow guiding plates disposed between the heat insulation and sound insulation layer and the interior structure to divide the cavity into multiple gas flow channels, with one end of the gas flow channel close to the air outlet side and the other end close to the air inlet side.

10. The ventilation system for an aircraft cockpit according to claim 1, wherein, The airflow outlet has multiple outlets, and the flow area of ​​each outlet is equal.

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