Ventilation device of aircraft cockpit

Abstract

The invention discloses a ventilation device of an aircraft cockpit, relates to the technical field related to aircrafts, and is used for solving the problem that a driver feels uncomfortable due to high local flow velocity of the cockpit and heat radiation generated by a high-temperature wall surface. The aircraft cockpit comprises a heat insulation and sound insulation layer and an interior structure, the interior structure is arranged on the inner side of the heat insulation and sound insulation layer, a cavity is defined by the interior structure and the heat insulation and sound insulation layer, the cavity is provided with an air outlet side, the air outlet side is provided with an airflow outlet communicated with the interior of the cavity, and the ventilation device comprises a ventilation main pipe. The ventilation device is used for guiding airflow in an air conditioning system of the aircraft to the ventilation device; one end of the distribution pipeline is communicated with the ventilation main pipe, and the other end of the distribution pipeline is communicated with an internal space limited by the interior structure; one end of the shunting pipeline is communicated with the ventilation main pipe, and the other end of the shunting pipeline is communicated with the cavity; and the regulating valve is arranged on the shunting pipeline. The ventilation device is used for ventilation and temperature adjustment of the cockpit.

Description

Technical Field

[0001] The present application relates to the technical field related to aircraft, and in particular to a ventilation device for an aircraft cockpit. Background Art

[0002] The cockpits of current civil aircraft are small and have uneven heat loads. The cockpits usually have large temperature gradients and excessively fast local air flow, resulting in a poor pilot experience. At the same time, due to insufficient air flow in the cockpit and low heat exchange efficiency in areas with low air flow rates, the temperature adjustment rate of the cockpit is also slow. Especially during high temperature periods, the heating of the interior structure caused by ground and solar heat radiation is difficult to eliminate through traditional cockpit air supply, and the heat radiation generated by high-temperature walls will aggravate the thermal discomfort of the crew in the cockpit.

[0003] Therefore, it is urgent to design a ventilation device to solve the above-mentioned technical problems. Summary of the invention

[0004] The present application provides a ventilation device for an aircraft cockpit, which can meet existing thermal design requirements and improve thermal efficiency, accelerate the temperature adjustment rate, and at the same time will not cause a strong blowing feeling to the pilot.

[0005] To achieve the above-mentioned purpose, the present application provides a ventilation device for an aircraft cockpit, wherein the cockpit includes an interior structure and a heat-insulating and sound-insulating layer, wherein the heat-insulating and sound-insulating layer is arranged on the inner side of the interior structure and encloses the interior structure to form a cavity, wherein the cavity has an air outlet side, and the air outlet side is provided with an air flow outlet communicating with the interior of the cavity, wherein the ventilation device includes:

[0006] A ventilation main for directing the airflow in the air conditioning system of the aircraft to the ventilation device on the cockpit of the aircraft;

[0007] a distribution pipeline, one end of which is in communication with the ventilation main pipe and the other end of which is in communication with the internal space defined by the interior structure;

[0008] A shunt pipeline, one end of which is connected to the ventilation main pipe, and the other end of which is connected to the cavity;

[0009] The regulating valve is arranged on the diversion pipeline.

[0010] In some embodiments of the present application, the interior structure is used to constitute the interior space of the cockpit, and is provided with a main air supply outlet connected to the interior space and the distribution pipeline. One end of the distribution pipeline away from the ventilation main pipe extends into the cavity and is connected to the main air supply outlet. The main air supply outlet can introduce airflow into the interior space.

[0011] In some embodiments of the present application, the airflow outlet is connected to an electronic equipment compartment located below the cockpit.

[0012] In some embodiments of the present application, the number of the main air supply ports is equal to the number of the distribution pipelines, and the main air supply ports are connected to the distribution pipelines correspondingly.

[0013] In some embodiments of the present application, the interior structure has a middle reference plane, the cavity has an air inlet side, and the diversion pipe includes at least one pair, and the two connection points of each pair of the diversion pipes and the air inlet side are symmetrically arranged relative to the middle reference plane.

[0014] In some embodiments of the present application, there are multiple shunt pipelines, each of which is connected to the cavity, and each of which is provided with the regulating valve;

[0015] Wherein, the ventilation device of the aircraft cockpit also includes:

[0016] The controller is electrically connected to the regulating valve and is used to control the on and off of the regulating valve.

[0017] In some embodiments of the present application, the ventilation device of the aircraft cockpit further includes:

[0018] A control member, which is arranged on the air conditioning system operation panel of the cockpit and is electrically connected to the controller;

[0019] Wherein, when the controller receives the first flow air supply mode instruction from the control member, the control valve is controlled to close to disconnect the diversion pipeline, so that all the airflow in the ventilation main pipe flows to the distribution pipeline;

[0020] When the controller receives the second flow air supply mode instruction of the control member, the controller controls the regulating valve to open to conduct the diversion pipeline, so that part of the airflow in the ventilation main pipe flows to the distribution pipeline, and the other part of the airflow flows to the diversion pipeline;

[0021] The gas flow rate of the first flow gas supply mode entering the internal space is greater than the gas flow rate of the second flow gas supply mode entering the internal space.

[0022] In some embodiments of the present application, the cavity has an air outlet side and an air inlet side arranged opposite to each other, and a guide structure is provided in the cavity, and the guide 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.

[0023] In some embodiments of the present application, the guide structure includes a plurality of guide plates arranged 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 the gas flow channel is close to the air outlet side, and the other end is close to the air inlet side.

[0024] In some embodiments of the present application, there are multiple airflow outlets, and the flow area of ​​each of the airflow outlets is equal.

[0025] In this technical solution, part of the airflow through the ventilation main is introduced into the distribution pipeline, and the other part is introduced into the shunt pipeline, thereby realizing the shunt operation of the airflow of the ventilation main. Specifically, part of the airflow introduced through the ventilation main can be introduced into the internal space through the distribution pipeline, and the other part of the airflow introduced through the ventilation main can be selectively introduced into the cavity through the shunt pipeline by turning on and off the regulating valve. Thus, on the one hand, the gas flow rate at the port of the distribution pipeline away from the ventilation main is reduced to prevent the airflow noise caused by the excessive gas flow rate at the port. At the same time, the overall flow rate of the internal space is reduced by reducing the air supply flow entering the internal space, thereby reducing the blowing feeling of the crew. On the other hand, the airflow flowing into the cavity is made to flow through the side of the interior structure close to the cavity, realizing the convection heat exchange between the interior structure and the air inside the cavity, which is conducive to reducing the temperature of the interior structure and avoiding the problem of strong heat radiation to the driver caused by the high temperature of the wall of the interior structure under strong solar radiation on the ground, causing discomfort to the driver. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 is a schematic structural diagram of a ventilation device for an aircraft cockpit in an embodiment of the present application;

[0028] Figure 2 It is a bottom view of the ventilation device of the aircraft cockpit in the embodiment of the present application.

[0029] The main reference numerals in the drawings of this application specification are described as follows:

[0030] 1-insulation and sound insulation layer; 10-interior structure; 101-main air outlet; 11-cavity; 12-air outlet; 121-air outlet; 13-air inlet;

[0031] 2- Ventilation main;

[0032] 3- Distribution pipeline;

[0033] 4-shunt pipeline;

[0034] 5- Regulating valve. DETAILED DESCRIPTION

[0035] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0036] In the description of the present application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0037] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0038] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0039] The present application provides a ventilation device for an aircraft cockpit, which is described in detail below. It should be noted that the description order of the following embodiments does not limit the preferred order of the embodiments of the present application. In the following embodiments, the description of each embodiment has its own emphasis. For parts that are not described in detail in a certain embodiment, please refer to the relevant description of other embodiments.

[0040] The cockpit is the cabin where the pilot controls the aircraft, usually located at the front of an aircraft. Except for some early aircraft, the cockpits of most aircraft today are of enclosed design. The cockpit of an aircraft is generally equipped with various flight instruments, aircraft control systems and a driver's seat. In most civil aircraft, the cockpit and the passenger cabin are separated by a door.

[0041] The cockpit is the central component of an aircraft, and it is designed to make the pilot feel as comfortable as possible. When the aircraft is flying, the pilot will be in the driver's seat. In order to ensure that the pilot has a good experience in the cockpit, the present application designs a new ventilation device for the aircraft cockpit, which can not only prevent the air flow noise caused by excessive gas flow rate in the cockpit, but also allow the air flow to flow through the side wall of the interior structure located inside the cavity, thereby realizing convective heat exchange of the interior structure, so as to reduce the discomfort caused to the driver by the heat radiation of the interior.

[0042] Reference Figure 1 and Figure 2 The cockpit includes a heat-insulating and sound-insulating layer 1 and an interior structure 10. The interior structure 10 is arranged on the inner side of the heat-insulating and sound-insulating layer 1 and encloses therewith to form a cavity 11. The cavity 11 has an air outlet side 12. The air outlet side 12 is provided with an air flow outlet 121 connected to the inside of the cavity 11. The ventilation device of the aircraft cockpit provided in the present application includes a ventilation main pipe 2, a distribution pipeline 3, a shunt pipeline 4 and a regulating valve 5. Among them, the cavity 11 is formed by enclosing the heat-insulating and sound-insulating layer 1 and the interior structure 10. The heat-insulating and sound-insulating layer 1 is arranged on the inner side of the cockpit skin. The interior structure 10 is fixed by a bracket installed on the skin frame. One end of the distribution pipeline 3 is connected to the ventilation main pipe 2, and the other end is connected to the internal space defined by the interior structure 10. One end of the shunt pipeline 4 is connected to the ventilation main pipe 2, and the other end is connected to the cavity 11. The regulating valve 5 is arranged on the shunt pipeline 4 to control the on and off of the shunt pipeline 4.

[0043] In this technical solution, part of the airflow through the ventilation main 2 is introduced into the distribution pipeline 3, and the other part is introduced into the diversion pipeline 4, so as to realize the diversion operation of the airflow of the ventilation main 2. Specifically, part of the airflow introduced through the ventilation main 2 can be introduced into the internal space through the distribution pipeline 3, and the other part of the airflow introduced through the ventilation main 2 can be selectively introduced into the cavity 11 through the diversion pipeline 4 through the on-off of the regulating valve 5. Thus, on the one hand, the gas flow rate at the port of the distribution pipeline 3 away from the ventilation main 2 is reduced to prevent the airflow noise caused by the excessive gas flow rate at the port, and at the same time, the overall flow rate of the internal space is reduced by reducing the air supply flow entering the internal space, thereby reducing the blowing feeling of the crew. On the other hand, the airflow flowing into the cavity 11 will flow through the side of the interior structure 10 close to the cavity 11, so as to realize the convection heat exchange between the interior structure 10 and the air inside the cavity 11, which is conducive to reducing the temperature of the interior structure 10 and avoiding the problem that the high temperature of the wall of the interior structure 10 generates strong heat radiation to the driver under the condition of strong solar radiation on the ground, causing discomfort to the driver.

[0044] Based on the above embodiment, the interior structure 10 is provided with a main air supply port 101 connected to the internal space and the distribution pipeline 3. The end of the distribution pipeline 3 away from the ventilation main pipe 2 extends into the cavity 11 and is connected to the main air supply port 101. The main air supply port 101 can introduce airflow into the internal space, adjust the temperature of the internal space and realize the ventilation function of the internal space. In addition, the above arrangement can also make the part of the structure where the distribution pipeline 3 is connected to the main air supply port 101 hidden in the cavity 11, so as to ensure the aesthetics of the aircraft cockpit structure. For example, the main air supply port 101 can be provided with a grille, through which the direction of gas flow into the cockpit can be adjusted. The main air supply port 101 is arranged at the top or side of the interior structure 10.

[0045] In addition, the airflow outlet 121 is connected to the electronic equipment compartment below the cockpit, and can guide the airflow into the electronic equipment compartment to prevent the gas pressure in the cavity 11 from being too high and causing damage to the structure of the cavity 11. At the same time, guiding the airflow at the airflow outlet 121 into the electronic equipment compartment can ensure the air intake in the electronic equipment compartment, so as to effectively prevent the electronic equipment compartment from overheating and causing damage to the electronic devices in the electronic equipment compartment.

[0046] The distribution pipelines 3 in the present application have multiple roots, and the number of main air supply outlets 101 is equal to the number of distribution pipelines 3, and the two are connected one-to-one to achieve multi-point cooling or ventilation of the internal space, improve the cooling effect or ventilation effect, and help improve the driver's experience.

[0047] In some embodiments of the present application, the interior structure 10 has an intermediate reference plane X, the cavity 11 has an air inlet side 13, and the diversion pipe 4 includes at least one pair, and the two connection points of each pair of diversion pipes 4 and the air inlet side 13 are arranged symmetrically relative to the intermediate reference plane to ensure that the airflow entering the cavity 11 is relatively uniform.

[0048] In addition, the interior structure 10 is symmetrical with respect to the middle reference plane. The connection between the distribution pipeline 3 and the air inlet side is closer to the middle reference plane than the connection between the flow diversion pipeline 4 and the air inlet side. For example, there are two distribution pipelines 3 and two flow diversion pipelines 4, and the four pipelines are symmetrically and evenly arranged with respect to the middle reference plane.

[0049] In some embodiments of the present application, there are multiple shunt pipes 4, each of which is connected to the cavity 11, and each of which 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 on and off of the regulating valves 5 to achieve the regulation of the gas flow entering the shunt pipe 4. On the basis of the total air flow of the ventilation main pipe 2 remaining unchanged, the above-mentioned setting can indirectly adjust the gas flow and gas flow rate in the distribution pipe 3.

[0050] Specifically, when the controller controls all the regulating valves 5 to be closed, all the airflows in the ventilation main pipe 2 are directed to the distribution pipeline 3, and the airflow velocity at the main air supply port 101 is the largest. When the controller controls all the regulating valves 5 to be opened, part of the airflow in the ventilation main pipe 2 is directed to the distribution pipeline 3, and another part of the airflow is directed to the diversion pipeline 4, and the airflow velocity at the main air supply port 101 is the smallest. Of course, the controller can also control some regulating valves 5 to be opened and other regulating valves 5 to be closed, so that the airflow velocity at the main air supply port 101 is moderate. By way of example, the regulating valve 5 can be an electric regulating valve.

[0051] In order to realize the automatic adjustment of the above-mentioned shunt pipeline 4, the ventilation device of the above-mentioned aircraft cockpit also includes a control part. The control part is arranged on the air conditioning system operation panel of the cockpit and is electrically connected to the controller to input air supply instructions of different flow rates to the controller. In which, when the controller receives the first flow air supply mode instruction of the control part, it can control the regulating valve 5 to close to disconnect the shunt pipeline 4, so that all the airflow in the ventilation main pipe 2 flows to the distribution pipeline 3; when the controller receives the second flow air supply mode instruction of the control part, it can control the regulating valve 5 to open to conduct the shunt pipeline 4, so that part of the airflow in the ventilation main pipe 2 flows to the distribution pipeline 3, and the other part of the airflow flows to the shunt pipeline 4. In which, the gas flow rate entering the internal space in the first flow air supply mode is greater than the gas flow rate entering the internal space in the second flow air supply mode.

[0052] For example, the control member may be a control button, and when the driver presses the control button, a first flow mode instruction is sent to the controller, and when the driver presses the control button, a second flow mode instruction is sent to the controller. Alternatively, the control member may be a control button, and when the driver touches the control button, a first flow mode instruction is sent to the controller, and when the driver touches the control button again, an instruction to end the second flow mode is sent to the controller.

[0053] In some embodiments of the present application, the cavity 11 has an air outlet side 12 and an air inlet side 13 that are arranged opposite to each other, and a guide structure is provided in the cavity 11. The guide 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, thereby ensuring that the airflow flows evenly through the inner wall of the interior structure 10 located in the cavity 11, which is beneficial to further ensure the cooling effect of the interior structure 10.

[0054] For example, the guide structure includes a plurality of guide plates disposed between the heat and sound insulation layer 1 and the interior structure 10 to divide the cavity 11 into a plurality of gas flow channels, one end of the gas flow channel is close to the air outlet side 12, and the other end is close to the air inlet side 13, so as to ensure that the airflow can flow evenly through the interior structure 10 toward the inner wall of the cavity 11. The flow area of ​​the gas flow channel can also be controlled by the shape of the guide plate. A throttling element can also be provided on the gas flow channel to enhance heat exchange. For example, the throttling element is an electronic expansion valve or a capillary tube.

[0055] In order to ensure the uniformity of the airflow discharged from the air outlet side, there are multiple airflow outlets 121, and the flow area of ​​each airflow outlet 121 is equal. It should be noted that the multiple airflow outlets 121 are arranged at equal intervals, and the flow area of ​​the 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, it is indirectly ensured that the flow area of ​​each airflow outlet 121 is equal, that is, the gas flow rate is equal. For example, the shape of the above-mentioned airflow outlet 121 of the present application is circular. Of course, it can also be an elliptical shape, a waist shape, and the like.

[0056] In summary, the ventilation device provided in the present application, by adding a diversion design and setting a flow channel in the cavity 11 between the interior structure 10 and the thermal insulation and sound insulation layer 1, optimizes the original pure heat conduction in the area to convection heat exchange, significantly improves the heat exchange efficiency between the air inside the cavity 11 and the interior structure 10, and at the same time creates a low wind feeling air supply in the cabin, forming a cockpit environment with high thermal efficiency and thermal comfort.

[0057] Among them, the ventilation device supports switching between high / low flow air supply modes in the cockpit (first flow air supply mode and second flow air supply mode), which makes it convenient for the driver to increase the air supply flow to get a cooler feeling on the ground stage on hot days.

[0058] At the same time, the heat-insulating and sound-insulating layer 1 in the ventilation device is made of heat-insulating and sound-insulating materials as the name implies. A distribution pipeline 3 and a regulating valve 5 are added to the cockpit ventilation main pipe 2 to introduce part of the cockpit ventilation flow into the cavity 11, and finally enter the electronic equipment compartment through the airflow outlet 121 of the cavity 11. In addition, by adjusting the regulating valve 5, on the one hand, the large flow of cockpit ventilation can be diverted, reducing the local flow rate and the pilot's blowing feeling, and further reducing the cockpit air conditioning noise. On the other hand, by optimizing the pure heat conduction between the interior structure 10 and the heat-insulating and sound-insulating layer 1 to convection heat exchange, the temperature of the interior structure 10 can be quickly adjusted to the target temperature, avoiding the strong heat radiation to the crew due to the high temperature of the interior wall in the case of strong solar radiation on the ground, thereby causing thermal discomfort. The regulating valve 5 is linked to the cockpit control panel. When the weather is hot and the pilot wants to increase the air volume to enhance the coolness, the opening of the regulating valve 5 can be reduced to increase the flow rate of the cockpit air supply port. Under normal operating conditions, the opening of the regulating valve 5 can be increased to increase the air supply volume of the cavity 11, so as to reduce the crew members' feeling of blowing and the cockpit air supply noise, and improve the heat exchange efficiency of the cockpit.

[0059] The specific working process of the ventilation device of the present application is as follows: the cockpit air supply from the upstream enters the cockpit through the ventilation main pipe 2, the distribution pipeline 3 and the main air supply port 101, so as to realize the air supply inside the cockpit. When the regulating valve 5 is opened, a part of the air flow enters the cavity 11 through the diversion pipeline 4, and enters the electronic equipment compartment below the cockpit through the air flow outlet 121.

[0060] Among them, in order to ensure uniform airflow inside the cavity 11, there are multiple diversion pipes 4 connected to the cavity 11, and they are evenly connected to the cavity 11. Each diversion pipe 4 is provided with a regulating valve 5. The air flow outlet 121 on the air outlet side 12 of the cavity 11 is a number of circular openings of the same size, and they are evenly arranged on the wall where the air outlet side 12 is located.

[0061] When the pilot selects the cockpit high flow mode, the regulating valve 5 is actuated to cut off the connection between the shunt pipe 4 and the ventilation main pipe 2, and all the cockpit air supply directly enters the distribution pipe 3 through the ventilation main pipe 2, and is sent into the cockpit through the main air supply port 101, giving the pilot a cooler feeling when on the ground on hot days.

[0062] When the aircraft is in normal operation, or the pilot ends the cockpit high flow mode, the regulating valve 5 is actuated to connect the shunt pipe 4 with the ventilation main 2, and a preset part of the cockpit air supply is sent to the cavity 11 through the shunt pipe 4, reducing the air supply directly entering the cockpit through the main air supply port 101, reducing the blowing feeling of the crew, reducing the cockpit air supply noise, and realizing the rapid temperature adjustment of the interior structure 10, avoiding the thermal discomfort caused by the heat radiation of the interior wall to the crew under strong solar radiation, and improving the overall thermal comfort of the cockpit. The cavity 11 is connected to the electronic equipment compartment under the cockpit through the air flow outlet 121, avoiding excessive pressure in the cavity 11 and causing structural damage, while ensuring the air intake of the electronic equipment compartment to avoid overheating of the electronic equipment compartment.

[0063] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0064] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims. In addition, the specification uses specific examples to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the method and its core idea of ​​the present application. The content of this specification should not be understood as a limitation on the present application.

Claims

1. A ventilation device for an aircraft cockpit, characterized in that: The aircraft cockpit comprises a heat-insulating and sound-insulating layer (1) and an interior structure (10), wherein the interior structure (10) is arranged on the inner side of the heat-insulating and sound-insulating layer (1) and encloses the interior structure (10) to form a cavity (11), wherein the cavity (11) has an air outlet side (12), and the air outlet side (12) is provided with an air flow outlet (121) communicating with the interior of the cavity (11), wherein the ventilation device comprises: a ventilation main pipe (2) for guiding the airflow in the air conditioning system of the aircraft to the ventilation device; a distribution pipeline (3), one end of which is in communication with the ventilation main pipe (2), and the other end of which is in communication with the internal space defined by the interior structure (10); A flow-dividing pipeline (4), one end of which is in communication with the ventilation main pipe (2), and the other end of which is in communication with the cavity (11); The regulating valve (5) is arranged on the diversion pipeline (4).

2. The ventilation device for an aircraft cockpit according to claim 1, characterized in that: The interior structure (10) is provided with a main air supply port (101) connected to the internal space and the distribution pipeline (3); one end of the distribution pipeline (3) away from the ventilation main pipe (2) extends into the cavity (11) and is connected to the main air supply port (101); the main air supply port (101) is capable of directing airflow into the internal space.

3. The ventilation device for an aircraft cockpit according to claim 2, characterized in that: The airflow outlet (121) is in communication with an electronic equipment compartment located below the cockpit.

4. The ventilation device for an aircraft cockpit according to claim 2, characterized in that: The number of the main air supply ports (101) is equal to the number of the distribution pipelines (3), and the main air supply ports (101) are connected to the distribution pipelines (3) correspondingly.

5. The ventilation device for an aircraft cockpit according to claim 1, characterized in that: The interior structure (10) has a middle reference plane, the cavity (11) has an air inlet side (13), and the flow diversion pipeline (4) includes at least one pair, and the two connection points of each pair of the flow diversion pipeline (4) and the air inlet side (13) are symmetrically arranged relative to the middle reference plane.

6. The ventilation device for an aircraft cockpit according to any one of claims 1 to 5, characterized in that: There are a plurality of the shunt pipelines (4), each of the shunt pipelines (4) is in communication with the cavity (11), and each of the shunt pipelines (4) is provided with the regulating valve (5); Wherein, the ventilation device of the aircraft cockpit also includes: The controller is electrically connected to all the regulating valves (5) and is used to control the on and off of the regulating valves (5).

7. The ventilation device for an aircraft cockpit according to claim 6, characterized in that: Also includes: A control member, which is arranged on the air conditioning system operation panel of the cockpit and is electrically connected to the controller; When the controller receives the first flow air supply mode instruction from the control element, it controls the regulating valve (5) to close to disconnect the flow diversion pipeline (4), so that all the airflow in the ventilation main pipe (2) flows to the distribution pipeline (3); When the controller receives the second flow air supply mode instruction from the control element, the controller controls the regulating valve (5) to open to conduct the diversion pipeline (4), so that part of the airflow in the ventilation main pipe (2) flows to the distribution pipeline (3), and the other part of the airflow flows to the diversion pipeline (4); The gas flow rate of the first flow gas supply mode entering the internal space is greater than the gas flow rate of the second flow gas supply mode entering the internal space.

8. The ventilation device for an aircraft cockpit according to claim 1, characterized in that: The cavity (11) has an air outlet side (12) and an air inlet side (13) arranged opposite to each other, and a flow guiding structure is provided in the cavity (11), wherein the flow guiding structure is used to guide the airflow entering from the air inlet side (13) to the airflow outlet (121) of the air outlet side (12) and discharge it.

9. The ventilation device for an aircraft cockpit according to claim 8, characterized in that: The guide structure comprises a plurality of guide plates arranged between the heat-insulating and sound-insulating layer (1) and the interior structure (10) so as to divide the cavity (11) into a plurality of gas flow channels, one end of the gas flow channel being close to the air outlet side (12) and the other end being close to the air inlet side (13).

10. The ventilation device for an aircraft cockpit according to claim 1, characterized in that: There are a plurality of air flow outlets (121), and the flow area of ​​each of the air flow outlets (121) is equal.

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