Instrument panel assembly and aircraft

Abstract

The application relates to an instrument panel assembly and an airplane. The instrument panel assembly is applied to the airplane, and the instrument panel assembly comprises an instrument frame, an instrument panel module, and an air outlet module. The air outlet module comprises a damper control system, an air inlet channel, a first air outlet channel and a second air outlet channel. The damper control system is installed on the instrument frame. The air inlet channel, the first air outlet channel and the second air outlet channel are connected with the damper control system. The air inlet channel is connected with an air conditioner module and communicates with the air conditioner module. The damper control system is used for distributing the air volume input by the air inlet channel to the first air outlet channel and / or the second air outlet channel. The first air outlet channel is used for blowing air to the front windshield glass. The second air outlet channel is used for blowing air to the cabin. The instrument panel assembly and the airplane provided by the application are convenient to assemble and have high assembly efficiency.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, specifically to an instrument panel assembly and an aircraft. Background Technology

[0002] With the development of society and the economy and the improvement of living standards, airplanes have become an indispensable tool for people. Airplanes are not only widely used in civil transportation and scientific research, but they are also important weapons in modern warfare. In addition to passenger and transport aircraft, civil aircraft include agricultural aircraft, forestry aircraft, aerial surveying aircraft, medical evacuation aircraft, sightseeing aircraft, business jets, sports aircraft, experimental research aircraft, meteorological aircraft, aerobatic display aircraft, and law enforcement aircraft, among others.

[0003] Traditional aircraft assembly is time-consuming, labor-intensive, and inefficient, all of which hinder efficient aircraft production. Therefore, providing an aircraft that is easy to assemble and has low assembly efficiency has become an urgent problem to solve. Utility Model Content

[0004] Therefore, it is necessary to provide an instrument panel assembly and aircraft that is easy to assemble and has high assembly efficiency to address the above problems.

[0005] An instrument panel assembly is applied to an aircraft, the aircraft including a fuselage assembly, the fuselage assembly including a fuselage frame, a windshield, and an air conditioning module, the fuselage frame housing a cabin, the windshield and the air conditioning module being mounted on the fuselage frame, characterized in that the instrument panel assembly is disposed within the cabin, and the instrument panel assembly includes:

[0006] Instrument frame;

[0007] Instrument panel module;

[0008] The air outlet module includes a damper control system, an air inlet duct, a first air outlet duct, and a second air outlet duct. The damper control system is installed on the instrument frame. The air inlet duct, the first air outlet duct, and the second air outlet duct are all connected to the damper control system. The air inlet duct is connected to and communicates with the air conditioning module. The damper control system is used to distribute the air volume input from the air inlet duct to the first air outlet duct and / or the second air outlet duct. The first air outlet duct is used to blow air onto the windshield, and the second air outlet duct is used to blow air into the cabin.

[0009] In some embodiments, there are multiple air inlets, all of which are connected between the air conditioning module and the damper control system.

[0010] In some embodiments, an assembly space is defined within the instrument frame, and the instrument panel module, the damper control system, the first air outlet duct, and the second air outlet duct are all installed within the assembly space;

[0011] The instrument frame has an air inlet, an instrument display port, a first air outlet, and a second air outlet, all of which are connected to the assembly space. The first air outlet is located on the top surface of the instrument frame and faces the windshield. The instrument display port and the second air outlet are located on the operating end face of the instrument frame facing the driver's seat in the engine compartment. The air inlet is located on the left and / or right side of the instrument frame, which are adjacent to both the top surface and the operating end face.

[0012] The air inlet duct passes through the air inlet opening, the instrument panel module is exposed through the instrument display port, the air outlet end of the first air outlet duct is connected to the first air outlet, and the air outlet end of the second air outlet duct is connected to the second air outlet.

[0013] In some embodiments, the left and right sides of the instrument frame are respectively provided with maintenance ports communicating with the assembly space.

[0014] In some embodiments, the instrument panel assembly further includes a service cover, which corresponds one-to-one with the service port, covers the service port, and is detachably connected to the instrument frame;

[0015] The instrument panel assembly also includes an instrument frame skin, which covers the outer surface of the instrument frame and avoids the air inlet, the instrument display port, the first air outlet, the second air outlet, and the maintenance cover.

[0016] In some embodiments, multiple connecting frames are provided on both the left and right sides of the instrument frame. All the connecting frames on the same side are spaced apart along the forward direction of the aircraft, and the connecting frames are detachably connected to both the instrument frame and the fuselage frame.

[0017] An aircraft, the aircraft comprising:

[0018] The fuselage assembly includes a fuselage frame, a windshield, and an air conditioning module. A cabin is located within the fuselage frame. The windshield is mounted at the front end of the fuselage frame along the forward direction of the aircraft. The air conditioning module is located at the rear end of the fuselage frame along the forward direction of the aircraft. The assembly also includes an instrument panel assembly as described in any of the above embodiments. The instrument panel assembly is located within the cabin and at the front end of the fuselage frame along the forward direction of the aircraft. The instrument panel frame is detachably connected to the fuselage frame. One end of the air intake duct away from the air vent control system is connected to and communicates with the air conditioning module. A first air outlet duct blows air onto the windshield, and a second air outlet duct blows air into the cabin.

[0019] In some embodiments, a first connecting frame, a second connecting frame, and a third connecting frame are provided on both the left and right sides of the instrument frame, and the first connecting frame, the second connecting frame, and the third connecting frame located on the same side are arranged at intervals along the forward direction;

[0020] The fuselage frame includes a cabin floor and cabin side panels surrounding the cabin floor. The first connecting frame is used to connect the cabin side panels and the instrument frame. The second connecting frame and the third connecting frame are both used to connect the cabin floor and the instrument frame.

[0021] In some embodiments, the first connecting frame includes a first box and a second box arranged side by side and connected together. The openings of the first box and the second box are both located away from the cabin floor. The first box and the second box are both located between the fuselage frame and the instrument frame. The side wall of the first box is detachably connected to the instrument frame, and the side wall of the second box is detachably connected to the cabin side panel.

[0022] In some embodiments, both the second connecting frame and the third connecting frame include a first plate, a second plate, and a reinforcing rib. The first plate is detachably connected to the instrument frame. The second plate is disposed at the bottom of the first plate and is bent away from the instrument frame in the left-right direction of the aircraft relative to the first plate. The second plate is detachably connected to the cabin floor. The reinforcing rib is connected between the first plate and the second plate.

[0023] Compared with the prior art, this application has the following beneficial effects:

[0024] The aforementioned instrument panel assembly and aircraft integrate the instrument panel module and air outlet module in the instrument panel assembly. After the instrument frame is installed on the aircraft, the instrument panel module and air outlet module can be installed in an integrated manner on the aircraft. This design makes aircraft assembly time-saving and labor-saving, and greatly improves the assembly efficiency of the aircraft. Attached Figure Description

[0025] Figure 1 This is a perspective view of an instrument panel assembly according to an embodiment of this application;

[0026] Figure 2 for Figure 1 The diagram shows the overall structure of the instrument panel assembly after removing the air intake duct.

[0027] Figure 3 for Figure 1 A schematic diagram of the air outlet module in the instrument panel assembly shown;

[0028] Figure 4 for Figure 1 The image shown is an exploded view of the instrument panel assembly after the air intake duct has been removed.

[0029] Figure 5 This is a schematic diagram of the connection between the instrument panel assembly and the fuselage assembly in an aircraft according to an embodiment of this application, after the air intake duct has been removed.

[0030] Figure 6 for Figure 5 The image shown is an exploded view of the aircraft.

[0031] Figure 7 for Figure 5 The diagram shown is a structural schematic of the first connecting frame of the instrument panel assembly in the embodiment shown.

[0032] Figure 8 for Figure 5 The illustrated embodiment shows a schematic diagram of the third connecting frame of the instrument panel assembly.

[0033] Icon labels:

[0034] 100. Airplane;

[0035] 10. Instrument panel assembly; 20. Airframe assembly;

[0036] 11. Instrument frame; 111. Assembly space; 112. Instrument display port; 113. First air outlet; 114. Second air outlet; 115. Top surface; 116. Operating end face; 117. Left side; 118. Right side; 119. Maintenance port; 12. Air outlet module; 121. Air damper control system; 122. Air inlet duct; 123. First air outlet duct; 124. Second air outlet duct; 13. Instrument frame skin; 14. Maintenance cover; 15. Connecting frame; 151. First connecting frame; 1511. First housing; 1512. Second housing; 152. Second connecting frame; 153. Third connecting frame; 1531. First plate; 1532. Second plate; 1533. Reinforcing rib plate;

[0037] 21. Fuselage frame; 211. Cabin; 212. Cabin floor; 213. Cabin side panels;

[0038] X represents the forward direction; Y represents the left and right direction. Detailed Implementation

[0039] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0040] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0041] Furthermore, 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 at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0042] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0043] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0044] It should be noted that when an element is referred to as being "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is considered to be "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0045] With the development of society and the economy and the improvement of living standards, airplanes have become an indispensable tool for people. Airplanes are not only widely used in civil transportation and scientific research, but they are also important weapons in modern warfare. In addition to passenger and transport aircraft, civil aircraft include agricultural aircraft, forestry aircraft, aerial surveying aircraft, medical evacuation aircraft, sightseeing aircraft, business jets, sports aircraft, experimental research aircraft, meteorological aircraft, aerobatic display aircraft, and law enforcement aircraft, among others.

[0046] Traditional aircraft assembly is time-consuming, labor-intensive, and inefficient, all of which hinder efficient aircraft production. Therefore, providing an aircraft that is easy to assemble and has low assembly efficiency has become an urgent problem to be solved.

[0047] Please refer to the following: Figures 1 to 6 In view of this, the applicant, after in-depth research, designed an instrument panel assembly 10, which is applied to an aircraft 100. The aircraft 100 also includes a fuselage assembly 20, which includes a fuselage frame 21, a windshield, and an air conditioning module. A cabin 211 is located within the fuselage frame 21. The windshield and air conditioning module are both mounted on the fuselage frame 21. The instrument panel assembly 10 is located within the cabin 211, and the instrument panel assembly 10 includes an instrument frame 11, an instrument panel module, and an air outlet module 12 (e.g., ...). Figure 1 (As shown by the blue line in the middle), the air outlet module 12 includes a damper control system 121, an air inlet duct 122, a first air outlet duct 123, and a second air outlet duct 124. The damper control system 121 is installed on the instrument frame 11. The air inlet duct 122, the first air outlet duct 123, and the second air outlet duct 124 are all connected to the damper control system 121. The air inlet duct 122 is connected to and communicates with the air conditioning module. The damper control system 121 is used to distribute the air volume input from the air inlet duct 122 to the first air outlet duct 123 and / or the second air outlet duct 124. The first air outlet duct 123 is used to blow air towards the windshield, and the second air outlet duct 124 is used to blow air towards the cabin 211.

[0048] Specifically, the fuselage frame 21 forms the overall frame of the aircraft 100, primarily serving a supporting and mounting function. The fuselage frame 21 contains a cabin 211, within which the pilot's seat and passenger seats are arranged sequentially from front to back. It is worth noting that the terms "front" and "rear" in this application refer to the forward and rearward positions of the aircraft 100 when it is moving forward, respectively; the terms "left" and "right" refer to the left and right positions of the aircraft 100 when it is moving forward, respectively; and the terms "top" and "bottom" refer to the upper and lower positions of the aircraft 100 when it is moving forward, respectively.

[0049] Windshield installation

[0050] Located at the front of the cockpit and facing it, the windshield not only serves to block the wind but also provides the pilot with a wide field of vision while flying the aircraft. The air conditioning module is located at the rear of the fuselage frame 21, outside the cabin 211, and is used to cool or heat the cabin 211.

[0051] The instrument panel assembly 10 includes an instrument frame 11, an instrument panel module, and an air outlet module 12. The instrument frame 11 is used to mount other components within the instrument panel assembly 10 and provides structural support for these components. The instrument panel module provides the pilot with flight parameters, navigation parameters, and information on the aircraft's system status. The air outlet module 12 includes a damper control system 121, an air inlet duct 122, a first air outlet duct 123, and a second air outlet duct 124. The air inlet duct 122 connects the damper control system 121 and the air conditioning module. The damper control system 121 includes a damper controller and a damper. The damper controller controls the opening and closing of the damper, thereby adjusting the airflow direction and volume of the air conditioning module. It can be understood that the damper controller controls the damper to output the cold or warm air volume from the air conditioning module through the air inlet duct 122 and then through the first air outlet duct 123 and / or the second air outlet duct 124, thus adjusting the airflow direction of the air conditioning system. The damper control system is a conventional technology in this field and will not be described in detail here.

[0052] When the damper controller controls the first air outlet 123 to blow air towards the windshield, it can defog the windshield to provide better clarity. When the damper controller controls the second air outlet 124 to blow air into the cabin 211, it can regulate the temperature inside the cabin 211 to meet the needs of the pilot and passengers.

[0053] In this application, by modularizing the instrument panel module and the air outlet module 12 within the instrument panel assembly 10, it is advantageous to facilitate the individual assembly of the instrument panel module and the air outlet module 12 onto the instrument frame 11, and to enable independent maintenance of the instrument panel module and the air outlet module 12. This simplifies the maintenance process for each module and improves the installation flexibility and efficiency. Furthermore, by integrating the instrument panel module and the air outlet module 12 into the instrument panel assembly 10, the instrument panel assembly 10 allows for integrated installation of the instrument panel module and the air outlet module 12 on the aircraft 100 after the instrument frame 11 is installed. This design saves time and effort in assembling the aircraft 100, significantly improving its assembly efficiency.

[0054] Please see Figure 1 and Figure 3 In some embodiments, there are multiple air inlets 122, all connected between the air conditioning module and the damper control system 121. Multiple air inlets 122 can simultaneously deliver either cold or warm air from the air conditioning module to the air outlet module 12, thereby meeting the large air volume output requirements of the air outlet module 12. Furthermore, compared to a single air inlet 122, multiple air inlets 122 can distribute the large air volume, thus preventing damage from excessive air pressure in a single air inlet 122 and extending the service life of the air outlet module 12.

[0055] In some embodiments, there are multiple second air outlet ducts 124, all of which are connected and communicate with the damper control system 121. Multiple second air outlet ducts 124 can simultaneously output the cold air volume or the warm air volume output by the air conditioning module, thereby meeting the needs of rapid cooling or heating.

[0056] Please see Figures 1 to 4 In some embodiments, an assembly space 111 is defined within the instrument frame 11, and the instrument panel module, the damper control system 121, the first air outlet 123 and the second air outlet 124 are all installed within the assembly space 111.

[0057] The instrument panel frame 11 has an air inlet, an instrument display port 112, a first air outlet 113, and a second air outlet 114, all of which are connected to the assembly space 111. The first air outlet 113 is located on the top surface 115 of the instrument panel frame 11 and faces the windshield. The instrument display port 112 and the second air outlet 114 are located on the operating end face 116 of the instrument panel frame 11 facing the driver's seat inside the engine compartment 211. The air inlet is located on the left side 117 and / or right side 118 of the instrument panel frame 11, which are adjacent to both the top surface 115 and the operating end face 116. An air inlet duct 122 passes through the air inlet, and the instrument panel module is exposed through the instrument display port 112. The air outlet end of the first air outlet duct 123 is connected to the first air outlet 113, and the air outlet end of the second air outlet duct 124 is connected to the second air outlet 114.

[0058] The assembly space 111 formed within the instrument frame 11 can accommodate and protect the instrument panel module, the damper control system 121, the first air outlet 123 and the second air outlet 124, so that the instrument panel assembly 10 has a higher degree of integration and compactness.

[0059] The instrument frame 11 has an air inlet recess, an instrument display port 112, a first air outlet 113, and a second air outlet 114. The air inlet recess is used to avoid the air intake duct 122, so that the air intake duct 122 can pass through the instrument frame 11 and connect with the air conditioning module. The instrument display port 112 is used to avoid the instrument module, so that the pilot can read the flight parameters, navigation parameters, and aircraft 100 system status information displayed on the instrument module through the display port. The first air outlet 113 is used to blow the cold or warm air output from the first air outlet duct 123 towards the windshield, and the second air outlet 114 is used to blow the cold or warm air output from the second air outlet duct 124 towards the cabin 211.

[0060] In some embodiments, the left side 117 and right side 118 of the instrument frame 11 are respectively provided with maintenance ports 119 communicating with the assembly space 111. By providing maintenance ports 119, the instrument panel module and the air outlet module 12 in the assembly space 111 can be maintained through the maintenance ports 119, thereby providing a maintenance path for the instrument panel module and the air outlet module 12 and avoiding the need to disassemble the entire instrument panel assembly 10 from the aircraft 100.

[0061] In some embodiments, the instrument panel assembly 10 further includes a service cover 14, which corresponds one-to-one with the service port 119, covers the service port 119, and is detachably connected to the instrument frame 11. The instrument panel assembly 10 also includes an instrument frame skin 13, which covers the outer surface of the instrument frame 11 and avoids the air inlet, the instrument display port 112, the first air outlet 113, the second air outlet 114, and the service cover 14.

[0062] The instrument panel frame skin 13 covers the outer surface of the instrument panel frame 11 to meet different styling requirements of the instrument panel assembly 10. The maintenance cover 14 covers the maintenance port 119, and together with the instrument panel frame skin 13, it encloses the instrument panel module and air outlet module 12 within the instrument panel frame 11 to protect them and reduce external damage. The maintenance cover 14 is detachably connected to the instrument panel frame 11, allowing for maintenance of the instrument panel module and air outlet module 12 by removing the maintenance cover 14.

[0063] Please see Figure 1 , Figure 2 and Figure 4In some embodiments, multiple connecting frames 15 are provided on both the left and right sides of the instrument frame 11. All connecting frames 15 located on the same side are arranged at intervals along the forward direction X of the aircraft 100, and the connecting frames 15 are detachably connected to both the instrument frame 11 and the fuselage frame 21. By providing multiple connecting frames 15 on the left and right sides of the instrument frame 11, the instrument frame 11 can be stably and reliably connected to the fuselage frame 21.

[0064] In actual operation, after all the modules (instrument panel module and air outlet module 12, etc.) of the instrument panel assembly 10 are assembled into the instrument frame 11, the instrument frame 11 is then installed onto the fuselage frame 21 through all the connecting brackets 15. This design greatly improves the assembly efficiency of the aircraft 100.

[0065] Please see Figures 1 to 6 This application also provides an aircraft 100, which includes a fuselage assembly 20 and an instrument panel assembly 10 as described in any of the above embodiments. The fuselage assembly 20 includes a fuselage frame 21, a windshield, and an air conditioning module. A cabin 211 is provided inside the fuselage frame 21. The windshield is installed at the front end of the fuselage frame 21 along the forward direction X of the aircraft 100, and the air conditioning module is located at the rear end of the fuselage frame 21 along the forward direction X. The instrument panel assembly 10 is located inside the cabin 211 and at the front end of the fuselage frame 21 along the forward direction X. The instrument frame 11 is detachably connected to the fuselage frame 21. One end of the air intake duct 122 away from the air door control system 121 is connected and communicates with the air conditioning module. A first air outlet duct 123 is used to blow air onto the windshield, and a second air outlet duct 124 is used to blow air into the cabin 211.

[0066] The aircraft 100 in this application is assembled by two separate production lines, with the instrument panel assembly 10 and the fuselage assembly 20 being assembled by two separate production lines. After that, the instrument panel assembly 10 is connected to the fuselage assembly 20 to improve the assembly efficiency of the aircraft 100.

[0067] The aircraft 100 provided in this embodiment has the effects of any of the above embodiments, so it will not be described again here.

[0068] Please see Figure 2 , Figures 4 to 8 In some embodiments, the instrument frame 11 is provided with a first connecting frame 151, a second connecting frame 152 and a third connecting frame 153 on both the left and right sides. The first connecting frame 151, the second connecting frame 152 and the third connecting frame 153 located on the same side are arranged at intervals along the forward direction X. The fuselage frame 21 includes a cabin floor 212 and a cabin side panel 213 arranged around the cabin floor 212. The first connecting frame 151 is used to connect the cabin side panel 213 and the instrument frame 11. The second connecting frame 152 and the third connecting frame 153 are both used to connect the cabin floor 212 and the instrument frame 11.

[0069] Specifically, the cabin floor 212 and the cabin side panels 213 are both oriented towards the cabin 211.

[0070] In the forward direction X of the aircraft 100, the second connecting frame 152 is located between the first connecting frame 151 and the third connecting frame 153. The first connecting frame 151 is used to connect the rear end of the instrument frame 11 to the cabin side panel 213, the second connecting frame 152 is used to connect the middle part of the instrument frame 11 to the cabin floor 212, and the third connecting frame 153 is used to connect the front end of the instrument frame 11 to the cabin floor 212. In this way, by setting the first connecting frame 151, the second connecting frame 152, and the third connecting frame 153 on both sides of the instrument frame 11, the front, middle, and rear positions on both sides of the instrument frame 11 can be fixed, improving the stability and reliability of the connection between the instrument frame 11 and the fuselage frame 21.

[0071] Please see Figure 5 and Figure 7 In some embodiments, the first connecting frame 151 includes a first box 1511 and a second box 1512 arranged side by side and connected together. The openings of the first box 1511 and the second box 1512 are both located away from the cabin floor 212. The side wall of the first box 1511 is detachably connected to the instrument frame 11, and the side wall of the second box 1512 is detachably connected to the cabin side panel 213.

[0072] Please see Figure 2 and Figure 8 In some embodiments, the third connecting frame 153 includes a first box 1511 and a second box 1512 arranged side by side and connected together. The openings of the first box 1511 and the second box 1512 are both located away from the cabin floor 212. The first box 1511 and the second box 1512 are both located between the fuselage frame 21 and the instrument frame 11. The side wall of the first box 1511 is detachably connected to the instrument frame 11, and the side wall of the second box 1512 is detachably connected to the cabin side panel 213.

[0073] To facilitate the installation of the instrument panel assembly 10 onto the fuselage frame 21, a gap is pre-reserved between the instrument frame 11 and the cabin side panel 213 in the left-right direction Y. Both the first housing 1511 and the second housing 1512 have a certain width in the left-right direction Y. During assembly, both the first housing 1511 and the second housing 1512 are positioned between the instrument frame 11 and the cabin side panel 213, and both can fill the gap between them. Then, the side wall of the first housing 1511 is detachably connected to the instrument frame 11, and the side wall of the second housing 1512 is detachably connected to the cabin side panel 213, thereby achieving the connection between the instrument frame 11 and the cabin 211 frame. In this design, the first box 1511 and the second box 1512 fill the gap between the instrument frame 11 and the cabin side panel 213, so that the instrument frame 11, the first connecting frame 151 and the cabin 211 frame can be closely fitted together in sequence, reducing the risk of the instrument frame 11 swaying relative to the cabin 211 frame during operation.

[0074] In some embodiments, the second connecting frame 152 and the third connecting frame 153 each include a first plate 1531, a second plate 1532, and a reinforcing rib 1533. The first plate 1531 is detachably connected to the instrument frame 11. The second plate 1532 is disposed at the bottom of the first plate 1531 and is bent away from the instrument frame 11 in the left-right direction Y of the aircraft 100 relative to the first plate 1531. The second plate 1532 is detachably connected to the cabin floor 212. The reinforcing rib 1533 is connected between the first plate 1531 and the second plate 1532.

[0075] The first connecting frame 151 and the second connecting frame 152, which are formed by the first plate 1531, the second plate 1532 and the reinforcing rib 1533, have a stable structure and high mechanical strength, and can stably and reliably connect the instrument frame 11 and the body frame 21.

[0076] It is worth mentioning that the detachable connection method mentioned in this application can be achieved by using screws, pins, or other detachable heating elements, and no specific limitation is made here.

[0077] In some embodiments, the fuselage assembly 20 also includes an interior trim panel that covers the cabin floor 212 to meet the styling requirements of the interior of the cabin 211.

[0078] In some embodiments, the fuselage frame 21 further includes multiple cabin floor 212 beams arranged along the left-right direction Y, and the cabin floor 212 beams are supported on the bottom side of the cabin floor 212 to improve the mechanical strength of the entire fuselage frame 21.

[0079] The instrument panel assembly 10 and the aircraft 100 mentioned above integrate the instrument panel module and the air outlet module 12 in the instrument panel assembly 10. After the instrument frame 11 is installed on the aircraft 100, the instrument panel module and the air outlet module 12 can be installed in an integrated manner on the aircraft 100. This design makes the assembly of the aircraft 100 time-saving and labor-saving, and greatly improves the assembly efficiency of the aircraft 100.

[0080] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0081] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An instrument panel assembly, applied to an aircraft, the aircraft including a fuselage assembly (20), the fuselage assembly (20) including a fuselage frame (21), a windshield and an air conditioning module, the fuselage frame (21) having a cabin (211) inside, the windshield and the air conditioning module both being mounted on the fuselage frame (21), characterized in that, The instrument panel assembly is located within the engine compartment (211), and the instrument panel assembly includes: Instrument frame (11); Instrument panel module; The air outlet module (12) includes a damper control system (121), an air inlet duct (122), a first air outlet duct (123), and a second air outlet duct (124). The damper control system (121) is installed on the instrument frame (11). The air inlet duct (122), the first air outlet duct (123), and the second air outlet duct (124) are all connected to the damper control system (121). The air inlet duct (122) is connected to and communicates with the air conditioning module. The damper control system (121) is used to distribute the air volume input from the air inlet duct (122) to the first air outlet duct (123) and / or the second air outlet duct (124). The first air outlet duct (123) is used to blow air onto the windshield, and the second air outlet duct (124) is used to blow air onto the cabin (211).

2. The instrument panel assembly according to claim 1, characterized in that, The air inlet duct (122) consists of multiple ducts, all of which are connected between the air conditioning module and the damper control system (121).

3. The instrument panel assembly according to claim 1, characterized in that, An assembly space (111) is defined within the instrument frame (11), and the instrument panel module, the damper control system (121), the first air outlet duct (123) and the second air outlet duct (124) are all installed within the assembly space (111). The instrument frame (11) has an air inlet, an instrument display port (112), a first air outlet (113), and a second air outlet (114) all communicating with the assembly space (111). The first air outlet (113) is located on the top surface (115) of the instrument frame (11) and faces the windshield. The instrument display port (112) and the second air outlet (114) are located on the operating end face (116) of the instrument frame (11) facing the driver's seat in the engine compartment (211). The air inlet is located on the left side (117) and / or the right side (118) of the instrument frame (11) adjacent to the top surface (115) and the operating end face (116). The air inlet duct (122) passes through the air inlet opening, the instrument panel module is exposed in the instrument display port (112), the air outlet end of the first air outlet duct (123) is connected to the first air outlet (113), and the air outlet end of the second air outlet duct (124) is connected to the second air outlet (114).

4. The instrument panel assembly according to claim 3, characterized in that, The left side (117) and right side (118) of the instrument frame (11) are respectively provided with maintenance ports (119) communicating with the assembly space (111).

5. The instrument panel assembly according to claim 4, characterized in that, The instrument panel assembly also includes a maintenance cover (14), which corresponds one-to-one with the maintenance port (119). The maintenance cover (14) covers the maintenance port (119) and is detachably connected to the instrument frame (11). The instrument panel assembly also includes an instrument frame skin (13), which covers the outer surface of the instrument frame (11) and avoids the air inlet, the instrument display port (112), the first air outlet (113), the second air outlet (114) and the maintenance cover (14).

6. The instrument panel assembly according to claim 1, characterized in that, Multiple connecting frames (15) are provided on the left and right sides of the instrument frame (11). All the connecting frames (15) located on the same side are arranged at intervals along the forward direction (X) of the aircraft, and the connecting frames (15) can be detachably connected to the instrument frame (11) and the fuselage frame (21).

7. An aircraft, characterized in that, The aircraft include: The fuselage assembly (20) includes a fuselage frame (21), a windshield, and an air conditioning module. The fuselage frame (21) houses a cabin (211). The windshield is mounted at the front end of the fuselage frame (21) along the forward direction (X) of the aircraft. The air conditioning module is located at the rear end of the fuselage frame (21) along the forward direction (X). The fuselage assembly also includes an instrument panel assembly as described in any one of claims 1 to 6. The assembly is located in the cabin (211) and at the front end of the fuselage frame (21) along the forward direction (X). The instrument frame (11) is detachably connected to the fuselage frame (21). The end of the air intake duct (122) away from the damper control system (121) is connected to and communicates with the air conditioning module. The first air outlet duct (123) is used to blow air onto the windshield, and the second air outlet duct (124) is used to blow air onto the cabin (211).

8. The aircraft according to claim 7, characterized in that, The instrument frame (11) is provided with a first connecting frame (151), a second connecting frame (152) and a third connecting frame (153) on the left and right sides. The first connecting frame (151), the second connecting frame (152) and the third connecting frame (153) located on the same side are arranged at intervals along the forward direction (X). The fuselage frame (21) includes a cabin floor (212) and cabin side panels (213) arranged around the cabin floor (212). The first connecting frame (151) is used to connect the cabin side panels (213) and the instrument frame (11). The second connecting frame (152) and the third connecting frame (153) are both used to connect the cabin floor (212) and the instrument frame (11).

9. The aircraft according to claim 8, characterized in that, The first connecting frame (151) includes a first box (1511) and a second box (1512) arranged side by side and connected together. The openings of the first box (1511) and the second box (1512) are both facing away from the cabin floor (212). The first box (1511) and the second box (1512) are both located between the fuselage frame (21) and the instrument frame (11). The side wall of the first box (1511) is detachably connected to the instrument frame (11), and the side wall of the second box (1512) is detachably connected to the cabin side panel (213).

10. The aircraft according to claim 8, characterized in that, The second connecting frame (152) and the third connecting frame (153) both include a first plate (1531), a second plate (1532), and a reinforcing rib plate (1533). The first plate (1531) is detachably connected to the instrument frame (11). The second plate (1532) is disposed at the bottom of the first plate (1531) and is bent away from the instrument frame (11) in the left-right direction (Y) of the aircraft relative to the first plate (1531). The second plate (1532) is detachably connected to the cabin floor (212). The reinforcing rib plate (1533) is connected between the first plate (1531) and the second plate (1532).

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