Modular fuselage

Abstract

The invention relates to the technical field of aircrafts, in particular to a modular fuselage which comprises fuselage beam frames (1) and skin wallboards (2). All the components are manufactured separately and then connected and combined, the manufacturing difficulty is reduced, and the production efficiency is high; the skin wall plate is of an integral structure, the production speed is high, and the cost of mass production is low.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and particularly to a modular fuselage. Background Art

[0002] On March 27, 2024, the Ministry of Industry and Information Technology, the Ministry of Science and Technology, the Ministry of Finance, and the Civil Aviation Administration of China issued the Implementation Plan for the Innovative Application of General Aviation Equipment (2024-2030), putting forward the main goals: By 2027, China's supply capacity and industrial innovation capacity of general aviation equipment will be significantly improved, a modern general aviation basic support system will be basically established, a highly integrated industrial ecosystem will be initially formed, the general aviation public service equipment system will be basically improved, and new general aviation equipment characterized by unmanned, electrified, and intelligent features will achieve commercial applications in fields such as urban air transportation, logistics distribution, and emergency rescue; By 2030, a new general aviation industry development model characterized by high-end, intelligent, and green features will be basically established, supporting and ensuring the safe and efficient operation of the "short-distance transportation + electric vertical takeoff and landing" passenger transportation network, the "trunk-branch-last-mile" unmanned aerial vehicle distribution network, and the low-altitude production operation network that meets the needs of industrial and agricultural operations. General aviation equipment will be fully integrated into all fields of people's production and life, becoming a powerful driving force for the growth of the low-altitude economy and forming a market scale of trillions of yuan.

[0003] The surging demand for aircraft requires the re-optimization of the structure of aircraft, and the current fuselage structure no longer meets the requirements of mass production.

[0004] A modular fuselage involved in the present application has at least the following beneficial technical effects: It can be mass-produced with high production efficiency and reduced costs. Summary of the Invention

[0005] The purpose of the present application is to provide a modular fuselage. The skin panels are segmented and manufactured separately, reducing the manufacturing difficulty and having high production efficiency; the skin panels adopt an integral structure and can be obtained by processing die forgings or die castings, with a fast production speed and low costs for mass production; the connection of each component is mainly achieved by connecting through ribs (or frameworks), with high connection strength, high safety, reducing the amount of work of connecting parts and related connections, and having high production efficiency; modular design, with each component manufactured separately and then connected and combined, having high production efficiency.

[0006] The technical solution of the present application is: A modular fuselage, the modular fuselage includes a fuselage beam frame (1) and skin panels (2);

[0007] The main material of the modular fuselage is aluminum alloy or magnesium alloy or titanium alloy, or the main material of the modular fuselage is two or three of aluminum alloy, magnesium alloy, and titanium alloy;

[0008] The fuselage beam frame (1) includes girders (11) and frames (12); there are several (or multiple) (two or more than two) girders (11) in the modular fuselage; there are several (or multiple) (four or more than four) frames (12) in the modular fuselage; the fuselage beam frame (1) serves to support the skin panel (2); the fuselage beam frame (1) serves to bear the axial force caused by bending moment and maintain the shape of the fuselage; it is relatively easy to open an opening in the fuselage as needed.

[0009] The girder (11) is a longitudinal (or similar longitudinal) member of the fuselage structure and is the main member to bear the axial force caused by bending moment; the frame (12) is a transverse (or similar transverse) member of the fuselage structure, which serves to bear and transfer loads, maintain the shape of the fuselage, and support the skin panel (2).

[0010] The frames (12) at the front and rear of the fuselage can be made into panel-type frames as needed; the middle frames (12) can be made into a circular ring shape, and the frames (12) at the opening part of the fuselage are incomplete.

[0011] The connection between the frame (12) and the skin panel (2) is mainly realized by connecting the frame (12) with the transverse rib (22) (or longitudinal rib 23) of the skin panel (2).

[0012] The skin panel (2) includes skin (21), transverse ribs (22), and longitudinal ribs (23); the transverse rib (22) is the skeleton of the skin panel (2) in the transverse (or similar transverse) direction of the fuselage, and the longitudinal rib (23) is the skeleton of the skin panel (2) in the longitudinal (or similar longitudinal) direction of the fuselage; the transverse rib (22) and longitudinal rib (23) serve to support the skin (21), form and maintain the shape of the skin panel (2), and transfer loads, etc.; the skin (21) serves to bear local aerodynamic forces and form the shape of the skin panel (2).

[0013] The skin panel (2) is an integral structure, which can be obtained by machining die forgings or die castings. It has a fast production speed, low production cost in large quantities, high consistency, and relatively high strength of the panel. There is no need to connect the skin to stringers, riblets, etc., which can reduce a large number of connecting parts and corresponding connection work, with high production efficiency and cost reduction.

[0014] There are multiple (six or more than six) skin panels (2) in the modular fuselage; the multiple skin panels (2) connected to the modular fuselage serve to maintain the shape of the fuselage, bear a small part (or part) of the axial force caused by bending moment, bear shear force and torque, and bear and transfer local aerodynamic loads; it is segmented, and each segment is manufactured separately, reducing the manufacturing difficulty, classifying production, and having high production efficiency.

[0015] After the skin panel is segmented, the size of a single skin panel (2) is relatively small, and it is relatively easy to manufacture complex curved surfaces, reducing the production difficulty;

[0016] The connection between the skin panels (2) is realized by means of transverse ribs (22) (or longitudinal ribs 23) connecting the adjacent edges of the skin panels (2);

[0017] The connection of each component is mainly achieved by ribs (or frameworks), with high connection strength and high safety; each panel can use skins of different thicknesses as needed without affecting the smoothness of the wing surface;

[0018] Modular design, with each component manufactured separately and then connected and combined, resulting in high production efficiency;

[0019] If a certain skin panel (2) is damaged, it can be replaced separately, with a fast replacement speed, low difficulty, and easy maintenance.

[0020] Unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. In the description of this application, terms such as "outer", "inner", "section", "level", "inlet", "outlet", "axial", "tangential", "inner diameter", "outer diameter", "staggered", "corresponding", "circumference", "certain", "last", etc. indicating orientation or positional relationships are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the devices and elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation on the present invention. In addition, terms such as "first level", "next level", "step by step", "a modular unit", "last level" and similar terms are only for descriptive purposes to distinguish different components and should not be construed as indicating or implying relative importance. The terms "one", "level", etc. used in the description of this application should not be construed as an absolute limitation on the quantity but should be understood as having at least one. The terms "deflected downward by 90 degrees", "horizontally backward", etc. used in the description of this application should not be construed as an absolute limitation on the degree but should be understood as including "deflected downward by 90 degrees", "horizontally backward". The terms "including", "or", "and" and similar terms used in the description of this application mean that the elements or objects appearing before this word cover the elements or objects listed after this word and their equivalents, without excluding other elements or objects.

[0021] In addition, it should be noted that, unless otherwise clearly specified and defined, the similar terms such as "connection", "assembly", "installation", "combination", "linkage", etc. used in the description of this application should be understood in a broad sense. For example, connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can also be the communication inside two components. Those skilled in the art can understand its specific meaning in this application according to the specific situation. Brief Description of the Drawings

[0022] Figure 1 is the schematic exploded view of the modular fuselage provided by the embodiment of this application;

[0023] Figure 2 is the schematic diagram of the fuselage beam frame provided by the embodiment of this application;

[0024] Figure 3 and 4 is the schematic diagram of the skin panel provided by the embodiment of this application;

[0025] Wherein: 1 - fuselage beam frame, 11 - main beam, 12 - frame, 2 - skin panel, 21 - skin, 22 - transverse rib, 23 - longitudinal rib.

[0026] To better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which do not represent the dimensions of the actual product; in addition, the drawings are for illustrative purposes only, and the terms describing the positional relationship therein are only for illustrative purposes and cannot be construed as a limitation of this patent. Detailed Embodiment

[0027] The specific embodiments described herein are only partial embodiments of this application, which are only used to explain this application rather than limit this application. It should be noted that, for the convenience of description, only the parts related to this application are shown in the drawings, and other related parts can refer to the general design. Without conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments;

[0028] The following makes supplementary explanations for this application in combination with the drawings;

[0029] Figure 1In the embodiment, the skin panel is longitudinally divided into 10 segments and transversely divided into 4 segments, with a total of 40 skin panels (2). Each skin panel (2) is manufactured separately, which reduces the manufacturing difficulty, enables classified production, and has high production efficiency. The size of a single skin panel (2) is small, and it can relatively easily manufacture complex curved surfaces, reducing the production difficulty. Each skin panel (2) can be designed with typical surfaces as needed to meet the requirements of different parts. The surface of a single skin panel (2) is processed well. After installation, there is no need for further surface treatment, which is highly efficient. The fuselage beam frame (1) serves as a structural member of the fuselage, and each skin panel (2) is installed on the fuselage beam frame (1).

[0030] Figure 2 In the embodiment, there are 4 main beams (11) of the modular fuselage (1), and 11 frames (12) of the modular fuselage. The fuselage beam frame (1) plays a role in supporting the skin panel (2), bearing the axial force caused by bending moment, and maintaining the shape of the fuselage.

[0031] Figure 3 、 4 In the embodiment, the skin panel (2) is of an integral structure and can be obtained by machining die forgings or die castings. The transverse ribs and longitudinal ribs cross each other, increasing the strength, and a relatively thin skin thickness can be adopted.

Claims

1. A modular fuselage, characterized in that, The modular fuselage includes a fuselage beam frame (1) and a skin panel (2).

2. The modular fuselage according to claim 1, characterized in that: The main material of the modular fuselage is aluminum alloy or magnesium alloy or titanium alloy, or the main material of the modular fuselage is two or three of aluminum alloy, magnesium alloy, and titanium alloy.

3. Modular fuselage according to any one of the preceding claims, characterized in that The fuselage beam frame (1) includes main beams (11) and frames (12); there are several (or multiple) (two or more) main beams (11) of the modular fuselage, and there are several (or multiple) (four or more) frames (12) of the modular fuselage; the fuselage beam frame (1) serves to support the skin panel (2).

4. The modular fuselage according to any one of the preceding claims, characterized in that, The main beam (11) is a longitudinal (or similar longitudinal) member of the fuselage structure, and the frame (12) is a transverse (or similar transverse) member of the fuselage structure.

5. Modular fuselage according to any one of the preceding claims, characterized in that The connection between the frame (12) and the skin panel (2) is mainly achieved through the connection between the frame (12) and the transverse rib (22) (or longitudinal rib 23) of the skin panel (2).

6. The modular fuselage according to any one of the preceding claims, characterized in that, The skin panel (2) includes a skin (21), a transverse rib (22), and a longitudinal rib (23); the transverse rib (22) is the skeleton of the skin panel (2) in the transverse (or similar transverse) direction of the fuselage, and the longitudinal rib (23) is the skeleton of the skin panel (2) in the longitudinal (or similar longitudinal) direction of the fuselage; the transverse rib (22) and the longitudinal rib (23) serve to support the skin (21), form and maintain the shape of the skin panel (2), and transfer loads, etc.; the skin (21) has the function of withstanding local aerodynamic forces and forming the outer shape of the skin panel (2).

7. The modular fuselage according to any one of the preceding claims, characterized in that, The skin panel (2) is an integral structure.

8. The modular fuselage according to any one of the preceding claims, characterized in that, There are multiple (six or more) skin panels (2) of the modular fuselage, and the multiple skin panels (2) connected to the modular fuselage serve to maintain the outer shape of the fuselage.

9. The modular fuselage according to any one of the preceding claims, characterized in that, The connection between the skin panels (2) is achieved by connecting the adjacent transverse ribs (22) (or longitudinal ribs 23) of the skin panels (2).

10. Modular fuselage according to any one of the preceding claims, characterized in that The fuselage beam frame (1) and the skin panel (2) are manufactured separately and then connected and combined to form the modular fuselage.

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