Machine body beam frame

Abstract

The invention relates to the technical field of aircrafts, in particular to a fuselage beam frame which comprises girders (11) and bulkheads (12). The fuselage beam frame can meet the requirements of a modular fuselage, and has the effects of supporting fuselage skin wallboards (or fuselage wallboards or fuselage skin assemblies), bearing axial force caused by bending moment and keeping the shape of the fuselage.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a fuselage beam frame. Background Art

[0002] The surge in demand for aircraft requires the re-optimization of aircraft structure, and the current fuselage structure is no longer suitable for mass production requirements.

[0003] The fuselage beam frame involved in the present application has at least the following beneficial technical effects: it can be produced in large quantities, has high production efficiency, and reduces costs. Summary of the Invention

[0004] The purpose of this application is to provide a fuselage beam frame that can meet the requirements of a modular fuselage, support the fuselage skin panel (or fuselage panel or fuselage skin assembly), withstand the axial force caused by bending moment, and maintain the fuselage shape; the main components, the beam and the bulkhead, are integral structures and can be obtained by processing die forgings or die castings or stampings or extrusions, with fast production speed and low cost for mass production; the fuselage beam frame is connected to the skeleton of the fuselage skin panel (or fuselage panel or fuselage skin assembly), with high connection strength and high safety, reducing the workload of connecting parts and related connections, and high production efficiency.

[0005] The technical solution of the present application is: a fuselage beam frame, the fuselage beam frame comprising a beam (11) and a bulkhead (12);

[0006] The main material of the fuselage beam frame is aluminum alloy, magnesium alloy or titanium alloy, or the main material of the fuselage beam frame is two or three of aluminum alloy, magnesium alloy and titanium alloy;

[0007] The fuselage beam frame has a plurality of beams (11) (two or more beams); the fuselage beam frame has a plurality of bulkheads (12) (four or more beams); the fuselage beam frame plays a role in supporting the fuselage skin panel (or fuselage panel or fuselage skin assembly), bearing the axial force caused by the bending moment, and maintaining the fuselage shape;

[0008] The beam (11) is a longitudinal (or similar longitudinal) member of the fuselage structure and is the main member for bearing the axial force caused by the bending moment; the bulkhead (12) is a transverse (or similar transverse) member of the fuselage structure and plays the role of bearing and transmitting loads, maintaining the shape of the fuselage, and supporting the skin panel (2);

[0009] The beam (11) is a longitudinal (or similar longitudinal) member of the fuselage structure and is the main member that bears the axial force caused by the bending moment;

[0010] The bulkhead (12) is a transverse (or similar transverse) member of the fuselage structure, which plays the role of bearing and transmitting loads, maintaining the shape of the fuselage, and supporting the fuselage skin panel (or fuselage panel or fuselage skin assembly);

[0011] The bulkhead (12) located in the middle of the fuselage beam frame is in the shape of a circular ring (or similar to a circular ring, or an incomplete circular ring), and the connection between the beam (11) and the bulkhead (12) located in the middle of the fuselage beam frame is achieved by connecting the beam (11) with the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame; the contact surface of the beam (11) connected to the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame is fitted (or similar to fitted) with the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame; the contact surface is similar to an arc surface, and the structure is relatively compact, which reduces the space occupied in the machine;

[0012] The connection between the fuselage beam frame and the fuselage skin panel (or fuselage panel or fuselage skin assembly) is mainly achieved by connecting the bulkhead (12) to the frame of the fuselage skin panel (or fuselage panel or fuselage skin assembly); the fuselage beam frame is no longer directly connected to the skin (typical skin: fixed to the frame by bonding or riveting to form a dimensional component surrounding the aerodynamic shape); the connection strength is high, a large number of connecting parts and corresponding connection work can be reduced, production efficiency is high, and cost is reduced;

[0013] The beam (11) is an integral structure and can be obtained by processing die forgings, die castings, stampings or extrusions, with high production speed, low mass production cost and high consistency;

[0014] The bulkhead (12) is an integral structure and can be obtained by processing die forgings, die castings, stampings or extrusions, with high production speed, low mass production cost and high consistency;

[0015] The fuselage beam frame is no longer connected to the stringer (typical stringer: a rod-shaped component that is subjected to axial force in the longitudinal direction of the fuselage), and has a simple structure and is easy to assemble.

[0016] Unless otherwise defined, the technical or scientific terms used in this description should have the ordinary meanings understood by those skilled in the art to which this application belongs. In this description, the terms "outer," "inner," "a section," "first level," "inlet," "outlet," "axial," "tangential," "inner diameter," "outer diameter," "interlaced," "corresponding," "circumference," "certain," "last," and the like, indicating positions or relationships, are used solely for the purpose of facilitating the description of the present invention and simplifying the description. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation and are therefore not to be construed as limitations on the present invention. Furthermore, the terms "first level," "next level," "step by step," "a modular unit," "last level," and similar terms are used solely for descriptive purposes to distinguish between different components and are not to be construed as indicating or implying relative importance. Terms such as "one" and "first level" used in this description should not be construed as absolute limitations on quantity, but rather as meaning the presence of at least one. Terms such as "downwardly deflected 90 degrees" and "horizontally rearward" used in this description should not be construed as absolute limitations on degree, but rather as encompassing "downwardly deflected 90 degrees" and "horizontally rearward." Words such as “including”, “or” and the like used in the description of this application mean that the elements or objects preceding the word include the elements or objects listed after the word and their equivalents, but do not exclude other elements or objects.

[0017] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "connect", "assemble", "install", "combination", "connect" and similar words used in the description of this application should be understood in a broad sense. For example, the 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, an indirect connection through an intermediate medium, or the internal connection of two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 is a schematic diagram of the fuselage beam frame provided in an embodiment of the present application;

[0019] Figure 2 、 3 1 is a schematic diagram of the rear section of the fuselage beam frame provided in an embodiment of the present application, cut along AA;

[0020] Figure 4 is a schematic diagram of the cross section of the beam provided in an embodiment of the present application;

[0021] Figure 5 is a schematic diagram of the bulkhead provided in an embodiment of the present application;

[0022] Among them: 11- beam, 12- partition frame.

[0023] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product; in addition, the drawings are used for illustrative purposes, and the terms describing the positional relationships therein are limited to illustrative purposes and cannot be understood as limitations on this patent. DETAILED DESCRIPTION

[0024] Figure 1 In the embodiment, the number of the beams (11) of the fuselage beam frame is 4, and the number of the bulkheads (12) of the modular fuselage is 11; the fuselage beam frame (1) plays the role of supporting the fuselage skin panel (or fuselage panel or fuselage skin assembly), bearing the axial force caused by the bending moment, and maintaining the fuselage shape;

[0025] Figure 2 、 3 In the fourth embodiment, the connection between the beam (11) and the bulkhead (12) located in the middle of the fuselage beam frame is achieved by connecting the beam (11) with the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame, and the connection strength is high; the contact surface of the beam (11) connected to the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame is fitted (or similarly fitted) with the inner surface of the inner ring of the bulkhead (12) in the fuselage beam frame; the contact surface is similar to an arc surface, and the structure is relatively compact, which reduces the space occupied in the machine;

[0026] Figure 5 In the embodiment, the bulkhead (12) in the middle of the fuselage beam frame is annular (or similar to annular) and can be obtained by processing die forgings, die castings, stampings or extrusions, with fast production speed, low mass production cost and high consistency.

Claims

1. A fuselage beam frame, characterized in that: The fuselage beam frame comprises a beam (11) and a bulkhead (12).

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

3. A fuselage beam frame according to any one of the preceding claims, characterised in that The number of the beams (11) of the fuselage beam frame is several (or more) (2 or more); the number of the bulkheads (12) of the fuselage beam frame is several (or more) (4 or more); the fuselage beam frame plays a role in supporting the fuselage skin panel (or fuselage panel or fuselage skin assembly), bearing the axial force caused by the bending moment, and maintaining the fuselage shape.

4. A fuselage beam frame according to any one of the preceding claims, characterised in that The beam (11) is a longitudinal (or similar longitudinal) member of the fuselage structure and is the main member for bearing the axial force caused by the bending moment.

5. A fuselage beam frame according to any one of the preceding claims, characterised in that The bulkhead (12) is a transverse (or similar transverse) member of the fuselage structure, which plays the role of bearing and transmitting loads, maintaining the shape of the fuselage, and supporting the fuselage skin panel (or fuselage panel or fuselage skin assembly).

6. A fuselage beam frame according to any one of the preceding claims, characterised in that The bulkhead (12) located in the middle of the fuselage beam frame is in the shape of a ring (or a shape similar to a ring, or an incomplete ring), and the connection between the beam (11) and the bulkhead (12) located in the middle of the fuselage beam frame is achieved by connecting the beam (11) with the inner surface of the inner ring of the bulkhead (12) in the middle of the fuselage beam frame.

7. A fuselage beam frame according to any one of the preceding claims, characterised in that The connection between the fuselage beam frame and the fuselage skin panel (or fuselage panel or fuselage skin assembly) is mainly achieved by connecting the bulkhead (12) to the skeleton of the fuselage skin panel (or fuselage panel or fuselage skin assembly); the fuselage beam frame is no longer directly connected to the skin (typical skin: fixed to the skeleton by bonding or riveting to form a dimensional component surrounding the aerodynamic shape).

8. A fuselage beam frame according to any one of the preceding claims, characterised in that The beam (11) is an integral structure and can be obtained by processing a die forging, a die casting, a stamping or an extrusion.

9. A fuselage beam frame according to any one of the preceding claims, characterised in that The partition frame (12) is an integral structure and can be obtained by processing a die forging, a die casting, a stamping or an extrusion.

10. A fuselage beam frame according to any one of the preceding claims, characterised in that The fuselage beam frames are no longer connected to stringers (typical stringers: rod-shaped components that are subjected to axial forces in the longitudinal direction of the fuselage).

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