Wing beam frame

Abstract

The invention relates to the technical field of aircrafts, in particular to a wing beam frame which comprises an upper cross beam (11), a lower cross beam (12), a front wing spar (13) and a rear wing spar (14). The wing beam frame is used as a main force bearing mechanism of the wing and adapts to the requirements of the modular wing; each main part is of an integral structure and can be obtained by machining die forgings or die castings or stamping parts or extrusion parts, 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 wing beam. Background Art

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

[0004] The wing beam involved in the present application has at least the following beneficial technical effects: it can be mass - produced, with high production efficiency and low cost. Summary of the Invention

[0005] The purpose of the present application is to provide a wing beam, as the main load - bearing mechanism of the wing, to meet the requirements of modular wings; all main components adopt an integral structure, which can be obtained by processing die - forgings, die - castings, stampings or extrusions, with fast production speed and low cost for mass production.

[0006] The technical solution of the present application is: a wing beam, the wing beam includes an upper cross - beam (11), a lower cross - beam (12), a front wing beam (13), and a rear wing beam (14);

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

[0008] The wing beam functions to bear the force and moment of the wing and support other components of the wing such as the wing wall panel (or wing skin wall panel or skin assembly); the wing beam is the main load - bearing mechanism of the wing;

[0009] The main functions of the front wing beam (13) and the rear wing beam (14) are to bear the bending moment and shear force of the wing;

[0010] The front wing beam (13) and the rear wing beam (14) are of integral structure, which can be obtained by processing die - forgings or die - castings, with fast production speed and low cost for mass production;

[0011] The upper cross - beam (11) and the lower cross - beam (12) are the skeletons in the transverse (or similar transverse) direction of the wing; the upper cross - beam (11) and the lower cross - beam (12) are of integral structure, which can be obtained by processing die - forgings, die - castings, stampings or extrusions, with fast production speed and low cost for mass production;

[0012] The upper cross - beam (11) and the lower cross - beam (12) are several (or multiple) (2 or more than 2);

[0013] The upper cross beam (11) is respectively connected to the upper parts of the front wing beam (13) and the rear wing beam (14), and the lower cross beam (12) is respectively connected to the lower parts of the front wing beam (13) and the rear wing beam (14); the enclosing frame formed by the upper cross beam (11), the front beam (13), the rear beam (14) and the lower cross beam (12) bears the torque of the wing;

[0014] The upper crossbeam (11) extends forward and approaches (or is similar to approaching or touching or is relatively close to) the leading edge of the wing, and extends backward and approaches (or is similar to approaching or touching or is relatively close to) the trailing edge of the wing; the lower crossbeam (12) extends forward and approaches (or is similar to approaching or touching or is relatively close to) the leading edge of the wing, and extends backward and approaches (or is similar to approaching or touching or is relatively close to) the trailing edge of the wing; the corresponding upper crossbeam (11) and lower crossbeam (12) on the wing beam frame constitute and maintain a specified partial (or most or complete) airfoil (or similar airfoil); for the convenience of explanation, the upper crossbeam and the lower crossbeam are separated, and can also be connected to increase strength.

[0015] The connection between the wing beam frame and the wing panel (or wing skin panel or skin assembly) is mainly achieved by connecting the upper crossbeam (11) and the lower crossbeam (12) to the wing panel (or wing skin panel or skin assembly) respectively; the upper crossbeam (11) and the lower crossbeam (12) also play a role in load transmission.

[0016] Unless otherwise defined, the technical terms or scientific terms used in the description of this application shall be the common meanings understood by the general technicians in the field to which this application belongs. In the description of this application, the terms "outer", "inner", "a section", "a level", "import", "export", "axial", "tangential", "inner diameter", "outer diameter", "interlaced", "corresponding", "circumference", "certain", "last", etc. indicate the position or position relationship, which is 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 therefore cannot be understood as limiting the present invention. In addition, "first level", "next level", "step by step", "a module unit", "last level" and similar terms are only used for descriptive purposes to distinguish different components, and cannot be understood as indicating or implying relative importance. The words "one", "a level" and the like used in the description of this application should not be understood as an absolute limitation on the number, but should be understood as the existence of at least one. The words "deflected downward 90 degrees", "horizontally backward" and the like used in the description of this application should not be understood as an absolute limitation on the degree, but should be understood as including "deflected downward 90 degrees" and "horizontally backward". Words such as “including”, “or” and “or” used in the description of this application mean that the elements or objects appearing before 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 specified and limited, the similar words 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 specific circumstances. Description of the Drawings

[0018] Figure 1 It is a schematic diagram of the wing beam frame provided by an embodiment of this application;

[0019] Figure 2 It is a schematic diagram corresponding to the upper cross beam (11) and the lower cross beam (12) provided by an embodiment of this application;

[0020] Figure 3 It is a schematic diagram of the upper cross beam (11) provided by an embodiment of this application;

[0021] Figure 4 It is a schematic diagram of the lower cross beam (12) provided by an embodiment of this application;

[0022] Wherein: 11 - upper cross beam, 12 - lower cross beam, 13 - front wing beam, 14 - rear wing beam.

[0023] In order to better illustrate this embodiment, some components in the drawings are omitted, enlarged or reduced, which does not represent the size 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 Embodiments

[0024] 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.

[0025] The following makes supplementary explanations for this application in conjunction with the drawings;

[0026] Figure 1In an embodiment, the upper crossbeam (11) is respectively connected to the upper parts of the front spar (13) and the rear spar (14), and the lower crossbeam (12) is respectively connected to the lower parts of the front spar (13) and the rear spar (14); the upper crossbeam (11) extends forward close to (or similarly close to or in contact with or relatively close to) the leading edge of the wing and extends backward close to (or similarly close to or in contact with or relatively close to) the trailing edge of the wing; the lower crossbeam (12) extends forward close to (or similarly close to or in contact with or relatively close to) the leading edge of the wing and extends backward close to (or similarly close to or in contact with or relatively close to) the trailing edge of the wing;

[0027] Figure 2 In an embodiment, the corresponding upper crossbeam (11) and lower crossbeam (12) on the wing beam frame form and maintain a specified part (or most part or complete) airfoil (or similar airfoil);

[0028] Figure 3 , 4 In an embodiment, the cross-section of the upper crossbeam (11) is similar to an L shape, is an integral type without breakage, and has high strength; the cross-section of the lower crossbeam (12) is similar to an inverted L shape, is an integral type without breakage, and has high strength; the connection between the wing beam frame and the wing skin panel (or wing skin wall panel or skin assembly) is mainly realized by connecting the upper crossbeam (11) and the lower crossbeam (12) to the wing skin panel (or wing skin wall panel or skin assembly) respectively.

Claims

1. A wing beam, characterized in that, The wing beam frame includes an upper cross beam (11), a lower cross beam (12), a front wing beam (13), and a rear wing beam (14).

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

3. The wing spar according to any one of the preceding claims, characterized in that, The wing beam frame functions to bear the forces and moments of the wing and support other components of the wing such as the wing skin (or wing skin panel or skin assembly).

4. The wing spar according to any one of the preceding claims, characterized in that, The main functions of the front wing beam (13) and the rear wing beam (14) are to bear the bending moment and shear force of the wing.

5. The wing beam frame according to any one of the preceding claims, characterized in that, The front wing beam (13) and the rear wing beam (14) are of integral structure and can be obtained by machining die forgings or die castings.

6. The wing spar according to any one of the preceding claims, characterized in that The upper cross beam (11) and the lower cross beam (12) are the skeletons of the wing in the transverse direction (or similar transverse direction); the upper cross beam (11) and the lower cross beam (12) are of integral structure and can be obtained by machining die forgings or die castings or stampings or extrusions.

7. The wing spar according to any one of the preceding claims, characterized in that, The upper cross beam (11) and the lower cross beam (12) are several (or multiple) (two or more than two).

8. The wing beam according to any one of the preceding claims, characterized in that, The upper cross beam (11) is respectively connected to the upper parts of the front wing beam (13) and the rear wing beam (14), and the lower cross beam (12) is respectively connected to the lower parts of the front wing beam (13) and the rear wing beam (14); the enclosed frame formed by the upper cross beam (11), the front beam (13), the rear beam (14), and the lower cross beam (12) bears the torque of the wing.

9. The wing spar according to any one of the preceding claims, characterized in that, The upper cross beam (11) extends forward close to (or similar to close to or contact or relatively close to) the leading edge of the wing and extends backward close to (or similar to close to or contact or relatively close to) the trailing edge of the wing; the lower cross beam (12) extends forward close to (or similar to close to or contact or relatively close to) the leading edge of the wing and extends backward close to (or similar to close to or contact or relatively close to) the trailing edge of the wing.

10. The wing beam frame according to any one of the preceding claims, characterized in that, The connection between the wing beam frame and the wing skin (or wing skin panel or skin assembly) is mainly achieved by connecting the upper cross beam (11) and the lower cross beam (12) to the wing skin (or wing skin panel or skin assembly) respectively.

Images