Machine body cylinder section structure

Abstract

The utility model discloses a fuselage cylinder section structure, and belongs to the technical field of fuselage cylinder section structures. A fuselage cylinder section structure comprises: a skin; the transverse reinforcing ribs are spliced with the skin; the first annular rib is horizontally and slidably connected with the skin; the second annular rib is horizontally and slidably connected with the skin; the positioning column is fixed with the second annular rib; wherein the skin comprises a limiting groove; the transverse reinforcing ribs comprise bulges; the bulge is inserted into the limiting groove; the skin is provided with a first sliding groove extending in the axial direction of the skin. The first annular rib and the second annular rib are partially located in the first sliding groove and move along the first sliding groove. The fuselage barrel section structure has the beneficial effect that the fuselage barrel section structure convenient to position is provided.

Description

Technical Field

[0001] This application relates to the technical field of fuselage barrel section structures, and more particularly, to a fuselage barrel section structure. Background Art

[0002] The fuselage barrel section structure is an important part of the aircraft airframe structure. Except for the wing structure, it includes the main structural parts of the aircraft. These structures include cylindrical structures such as the fuselage, nacelle, and tail strut. Their main functions are to load and transmit forces, and at the same time connect key components such as wings, tails, engines, and landing gears together. In addition, the fuselage barrel section can also accommodate crew members and passengers, and load fuel, weapons, instruments, equipment, and goods, etc.

[0003] The fuselage barrel section structure usually consists of a skin and an internal skeleton. The internal skeleton is composed of longitudinal elements (the first annular rib and the second annular rib) and a transverse skeleton (transverse stiffeners). Finally, the above parts are formed into a panel assembly through mechanical connection or bonding, and the panel assembly is then overlapped or butted to form a complete fuselage barrel section structure. Before the internal skeleton is mechanically connected or bonded to the skin, it is necessary to evenly distribute the internal skeleton onto the skin, but the positioning of the internal skeleton is rather troublesome.

[0004] Therefore, a fuselage barrel section structure with convenient positioning is provided. Summary of the Utility Model

[0005] The content part of this application is used to briefly introduce concepts, which will be described in detail in the following detailed implementation part. The content part of this application is not intended to identify the key features or essential features of the claimed technical solution, nor is it intended to limit the scope of the claimed technical solution.

[0006] To solve the technical problems mentioned in the above background art part, some embodiments of this application provide a fuselage barrel section structure, including: a skin; a transverse stiffener inserted into the skin; a first annular rib horizontally slidably connected to the skin; a second annular rib horizontally slidably connected to the skin; a positioning post fixed to the second annular rib; wherein, the skin includes a limiting groove; the transverse stiffener includes a protrusion; the protrusion is inserted into the limiting groove; the skin is provided with a first sliding groove extending along the axial direction of the skin; a part of the first annular rib and the second annular rib is located in the first sliding groove and moves along the first sliding groove.

[0007] Insert the transverse stiffener into the limiting groove, then set the first annular rib at one end of the skin, set the second annular rib in the skin through the first sliding groove, and position it through the positioning post, so that the first annular rib is set at both ends of the skin, and the second annular ribs are equidistantly distributed, then the positioning of the first annular rib, the second annular rib and the transverse stiffener with respect to the skin can be completed, and thus the positioning is more convenient.

[0008] Further, there are two first annular ribs, which are respectively located at both ends of the skin.

[0009] Further, the two first annular ribs are symmetrically arranged.

[0010] Further, the transverse reinforcing rib includes a first positioning portion; the first annular rib includes a second positioning portion; the second positioning portion is used for positioning the first positioning portion.

[0011] Further, there are multiple transverse reinforcing ribs, which are respectively distributed along the circumferential direction of the skin.

[0012] Further, there are multiple second annular ribs, which are respectively distributed along the axial direction of the skin.

[0013] Further, the second annular rib includes a clearance groove; the clearance groove is for the transverse reinforcing rib to pass through.

[0014] Further, there are multiple groups of positioning posts.

[0015] The beneficial effect of this application is that it provides a fuselage barrel section structure that is specifically convenient for positioning. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The drawings constituting a part of this application are used to provide a further understanding of this application, making other features, purposes, and advantages of this application more obvious. The schematic embodiments and descriptions thereof of this application are used to explain this application and do not constitute an improper limitation of this application.

[0017] In addition, throughout the drawings, the same or similar reference numerals represent the same or similar elements. It should be understood that the drawings are schematic and the elements and elements are not necessarily drawn to scale.

[0018] In the drawings:

[0019] Figure 1 is the overall schematic diagram according to the embodiment of this application;

[0020] Figure 2 is the structural schematic diagram of a part of the embodiment, mainly showing the structure of the clearance groove;

[0021] Figure 3 is the structural schematic diagram of a part of the embodiment, mainly showing the structure of the first sliding groove and the limiting groove;

[0022] Figure 4 is the structural schematic diagram of a part of the embodiment, mainly showing the structure of the protrusion;

[0023] Figure 5 is Figure 4 the enlarged view of part A of, mainly showing the structure of the first positioning portion and the second positioning portion.

[0024] Reference numerals:

[0025] 100, fuselage barrel section structure; 101, skin; 101a, limiting groove; 101b, first chute; 102, transverse stiffener;

[0026] 102a, protrusion; 102b, first positioning portion; 103, first annular rib; 103a, second positioning portion; 104, second annular rib; 104a, clearance groove; 105, positioning post. Detailed implementation manners

[0027] Embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although some embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. On the contrary, these embodiments are provided to more thoroughly and completely understand the present disclosure. It should be understood that the drawings and embodiments of the present disclosure are only for exemplary purposes and are not used to limit the protection scope of the present disclosure.

[0028] In addition, it should be noted that for the sake of convenience of description, only parts related to the relevant invention are shown in the drawings. Without conflict, the embodiments in the present disclosure and the features in the embodiments can be combined with each other.

[0029] It should be noted that the concepts such as "first" and "second" mentioned in the present disclosure are only used to distinguish different devices, modules or units, and are not used to limit the order or mutual dependence relationship of the functions performed by these devices, modules or units.

[0030] It should be noted that the modifications of "one" and "multiple" mentioned in the present disclosure are illustrative rather than restrictive. Those skilled in the art should understand that unless otherwise clearly stated in the context, it should be understood as "one or more".

[0031] The present disclosure will be described in detail below with reference to the drawings and in combination with embodiments.

[0032] Referring to Figures 1-5 , a fuselage barrel section structure 100 includes: a skin 101, a transverse stiffener 102, a first annular rib 103, a second annular rib 104, and a positioning post 105. The skin 101 is a ring-shaped structure. The transverse stiffener 102 is inserted into the skin 101. Specifically, the skin 101 includes a limiting groove 101a, and the transverse stiffener 102 includes a protrusion 102a, and the protrusion 102a is inserted into the limiting groove 101a. The first annular rib 103 is horizontally slidably connected to the skin 101. There are two first annular ribs 103, which are respectively located at both ends of the skin 101. The two first annular ribs 103 are symmetrically arranged.

[0033] The second annular rib 104 is horizontally slidably connected to the skin 101. Specifically, the skin 101 is provided with a first sliding groove 101b extending along the axial direction of the skin 101. The first annular rib 103 and the second annular rib 104 are partially located in the first sliding groove 101b and move along the first sliding groove 101b. The positioning post 105 is fixed to the second annular rib 104. There are multiple groups of positioning posts 105.

[0034] Among them, the transverse reinforcing rib 102 includes a first positioning portion 102b, and the first annular rib 103 includes a second positioning portion 103a. The second positioning portion 103a is used for positioning the first positioning portion 102b. The first positioning portion 102b is an L-shaped surface, and the second positioning portion 103a includes an arc surface and an end surface. There are multiple transverse reinforcing ribs 102, which are respectively distributed along the circumferential direction of the skin 101 (which can be distributed according to requirements). There are multiple second annular ribs 104, which are respectively distributed along the axial direction of the skin 101 (which can be distributed according to requirements). The second annular rib 104 includes a clearance groove 104a for the transverse reinforcing rib 102 to pass through. Insert the protrusion 102a of the transverse reinforcing rib 102 into the limit groove 101a, then the first annular rib 103 is arranged inside the skin 101, and abuts against the first positioning portion 102b through the second positioning portion 103a to position one end of the transverse reinforcing rib 102. The second annular rib 104 is arranged inside the skin 101 and is positioned by the positioning post 105, so as to complete the positioning of the transverse reinforcing rib 102, the first annular rib 103 and the second annular rib 104, making the positioning more convenient and facilitating the subsequent bonding of the reinforcing rib, the first annular rib 103 and the second annular rib 104 to the skin 101.

[0035] Workflow: Insert the protrusion 102a of the transverse reinforcing rib 102 into the limit groove 101a, then the first annular rib 103 is arranged inside the skin 101 through the first sliding groove 101b, and abuts against the first positioning portion 102b through the second positioning portion 103a to position one end of the transverse reinforcing rib 102. The second annular rib 104 is arranged inside the skin 101 through the first sliding groove 101b and is equally spaced by the positioning post 105, so as to complete the positioning of the transverse reinforcing rib 102, the first annular rib 103 and the second annular rib 104, making the positioning more convenient. Moreover, the first annular rib 103, the second annular rib 104 and the transverse reinforcing rib 102 form a net-like structure in the inner circle of the skin 101, facilitating the subsequent bonding of the reinforcing rib, the first annular rib 103 and the second annular rib 104 to the skin 101.

[0036] The above description is only some preferred embodiments of the present disclosure and an explanation of the applied technical principles. Those skilled in the art should understand that the scope of the invention involved in the embodiments of the present disclosure is not limited to the technical solutions formed by the specific combination of the above technical features, and should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the above inventive concept. For example, the technical solutions formed by mutually replacing the above features with the technical features (but not limited to) disclosed in the embodiments of the present disclosure that have similar functions.

Claims

1. A fuselage barrel section structure, comprising: Skinning; Features: The fuselage barrel section structure also includes: Transverse stiffeners, plugged into the skin; A first annular rib is horizontally slidably connected to the skin; The second annular rib is horizontally slidably connected to the skin; A positioning column, fixed to the second annular rib; Among them, the skin includes a limiting groove; the transverse reinforcement rib includes a protrusion; the protrusion is inserted into the limiting groove; the skin is provided with a first slide groove extending along the axial direction of the skin; the first annular rib and the second annular rib are partially located in the first slide groove and move along the first slide groove.

2. The fuselage barrel section structure according to claim 1, characterized in that: There are two first annular ribs, which are respectively located at two ends of the skin.

3. The fuselage barrel section structure according to claim 2, characterized in that: The two first annular ribs are symmetrically arranged.

4. The fuselage barrel section structure according to claim 3, characterized in that: The transverse reinforcing rib includes a first positioning portion; The first annular rib includes a second positioning portion; The second positioning portion is used for positioning the first positioning portion.

5. The fuselage barrel section structure according to claim 4, characterized in that: There are a plurality of transverse reinforcing ribs, which are distributed along the circumferential direction of the skin.

6. The fuselage barrel section structure according to claim 5, characterized in that: There are a plurality of second annular ribs, which are respectively distributed along the axial direction of the skin.

7. The fuselage barrel section structure according to claim 6, characterized in that: The second annular rib includes a void avoidance groove; The air avoidance groove is for the transverse reinforcing rib to pass through.

8. The fuselage barrel section structure according to claim 7, characterized in that: The positioning posts are provided in multiple groups.

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