Non-load-bearing internal impact protection support structure for fairings

Abstract

The utility model belongs to the technical field of airplane fairing, disclose a kind of inside anti-impact support structure of non-force fairing, including enclosure frame, horizontal limiting piece and cantilever connecting piece, the circumferential outer shape surface of enclosure frame is matched with the inner shape surface of airplane fairing big end open, horizontal limiting piece is installed in the top of enclosure frame and transversely supports enclosure frame, cantilever connecting piece is arranged in the top of horizontal limiting piece, the outside surface of cantilever connecting piece is contacted with airplane fairing inner wall surface.The utility model has arranged support inside the most dangerous area of cover body impact load, support is connected after completion and is composed of frame structure, fairing is connected in the outside of frame structure, to directly improve the carrying capacity of fairing, realize the stiffness promotion of entire fairing area.Compared with prior art, when fairing is subjected to same load, it is not easy to deform and damage, and service life is greatly improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft fairing technology, and relates to an internal support structure for an aircraft fairing, specifically an internal impact-resistant support structure for a non-load-bearing fairing. Background Technology

[0002] There are many forms of composite fairings, one of which is a tapered variable cross-section design, often used for aerodynamic design at the connection between smaller components and the airframe structure. In existing technology, the fairing that functions as an aerodynamic element at the connection between the float strut and the wing is designed as a single-sided fixed-to-the-float strut, cantilevered design on one side of the wing, influenced by the arrangement of the wing fuel tanks and the aerodynamic shape of the lower surface. Furthermore, due to the large volume of the entire fairing, it is prone to deformation under hydrodynamic impact, leading to localized tearing, detachment, and even flight safety issues. To address the insufficient rigidity of existing fairings, it is necessary to design metal components inside the fairing to provide rigid support. Utility Model Content

[0003] Therefore, this utility model provides an internal shock-resistant support structure for a non-load-bearing fairing, thereby improving the fairing's shock resistance by arranging support components in areas subject to large loads.

[0004] The technical solution of this utility model is as follows: An internal shock-resistant support structure for a non-load-bearing fairing includes a frame, a horizontal limiting member, and a cantilever connector. The circumferential outer surface of the frame matches the inner surface of the open end of the aircraft fairing. The horizontal limiting member is installed above the frame and provides lateral support to the frame. The cantilever connector is located above the horizontal limiting member, and its outer surface contacts the inner wall of the aircraft fairing.

[0005] Furthermore, the frame includes a left strip and a right strip, the outer sides of which match the left inner surface and right inner surface of the large end opening of the aircraft fairing, respectively, and the left strip and the right strip are connected by a horizontal limiting member.

[0006] Furthermore, both the left and right strips are arc-shaped strip structures with an "L"-shaped cross-section.

[0007] Furthermore, the horizontal limiting component is a straight bar structure with an "L" shaped cross-section. There are two horizontal limiting components, which are respectively located at the front and middle-rear sections of the left and right bars.

[0008] Furthermore, there are two cantilever connectors, which are installed above different horizontal limiters.

[0009] Furthermore, the cantilever connector contacts the overlap area of ​​the aircraft fairing, and the cantilever connector is connected to the aircraft fairing via a bracket nut.

[0010] Technical effects: This invention, through load analysis, arranges support components inside the area of ​​the fairing most vulnerable to impact loads. These support components are interconnected to form a frame structure, with the fairing fitted tightly to the outside of this frame. This directly improves the fairing's load-bearing capacity and enhances the rigidity of the entire fairing area. Compared to existing technologies, this makes the fairing less prone to deformation and damage under the same load, significantly extending its service life. Attached Figure Description

[0011] Figure 1 This is a schematic diagram of the overall structure of the support member according to an embodiment of the present utility model; Figure 2 for Figure 1 Exploded view of the structure.

[0012] Figure 3 for Figure 1 A schematic diagram showing the connection relationship between the double-sided surrounding frame and the horizontal limiting component in the structure; Figure 4 for Figure 1 A schematic diagram showing the connection relationship between the cantilever connector and the horizontal limiting component in the structure.

[0013] Among them, 1—frame component, 2—horizontal limiting component, 3—cantilever connector, 4—plate nut, and 5—fairing. Detailed Implementation

[0014] The features and illustrative embodiments of various aspects of this utility model will now be described in detail. Numerous specific design details are set forth in the following detailed description to provide a more complete understanding of this utility model. However, it will be apparent to those skilled in the art that this utility model can be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of this utility model by illustrating examples of it. This utility model is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structure, method, and device without departing from the spirit of this utility model. In the drawings and the following description, any parts not exhaustively described are considered to be common knowledge or conventional practices in the art.

[0015] It should be noted that, where there is no conflict, the embodiments of this utility model and the features therein can be combined with each other, and the various embodiments can be referenced and cited in turn. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0016] Example 1: An internal shock-resistant support structure for a non-load-bearing fairing includes a frame 1, a horizontal limiting member 2, and a cantilever connector 3. The circumferential outer surface of the frame 1 matches the inner surface of the open end of the aircraft fairing. The horizontal limiting member 2 is installed above the frame 1 and provides lateral support to the frame 1. The cantilever connector 3 is located above the horizontal limiting member 2, and its outer surface contacts the inner wall of the aircraft fairing.

[0017] The frame component 1 includes a left strip and a right strip. The outer sides of the left strip and the right strip are respectively matched with the left inner surface and the right inner surface of the open end of the aircraft fairing. The left strip and the right strip are connected by a horizontal limiting component 2.

[0018] Both the left and right strips are arc-shaped strip structures with an "L"-shaped cross-section.

[0019] The horizontal limiting member 2 is a straight bar structure with an "L" shaped cross section. There are two horizontal limiting members 2, which are respectively located at the front and middle-rear sections of the left and right bars.

[0020] There are two cantilever connectors 3, and the two cantilever connectors 3 are installed above different horizontal limiters 2.

[0021] The cantilever connector 3 contacts the overlap of the aircraft fairing, and the cantilever connector 3 is connected to the aircraft fairing through the bracket nut 4.

[0022] Example 2: The embodiments of this utility model are described in detail below, with reference to Figures 1 to 4 The present invention provides an internal support structure for a fairing, which is a combined frame structure with multiple support members overlapping. In one possible implementation, it includes a frame member 1, a horizontal limiting member 2, a cantilever connector 3, and several support plate nuts 4 and flat round head bolts 5; wherein, the flat round head bolts 5 are located outside the fairing and connect the support members to the fairing.

[0023] This invention incorporates support components inside the fairing, forming a frame structure through modular connections. The fairing is then fitted tightly to the outside of this frame structure. This improves the overall rigidity of fairings under water impact loads, enabling the fairing in this example to withstand water impacts without easily deforming. It is applicable to the interior of thin-walled, irregularly shaped fairing structures, achieving water impact resistance while ensuring lightweight fairing and support components. Furthermore, the support component structure is simple and easy to manufacture.

[0024] Specifically, the frame component 1 is located at the most open end of the fairing, consisting of two parts, left and right, both of which are "L" shaped metal parts. Several support plate nuts 4 are pre-embedded on the inner side, and one edge strip on the outer side is attached to the inside of the fairing, while the other edge strip is attached to the horizontal limiting component.

[0025] The horizontal limiting member 2 is an "L"-shaped metal part, which is located above the frame member, and a flange is connected to the two frame members respectively.

[0026] The cantilever connector 3 is an "L"-shaped metal part located on the side of the minimum cross section of the fairing. One flange is connected to the horizontal limiting member 2, and the other flange is fixedly supported by the surrounding cantilever structure.

[0027] like Figure 1 As shown: The two frame components, the horizontal limiting component, and the cantilever connector are connected to form a closed frame structure. The outer side of the frame component and the outer side of the cantilever connector are respectively attached to the inner wall of the fairing.

[0028] like Figure 3 , 4 As shown, at the joints of the frame component 1, the horizontal limiting component 2, and the cantilever connector 3, the overlapping area meets the requirement of at least one row of tray nut connection width.

[0029] The inner surfaces of the overlapping areas of the frame component 1 and the cantilever connector 3 are pre-installed with support plate nuts 4. After the frame is connected, the fairing 6 is connected to the frame by flat round head bolts 5 with aerodynamic shape characteristics.

[0030] The above description is only a preferred embodiment of the present utility model. It should be noted that for those skilled in the art, several improvements can be made without departing from the principle of the present utility model, and these improvements should also be considered within the protection scope of the present utility model.

Claims

1. An internal impact-resistant support structure for a non-load-bearing fairing, characterized in that, It includes a frame (1), a horizontal limiting member (2) and a cantilever connector (3). The circumferential outer surface of the frame (1) matches the inner surface of the large open end of the aircraft fairing. The horizontal limiting member (2) is installed above the frame (1) and supports the frame (1) laterally. The cantilever connector (3) is located above the horizontal limiting member (2). The outer side of the cantilever connector (3) contacts the inner wall of the aircraft fairing.

2. The internal impact-resistant support structure for a non-load-bearing fairing according to claim 1, characterized in that, The frame component (1) includes a left strip and a right strip. The outer sides of the left strip and the right strip are respectively matched with the left inner surface and the right inner surface of the open end of the aircraft fairing. The left strip and the right strip are connected by a horizontal limiting component (2).

3. The internal impact-resistant support structure for a non-load-bearing fairing according to claim 2, characterized in that, Both the left and right strips are arc-shaped strip structures with an "L"-shaped cross-section.

4. The internal impact-resistant support structure for a non-load-bearing fairing according to claim 1, characterized in that, The horizontal limiting component (2) is a straight bar structure with an "L" shaped cross section. There are two horizontal limiting components (2), which are respectively located at the front and middle-rear sections of the left and right bars.

5. The internal impact-resistant support structure for a non-load-bearing fairing according to claim 4, characterized in that, There are two cantilever connectors (3), and the two cantilever connectors (3) are installed above different horizontal limiters (2).

6. The internal impact-resistant support structure for a non-load-bearing fairing according to claim 1, characterized in that, The cantilever connector (3) contacts the overlap of the aircraft fairing, and the cantilever connector (3) is connected to the aircraft fairing through the bracket nut (4).

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