Wing supporting rod structure of airplane

Abstract

The utility model relates to the technical field of aircraft manufacturing, and provides an aircraft wing supporting rod structure which comprises a composite material pipe and two metal joints, and the two metal joints are connected to the two ends of the composite material pipe in a sleeved mode respectively. Wherein the composite material pipe is of a hollow streamline-shaped tubular structure, and the composite material pipe is formed through paving. The hollow streamline-shaped composite material pipe is adopted to replace a traditional metal supporting rod and a supporting rod fairing, and the composite material pipe can play a role in bearing and reducing resistance, so that the supporting rod fairing does not need to be arranged, the assembly difficulty can be reduced, and the assembly time can be shortened; moreover, the composite pipe is formed through paving, so that the material utilization rate can be effectively improved, the processing time is saved, and the structural weight and the manufacturing cost are reduced.

Description

Technical Field

[0001] This utility model relates to the field of aircraft manufacturing technology, and in particular to an aircraft wing strut structure. Background Technology

[0002] In the field of aircraft manufacturing, the wing, as a key component, directly affects the performance, safety, and economy of an aircraft through its structural design and material selection. The wing strut, as an important part of the wing structure, primarily undertakes the tasks of reducing wing root bending moment, simplifying force transmission paths, and ensuring the overall stability of the wing structure. Traditional wing strut structures typically employ a combination of metal struts and strut fairings. Metal struts are widely used due to their high strength and good load-bearing capacity. However, this structure also has several drawbacks. First, metal struts are manufactured through machining, which often requires a large amount of raw materials and generates significant waste during processing, resulting in low material utilization and substantial waste. Second, the precision machining requirements of metal struts increase production costs and time, reducing production efficiency. Furthermore, the relatively large weight of metal struts is a significant disadvantage for modern aircraft that prioritize lightweight design.

[0003] To reduce air resistance caused by the metal struts, traditional designs also install strut fairings on the outside of the struts. While strut fairings can reduce air resistance to some extent, their installation increases the complexity and time cost of wing assembly. At the same time, the strut fairings themselves also increase the weight of the overall structure, further exacerbating the challenges of lightweight design.

[0004] In summary, while existing metal strut and strut fairing combinations can meet basic usage requirements, they have several shortcomings in terms of material utilization, processing cost, processing time, assembly difficulty, assembly time, and overall weight. Therefore, it is necessary to provide a new technical solution to address these issues. Utility Model Content

[0005] This utility model provides an aircraft wing strut structure to address the shortcomings of existing wing strut structures formed by combining metal struts and strut fairings in terms of material utilization, processing cost, processing time, assembly difficulty, assembly time, and overall weight.

[0006] This utility model provides an aircraft wing strut structure, including a composite material tube and metal joints, with two metal joints respectively sleeved at both ends of the composite material tube;

[0007] The composite material tube is a hollow, streamlined tubular structure, and it is formed by laying and pasting.

[0008] According to the wing strut structure of the aircraft provided by this utility model, the metal joint is detachably connected to the composite material tube.

[0009] According to the wing strut structure of the aircraft provided by this utility model, the metal joint includes a tubular connecting part, the cross-sectional shape of the tubular connecting part is adapted to the cross-sectional shape of the composite material tube, and the metal joint is sleeved on the composite material tube through the tubular connecting part.

[0010] According to the wing strut structure of the aircraft provided by this utility model, both the tubular connecting part and the composite material tube are provided with mounting holes, and fasteners are inserted into the mounting holes to achieve a tight connection between the metal joint and the composite material tube.

[0011] According to the wing strut structure of the aircraft provided by this utility model, the outer wall of the tubular connector is provided with a groove, the inner wall of the end of the composite material tube is provided with a buckle, and the metal joint and the composite material tube are engaged with each other through the groove and the buckle.

[0012] According to the wing strut structure of the aircraft provided by this utility model, the tubular connecting part is embedded in the composite material tube.

[0013] According to the aircraft wing strut structure provided by this utility model, the metal joint further includes two connecting lugs. The two connecting lugs are fixed to the tubular connecting part perpendicular to the end face of the tubular connecting part. The two connecting lugs are arranged parallel to each other, and the two connecting lugs are symmetrically provided with connecting holes.

[0014] According to the wing strut structure of the aircraft provided by this utility model, the tubular connecting part is integrally formed with the two connecting lugs.

[0015] According to the aircraft wing strut structure provided by this utility model, the two connecting lugs are arranged at intervals, and the strut structure is connected to the external connector through the connecting lugs.

[0016] According to the wing strut structure of the aircraft provided by this utility model, the composite material tube is a carbon fiber epoxy resin tube.

[0017] The above-mentioned technical solution of this utility model has the following beneficial effects:

[0018] This invention relates to an aircraft wing strut structure that uses a hollow, streamlined composite material tube instead of the traditional metal strut and strut fairing design. The composite material tube serves both a load-bearing function and a drag-reducing function, thus eliminating the need for a strut fairing, reducing assembly difficulty and time, and also reducing the overall weight of the structure. In addition, compared to the machining of traditional metal struts, the composite material tube of this invention, through lay-up molding, can effectively improve material utilization, save processing time, and reduce structural weight and manufacturing costs. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 A schematic diagram of the wing strut structure provided in this embodiment of the utility model;

[0021] Figure 2 This is a schematic diagram of the structure of the composite material tube provided in an embodiment of the present utility model;

[0022] Figure 3 This is a schematic diagram of the structure of a metal connector provided in an embodiment of the present invention.

[0023] Figure label:

[0024] 1. Composite material pipe; 2. Metal joint; 201. Tubular connection part; 202. Connecting lug. Detailed Implementation

[0025] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0026] See Figure 1 and Figure 2This utility model provides an aircraft wing strut structure, including a composite material tube 1 and two metal connectors 2. The two metal connectors 2 are respectively sleeved at both ends of the composite material tube 1, and the strut structure can be connected to other components through the two metal connectors 2. The composite material tube 1 is a hollow, streamlined tubular structure that serves both a load-bearing function and a drag-reducing function. By laying and molding the composite material tube 1, material utilization can be effectively improved, processing time can be saved, and structural weight and manufacturing costs can be reduced.

[0027] The composite material tube 1 can be a carbon fiber epoxy resin tube, but is not limited to this. The metal connector 2 is detachably connected to the composite material tube 1 for easy installation and subsequent replacement.

[0028] The specific process of laying and forming the composite material pipe 1 includes the following steps:

[0029] Step 1: Provide a mold for preparing the composite material tube;

[0030] Step 2: Lay the prepreg on the mold surface in the layup sequence;

[0031] The prepreg includes a reinforcing material and a matrix material. The reinforcing material includes, but is not limited to, at least one of carbon fiber and glass fiber, and the matrix material includes, but is not limited to, at least one of epoxy resin and unsaturated polyester resin.

[0032] Step 3: Wrap heat shrinkable tape around the surface of the prepreg to aid in molding;

[0033] Step 4: Place the laid composite material pipe into the curing oven for overall curing;

[0034] Step 5: After curing is complete, remove the composite material tube from the mold.

[0035] See Figure 1 and Figure 3 The metal connector 2 includes a tubular connecting part 201 and two connecting lugs 202. Both connecting lugs 202 are fixed to the tubular connecting part 201 perpendicular to its end face. The two connecting lugs 202 are arranged parallel to each other, and symmetrical connecting holes are provided on each connecting lug 202. The metal connector 2 is sleeved onto the composite material tube 1 through the tubular connecting part 201. The two connecting lugs 202 are spaced apart from each other, and the strut structure is connected to external connectors through the connecting lugs 202.

[0036] Among them, the metal joint 2 can be machined, and the tubular connecting part 201 and the two connecting lugs 202 are integrally formed, which can improve the structural strength.

[0037] Furthermore, the cross-sectional shape of the tubular connector 201 is adapted to the cross-sectional shape of the composite material tube 1, and the tubular connector 201 can be embedded in the composite material tube 1. This can maintain the smoothness of the outer surface of the strut structure as much as possible, so as to reduce resistance.

[0038] In one embodiment, both the tubular connector 201 and the composite material tube 1 are provided with mounting holes, and fasteners are inserted into the mounting holes to achieve a tight connection between the metal connector 2 and the composite material tube 1.

[0039] In another embodiment, the outer wall of the tubular connector 201 is provided with a groove, and the inner wall of the end of the composite material tube 1 is provided with a buckle. The metal connector 2 and the composite material tube 1 are engaged by the groove and the buckle.

[0040] The wing strut structure of this utility model uses a combination of streamlined composite material tube 1 and metal joint 2, replacing the traditional design of metal strut and strut fairing. The streamlined composite material tube 1 can both bear load and reduce drag, which can effectively improve material utilization, reduce structural weight and manufacturing cost, and ensure normal load transmission. The metal joints 2 at both ends are easy to process and connect, have good interchangeability, and reduce assembly difficulty and time.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A wing strut structure of an aircraft, characterized by, The composite pipe and the metal joint, two of the metal joints are sleeved on two ends of the composite pipe respectively; The composite pipe is a hollow streamline tubular structure, and the composite pipe is formed by laying-up molding.

2. The wing strut structure of an aircraft according to claim 1, characterized by, The metal joint is detachably connected with the composite pipe.

3. The wing strut structure of an aircraft according to claim 1, characterized by, The metal joint comprises a tubular connecting part, the cross-sectional shape of the tubular connecting part is matched with the cross-sectional shape of the composite pipe, and the metal joint is sleeved on the composite pipe through the tubular connecting part.

4. The wing strut structure of an aircraft according to claim 3, characterized in that, The tubular connecting part and the composite pipe are both provided with mounting holes, and a fastener is arranged in the mounting holes to achieve fastening connection of the metal joint and the composite pipe.

5. The wing strut structure of an aircraft according to claim 3, characterized in that, The outer wall of the tubular connecting part is provided with a clamping groove, the inner wall of the end of the composite pipe is provided with a buckle, and the metal joint and the composite pipe are clamped through the clamping groove and the buckle.

6. The wing strut structure of an aircraft according to claim 3, characterized by, The tubular connecting part is embedded in the composite pipe.

7. The wing strut structure of an aircraft according to claim 3, characterized by, The metal joint further comprises two connecting lugs, the two connecting lugs are both fixed on the tubular connecting part perpendicularly to the end face of the tubular connecting part, the two connecting lugs are arranged in parallel to each other, and the two connecting lugs are symmetrically provided with connecting holes.

8. The wing strut structure of an aircraft according to claim 7, characterized in that, The tubular connecting part and the two connecting lugs are integrally formed.

9. The wing strut structure of an aircraft according to claim 7, characterized in that, The two connecting lugs are arranged in spaced relation to each other, and the supporting rod structure is connected with external connecting members through the connecting lugs.

10. The wing strut structure of an aircraft according to claim 1, characterized by, The composite pipe is a carbon fiber epoxy resin pipe.

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