Lightweight solar-powered unmanned aircraft wing rib

Abstract

The utility model relates to a kind of light solar unmanned aerial vehicle wing ribs, including two ultra-thin carbon fiber epoxy resin prepreg, foam core material, the foam core material is clamped between the two ultra-thin carbon fiber epoxy resin prepreg, the foam core material includes rim strip, the rim strip is overall frame type, outer surface smooth transition is used for skin to adhere, middle part is provided with multiple rib, and the air slot is formed between rib, to reduce weight.

Description

Technical Field

[0001] This utility model relates to the field of unmanned aerial vehicles (UAVs), and in particular to a lightweight solar-powered UAV wing rib. Background Technology

[0002] Currently, solar-powered drones are designed for high altitude and long endurance, making structural weight control crucial. Most commonly used solar-powered drone wing rib structures are made of pure fiber lay-up, requiring adhesive reinforcement at weak points, resulting in significant overall weight. Furthermore, because solar panels need to be mounted on the upper edge of the drone, the wing ribs require a sufficiently wide bonding area. Conventional wing rib construction often leads to overly soft bonding surfaces, resulting in weak shape retention at the upper edge and negatively impacting the overall aerodynamic shape. Summary of the Invention

[0003] This utility model provides a lightweight solar-powered drone wing rib, comprising two ultra-thin carbon fiber epoxy resin prepregs and a foam core material. The foam core material is sandwiched between the two ultra-thin carbon fiber epoxy resin prepregs. The foam core material includes a flange strip, which is frame-shaped with a smooth outer surface for skin bonding. Multiple ribs are provided in the middle, and grooves are formed between the ribs to reduce weight.

[0004] Furthermore, the hollow slot includes a support slot for accommodating the main beam and a hollow lightening slot. The support slot matches the shape of the main beam, thereby maintaining a tight fit between the rib and the main beam.

[0005] Furthermore, the thickness of the rib at the connection point with the flange is greater than the thickness of the middle portion.

[0006] Furthermore, the thickness of the ultrathin carbon fiber epoxy resin prepreg is 0.04 mm.

[0007] Because the ribs use a foam sandwich structure, the thickness of the ribs can be increased without increasing the weight, so that the solar panels have sufficient bonding area and the stiffness of the ribs can be improved. At the same time, the overall structural stress is improved by the variable thickness rib design. Attached Figure Description

[0008] Figure 1 This is a diagram showing the usage status of the drone's wing ribs;

[0009] Figure 2 This is a schematic diagram of the wing rib section of the drone;

[0010] Figure 3 This is a schematic diagram of the foam core material structure. Detailed Implementation

[0011] See Figure 1The diagram shows the usage status of the wing rib of the drone. The outer periphery of the wing rib 4 is wrapped with skin 5, which is tightly attached to the outer periphery of the wing rib 4. A main beam 6 is inserted through the middle of the wing rib 4 to provide overall support for the wing.

[0012] See Figure 2 The diagram shows half of the structure of the wing rib 4. The wing rib 4 includes two ultra-thin carbon fiber epoxy resin prepregs (1, 3) and a foam core material 2. The foam core material 2 is sandwiched between the two ultra-thin carbon fiber epoxy resin prepregs (1, 3). The thickness of the ultra-thin carbon fiber epoxy resin prepreg is 0.04 mm.

[0013] Using foam core material 2 can reduce the weight of rib 4. For further weight reduction, see [link to relevant documentation]. Figure 3 The foam core material 2 includes a ferrule 204, which is frame-shaped with a smooth outer surface for skin bonding. Multiple ribs 202 are provided in the middle, forming grooves between them to reduce weight. The grooves include support grooves 201 for accommodating the main beam 6. Figure 3 The diagram shows a portion of the edge structure of the support groove and a hollow weight-reducing groove. The support groove 201 matches the shape of the main beam 6, thereby maintaining a tight fit between the rib and the main beam. The thickness of the rib 202 at the connection portion 203 with the flange 204 is greater than the thickness of the middle portion, that is, the portion near the flange 204 is thicker. This improves structural strength and reduces weight by using less material in the middle portion.

[0014] The lightweight solar-powered drone wing rib structure of this utility model uses a foam sandwich structure to increase the thickness of the wing ribs without increasing the weight, so that the solar panels have sufficient bonding area and the wing rib stiffness is improved. At the same time, the variable thickness rib design improves the stress of the overall structure.

[0015] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended 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 lightweight solar-powered unmanned aerial vehicle (UAV) wing rib, characterized in that, It includes two ultra-thin carbon fiber epoxy resin prepregs (1, 3) and a foam core material (2). The foam core material (2) is sandwiched between the two ultra-thin carbon fiber epoxy resin prepregs (1, 3). The foam core material (2) includes a flange (204). The flange (204) is frame-shaped with a smooth outer surface for skin bonding. Multiple ribs (202) are provided in the middle, and a groove is formed between the ribs (202) to reduce weight.

2. The lightweight solar-powered UAV wing rib according to claim 1, characterized in that, The hollow slot includes a support slot (201) for accommodating the main beam (6) and a hollow lightening slot. The support slot (201) matches the shape of the main beam (6) to maintain a tight fit between the rib and the main beam.

3. The lightweight solar-powered UAV wing rib according to claim 2, characterized in that, The thickness of the rib (202) at the connection portion (203) with the flange (204) is greater than the thickness of the middle portion.

4. The lightweight solar-powered UAV wing rib according to claim 3, characterized in that, The thickness of the ultrathin carbon fiber epoxy resin prepreg is 0.04 mm.

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