Carbon beam composite material wing structure

Abstract

The utility model relates to the technical field of gliders, in particular to a carbon beam composite material wing structure. The airfoil comprises an airfoil main beam and foam layers located at the two ends of the airfoil main beam, the airfoil is of a structure which is thick in the middle and thin at the two ends on the whole, the airfoil main beam and the foam layers are wrapped with a layer of airfoil skin, and the airfoil main beam and the airfoil handle are connected in an inserted mode and fastened through a binder and a bolt; a weight reduction structure is designed in a non-bearing area of the wing handle, so that the overall weight of the structure is reduced; the modulus of the high-modulus carbon fiber main beam can reach 200Gpa, so that the deformation in a bearing state is effectively controlled, and the structural modal of the airfoil is improved; the high-modulus carbon beams and the wing handles are connected in an inserted mode, bonded through epoxy glue and connected in a fastened mode through bolts, and the bearing force of the wing surfaces is effectively transmitted to wing handle connecting points; the outer skin of the airfoil is made of high-strength carbon fiber one-way material, the laying direction and number of fibers are designed according to calculated stress, the 0-degree fiber direction, the 90-degree fiber direction and the + / -45-degree fiber direction are configured, and the torsional strength of the airfoil is improved on the premise that the bearing requirement is met.

Description

Technical Field

[0001] The utility model relates to the technical field of gliders, in particular to a carbon beam composite material wing structure. Background Art

[0002] The weight control of glider wings is an important aspect in glider design, which is directly related to the flight performance, stability and safety of the glider. The following is a detailed analysis of the weight control of glider wings:

[0003] 1. Flight performance: A glider's flight performance, such as glide ratio and flight speed, is affected by wing weight. Lighter wings can reduce overall weight, thereby improving the glider's flight efficiency.

[0004] 2. Stability: The weight distribution of the wings is crucial to the stability of the glider. Proper weight control can ensure that the glider remains stable during flight, avoiding unnecessary turbulence and loss of control.

[0005] 3. Safety: Weight control is also related to the safety of the glider. Overweight wings may increase risks during flight, such as increased impact force during landing.

[0006] In addition, the glider wing surface needs to strictly control the weight while also meeting the dive acceleration load, and the wingtip flutter must be controllable and not affect flight control. However, the existing conventional structure cannot meet the load requirements while meeting the weight requirements. Summary of the Invention

[0007] The purpose of the present invention is to provide a carbon beam composite wing structure for solving at least one of the above technical problems.

[0008] In order to solve the above technical problems, the technical solutions adopted by the present invention are as follows:

[0009] A carbon beam composite wing structure comprises an airfoil and a wing handle. The airfoil comprises an airfoil main beam and foam layers at both ends thereof and has an overall structure that is thick in the middle and thin at both ends. The airfoil main beam and the foam layer are covered with a layer of airfoil skin. The airfoil main beam and the wing handle are plug-connected and fastened by adhesive and bolts.

[0010] Furthermore, a U-shaped slot is provided at one end of the wing handle connected to the wing main beam, and a plug connector matching the U-shaped slot is provided at one end of the wing main beam connected to the wing handle. Adhesive is filled between the slot and the plug connector, and bolts are provided through the slot and the plug connector.

[0011] Furthermore, the wing main beam is made of high modulus carbon fiber composite material, and the wing main beam is connected to the foam layer by an adhesive.

[0012] Furthermore, the wing main beam includes at least two upper cambered layers, a middle area and at least two lower cambered layers, and each layer is connected by an adhesive.

[0013] Furthermore, the laying angles of the fibers in the high modulus carbon fiber are 0°, 90° and ±45°.

[0014] Furthermore, the wing skin is made of high-strength carbon fiber unidirectional material, and the fiber laying angles are 0°, 90° and ±45°.

[0015] Furthermore, the thickness of the wing main beam is 11-16 mm, and the thickness of the outer skin is 0.8-1.2 mm.

[0016] Furthermore, the wing handle is made of 05Cr 17 Ni4Cu4Nb material structure.

[0017] Furthermore, a groove is provided on the wing handle, and the groove is located in a non-load-bearing area of the wing handle.

[0018] Beneficial effects:

[0019] The wing handle in the utility model is designed with a weight-reducing structure in the non-load-bearing area to reduce the overall weight of the structure; the modulus of the high-modulus carbon fiber main beam can reach 200GPa, which effectively controls the deformation under load and improves the structural modulus of the wing surface; the high-modulus carbon beam is plugged into the wing handle and connected by epoxy adhesive and bolt fastening, which effectively transmits the wing surface bearing force to the wing handle connection point; the outer skin of the wing surface is made of high-strength carbon fiber unidirectional material, and the fiber laying direction and quantity are designed according to the calculated force, and the fiber directions of 0°, 90°, and ±45° are configured to improve the torsional strength of the wing surface while meeting the load-bearing requirements.

[0020] The carbon beam composite wing structure design in the present invention can control the wing weight to below 4.5kg; the wing surface deformation control requirements are ≤150mm and 220mm when loaded with 3000N and 45000N at a certain distance from the rotation axis, and the structure is damage-free; the overall wing mode is not less than 21HZ. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the wing structure in the present utility model.

[0022] Figure 2 for Figure 1 The middle AA section diagram is also a diagram of the connection between the wing main beam and the wing handle.

[0023] Figure 3 for Figure 1 Schematic diagram of the middle BB section.

[0024] Figure 4Schematic diagram of the layer structure in the thickness direction of the wing main beam.

[0025] In the figure: 1 wing handle, 2 wing main beam, 201 upper curved surface layer, 202 middle area, 203 lower curved surface layer, 3 foam layer, 4 wing skin, 5 bolts, 6 grooves. DETAILED DESCRIPTION

[0026] The present invention will now be described in further detail with reference to specific embodiments. The following embodiments will enable those skilled in the art to more fully understand the present invention, but these embodiments are not intended to limit the scope of protection of the present invention. The "one embodiment" or "embodiment" referred to herein refers to specific features, structures, or characteristics that may be included in at least one implementation of the present invention. The phrase "in one embodiment" that appears in various places in this specification does not necessarily refer to the same embodiment, nor does it refer to a separate or selective embodiment that is mutually exclusive with other embodiments.

[0027] See also Figures 1 to 4 The carbon beam composite wing structure in the utility model includes an airfoil and a wing handle 1. The airfoil includes an airfoil main beam 2 and foam layers 3 located at both ends thereof and has an overall structure that is thick in the middle and thin at both ends. The airfoil main beam 2 and the foam layer 3 are covered with a layer of airfoil skin 4. The airfoil main beam 2 and the wing handle 1 are plug-connected and fastened by adhesive and bolts 5. The adhesive in this embodiment is epoxy resin adhesive.

[0028] The wing handle 1 in the utility model is made of 05Cr 17 The Ni4Cu4Nb material structure is sequentially milled and solution treated, and is connected and fastened to the wing main beam 2 with bolts 5. The plug-in area between the wing main beam 2 and the wing handle 1 is filled with epoxy glue, which meets the requirements of high strength and high corrosion resistance. In addition, the high modulus carbon beam in this embodiment is plugged into the wing handle 1 with epoxy glue and fastened with bolts 5, which effectively transfers the wing surface bearing force to the connection point of the wing handle 1.

[0029] Specifically, the foam layer 3 in the present invention is made by an integral milling process, with a machining allowance controlled at +0.5 mm, and the material of the foam layer 3 is PET / PMI.

[0030] As a preferred embodiment, the wing handle 1 in this embodiment is provided with a U-shaped plug-in groove at one end connected to the wing surface main beam 2, and the wing surface main beam 2 is provided with a plug-in joint matching the U-shaped groove at one end connected to the wing handle 1. The plug-in groove and the plug-in joint are filled with adhesive, and the bolt 5 passes through the plug-in groove and the plug-in joint. With this structural design, the installation between the wing handle 1 and the wing surface main beam 2 is more convenient, and the wing surface bearing force can be effectively transferred to the connection point of the wing handle 1.

[0031] As a preferred embodiment, the wing main beam 2 in this embodiment is made of a high-modulus carbon fiber composite material, connected to the foam layer 3 by an adhesive. The wing main beam 2 is compression molded using high-modulus carbon fiber epoxy prepreg. The fiber scheme is arranged in layers based on calculations, including at least two upper curved layers 201, a middle region 202, and at least two lower curved layers 203. The layers are connected by adhesive, and the fiber lay angles of the high-modulus carbon fiber are 0°, 90°, and ±45°. The high-modulus carbon fiber main beam in this embodiment can achieve a modulus of 200GPa, effectively controlling deformation under load and improving the wing structure modality.

[0032] As a preferred embodiment, the wing skin 4 in this embodiment adopts high-strength carbon fiber unidirectional material, and the fiber laying angles are 0°, 90° and ±45°. The outer skin of the wing adopts high-strength carbon fiber unidirectional material. The fiber laying direction and quantity are designed according to the calculated force, and the fiber directions are configured at 0°, 90°, and ±45°. Under the premise of meeting the load-bearing requirements, the torsional strength of the wing is improved.

[0033] As a preferred embodiment, the thickness of the wing main beam 2 in this embodiment is 11-16 mm, specifically 11 mm, 12 mm, 13 mm, 14 mm, 15 mm, and 16 mm, and the thickness of the outer skin is 0.8-1.2 mm, specifically 0.8 mm, 0.9 mm, 1.0 mm, 1.1 mm, and 1.2 mm.

[0034] As a preferred embodiment, the wing handle 1 of this embodiment is provided with a groove 6 located in a non-load-bearing area of the wing handle 1. This structural design can reduce the overall weight of the structure while maintaining overall strength. The specific diameter and depth of the groove 6 are determined according to actual needs and can be determined through limited experimentation, so they will not be detailed in this application.

[0035] With the above embodiments of the present invention as inspiration, and through the above description, relevant personnel in this field can make various changes and modifications without departing from the technical concept of this invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention. The technical scope of this invention is not limited to the contents of the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A carbon beam composite wing structure, characterized by: The wing structure includes an airfoil and a wing handle. The airfoil includes an airfoil main beam and foam layers at both ends thereof and has an overall structure that is thick in the middle and thin at both ends. The airfoil main beam and the foam layer are covered with a layer of airfoil skin. The airfoil main beam and the wing handle are plug-connected and fastened by adhesive and bolts.

2. The carbon beam composite wing structure according to claim 1, characterized in that: A U-shaped slot is provided at one end of the wing handle connected to the wing main beam, and a plug connector matching the U-shaped slot is provided at one end of the wing main beam connected to the wing handle. Adhesive is filled between the slot and the plug connector, and bolts are provided through the slot and the plug connector.

3. The carbon beam composite wing structure according to claim 1, characterized in that: The wing main beam is made of high modulus carbon fiber composite material, and the wing main beam is connected to the foam layer by an adhesive.

4. The carbon beam composite wing structure according to claim 1, characterized in that: The wing main beam includes at least two upper cambered layers, a middle area and at least two lower cambered layers, and the layers are connected by adhesive.

5. The carbon beam composite wing structure according to claim 3, characterized in that: The fiber laying angles in high modulus carbon fiber composites are 0°, 90° and ±45°.

6. The carbon beam composite wing structure according to claim 1, characterized in that: The wing skin is made of high-strength carbon fiber unidirectional material, and the fiber laying angles are 0°, 90° and ±45°.

7. The carbon beam composite wing structure according to claim 1, characterized in that: The thickness of the wing main beam is 11-16 mm, and the thickness of the outer skin is 0.8-1.2 mm.

8. The carbon beam composite wing structure according to claim 1, characterized in that: The wing handle is 05Cr 17 Ni4Cu4Nb material structure.

9. The carbon beam composite wing structure according to claim 1, characterized in that: The wing handle is provided with a groove, and the groove is located in the non-load-bearing area of the wing handle.

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