Aircraft model cabin carbon fiber corrugated sandwich wallboard

Abstract

The utility model discloses an aircraft model cabin carbon fiber corrugated sandwich wallboard, the wallboard includes the panel of both sides and sets up the corrugated sandwich layer between two wallboards, the panel is bonded with the corrugated sandwich layer, is provided with the corrugated structure and local reinforcing structure on the corrugated sandwich layer, the corrugated structure with local reinforcing structure staggered uneven arrangement, through above -mentioned scheme, staggered uneven arrangement breaks the homogeneous characteristic of traditional structure, formed the mechanical gradient, and local reinforcing structure directly strengthened the high stress area, and its staggered layout can more effectively guide and disperse load, avoids stress concentration, and the flexible region of not strengthening can absorb impact energy through slight deformation to the overall and local performance of wallboard is improved in coordination.

Description

Technical Field

[0001] This utility model relates to the field of aircraft model wall panel technology, and in particular to a carbon fiber corrugated sandwich wall panel for an aircraft model cabin. Background Technology

[0002] Carbon fiber corrugated sandwich panels represent the cutting edge of aerospace composite material structure design. Through an ingenious "sandwich" configuration, they maximize the superior performance of carbon fiber materials and are one of the key technologies for achieving lightweight and high-performance aircraft. Although there are challenges in terms of cost and manufacturing, their performance advantages in high-end aerospace applications are irreplaceable.

[0003] Existing aircraft model cabin panels mostly use solid laminated panels, foam sandwich panels, or honeycomb sandwich panels. Solid laminated panels are heavy, which is not conducive to weight reduction and performance improvement of model aircraft; foam sandwich panels are lightweight, but lack rigidity, are prone to deformation under aerodynamic loads, and have poor impact resistance; honeycomb sandwich panels have complex manufacturing processes, high costs, and significant anisotropy in the honeycomb structure, resulting in weak load-bearing capacity in specific directions, easy crushing at the edges, and relatively small bonding area with the panel. In addition, traditional homogeneous corrugated sandwich structures are prone to stress concentration when facing localized concentrated loads (such as equipment mounting points), leading to corrugation crushing, affecting structural integrity and safety. Utility Model Content

[0004] The purpose of this utility model is to overcome the shortcomings of the prior art and provide a carbon fiber corrugated sandwich panel for an aircraft model cabin, which is lightweight, has high rigidity and strength, and has excellent local load-bearing capacity and impact resistance.

[0005] The purpose of this utility model is achieved through the following technical solution: a carbon fiber corrugated sandwich panel for an aircraft model cabin, the panel including two side panels and a corrugated sandwich layer disposed between the two side panels, the side panels being bonded to the corrugated sandwich layer, the corrugated sandwich layer being provided with a corrugated structure and a local reinforcing structure, the corrugated structure and the local reinforcing structure being non-uniformly staggered.

[0006] The above scheme breaks the homogeneous characteristics of traditional structures by staggered non-uniform arrangement, forming a mechanical gradient. The locally reinforced structure directly strengthens the high-stress area, while its staggered layout can more effectively guide and disperse the load, avoiding stress concentration. At the same time, the unreinforced flexible area can absorb impact energy through small deformation, thereby synergistically improving the overall and local performance of the wall panel.

[0007] The present invention is further configured such that the corrugated structure is a trapezoidal structure with a uniformly arranged cross-section.

[0008] By employing a trapezoidal wave structure, a flat and wide bonding platform is provided, enhancing the bonding strength with the panel. At the same time, its stable geometry is easy to manufacture and has good shear resistance.

[0009] The present invention is further configured such that the local reinforcing structure is a uniformly intersecting semi-spherical shell structure.

[0010] By adopting a hemispherical shell structure and utilizing the principle of thin shells, the local stiffness is maximized with minimal material cost, effectively resisting pressure from all directions.

[0011] The present invention is further configured such that the local reinforcing structure is a uniformly intersecting semi-elliptical spherical shell structure.

[0012] By adopting a semi-ellipsoidal shell structure, the orientation of the ellipsoid can be adjusted according to the direction of the principal stress, thereby achieving better stiffness and load distribution capability in a specific direction.

[0013] The present invention is further configured such that the distribution density of the local reinforcing structure in the stress concentration portion of the panel is greater than that in the stress non-stress concentration portion of the panel.

[0014] By matching the distribution density of locally reinforced structures with the load distribution, material is allocated as needed, providing the strongest support in critical areas and reducing weight in non-critical areas, thus optimizing structural efficiency.

[0015] The present invention is further configured such that the local reinforcing structure and the corrugated structure are both densely distributed in strips and are arranged in an interlaced manner.

[0016] By densely and interlacedly arranged strips, a continuous and efficient force flow transmission path network is formed within the wall panel, ensuring that local loads can be quickly transferred to the entire wall panel, greatly improving the integrity and resistance to damage of the structure.

[0017] The present invention has the following beneficial effects: the local reinforcement structure acts directly on the stress concentration point, which significantly improves the ability of the wall panel to resist local crushing and deformation, and is particularly suitable for equipment installation and high load areas.

[0018] The interlaced, non-uniform structure forms a collaborative working mechanism between the reinforced and flexible zones. Impact energy can be effectively absorbed by the deformation of the flexible zones, while the spread of damage is limited by the reinforced islands.

[0019] Adding tiny reinforcing structures to the corrugated substrate results in a minimal increase in weight, but in a significant improvement in overall and local rigidity.

[0020] The shape, density, and distribution of the strong structure can be precisely designed and adjusted according to specific load conditions, achieving performance customization and meeting the aircraft model's pursuit of high-performance structures. Attached Figure Description

[0021] Figure 1 This is a plan view of the corrugated structure in an embodiment of this utility model; Figure 2 This is a plan view of a partial reinforcing structure in an embodiment of this utility model; Figure 3 This is a cross-sectional view of the corrugated structure in an embodiment of this utility model; Figure 4 This is a cross-sectional view of a partial reinforcing structure in an embodiment of this utility model; Figure 5 This is a plan view of a preferred embodiment of the local reinforcement structure in this utility model. Figure 6 This is a cross-sectional view of a preferred embodiment of the local reinforcement structure in this utility model.

[0022] In the picture: 1. Corrugated structure; 11. Trapezoidal structure; 2. Locally reinforced structure; 21. Hemispherical shell structure; 22. Hemispherical shell structure. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments 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. The components of the embodiments of this utility model described and shown in the accompanying drawings can typically be arranged and designed in various different configurations.

[0024] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0025] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other.

[0026] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0027] In the description of this utility model, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this utility model is in use, or the orientation or positional relationship commonly understood by those skilled in the art. They are only used for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first," "second," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0028] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0029] The following is in conjunction with the appendix Figure 1-6 The present invention will be described in further detail, but the scope of protection of the present invention is not limited to the following.

[0030] like Figure 1 As shown, a carbon fiber corrugated sandwich panel for an aircraft model cabin includes two side panels and a corrugated core layer disposed between the two side panels. The side panels are bonded to the corrugated core layer. The corrugated core layer is provided with a corrugated structure 1 and a local reinforcement structure 2, which are arranged in an alternating non-uniform pattern. Through the above scheme, the alternating non-uniform arrangement breaks the homogeneous characteristics of the traditional structure and forms a mechanical gradient. The local reinforcement structure 2 directly strengthens the high-stress area, while its alternating layout can more effectively guide and disperse the load, avoiding stress concentration. At the same time, the unreinforced flexible area can absorb impact energy through small deformations, thereby synergistically improving the overall and local performance of the panel.

[0031] In this embodiment: the corrugated structure 1 is a trapezoidal structure 11 with a uniformly distributed cross section; by adopting the trapezoidal corrugated structure, a flat and wide bonding platform is provided, which enhances the bonding strength with the panel. At the same time, its stable geometry is easy to manufacture and has good shear resistance.

[0032] In this embodiment: the local reinforcement structure 2 is a uniformly intersecting semi-spherical shell structure 21; by adopting the semi-spherical shell structure 21, the principle of thin shell is used to maximize the improvement of local stiffness with minimal material cost, and it can effectively resist pressure from all directions.

[0033] In this embodiment: the local reinforcement structure 2 is a uniformly intersecting semi-elliptical spherical shell structure 22; by adopting the semi-elliptical spherical shell structure 22, the ellipsoidal orientation can be adjusted according to the principal stress direction to achieve better stiffness and load dispersion in a specific direction.

[0034] In this embodiment: the distribution density of the local reinforcement structure 2 in the stress concentration part of the panel is greater than that in the stress non-stress concentration part of the panel; by matching the distribution density of the local reinforcement structure 2 with the load distribution, the material is allocated as needed, providing the strongest support in the critical area and reducing the weight in the non-critical area, thereby optimizing the structural efficiency.

[0035] In this embodiment, both the local reinforcing structure 2 and the corrugated structure 1 are arranged in a dense strip pattern and interspersed with each other. Through the dense strip pattern and interspersed arrangement, a continuous and efficient force flow transmission path network is formed in the wall panel, ensuring that the local load can be quickly transmitted to the entire wall panel, which greatly improves the integrity and resistance to damage of the structure.

[0036] At the connection surface between the locally reinforced structure 2 and the corrugated structure 1, a uniformly inclined oblique cut can be made to form a slope surface, thereby increasing the bonding area and improving the force flow transmission.

[0037] In this embodiment: the corrugated structure 2 is a corrugated structure composed of corrugated units with different wave heights, corrugated units with different wave pitches, and corrugated units with different waveforms, and different stress resistance effects are set at different stress locations.

[0038] In summary, this utility model has the following beneficial effects: the local reinforcement structure 2 acts directly on the stress concentration point, which significantly improves the wall panel's ability to resist local crushing and deformation, and is particularly suitable for equipment installation and high-load areas.

[0039] The interlaced, non-uniform structure forms a collaborative working mechanism between the reinforced and flexible zones. Impact energy can be effectively absorbed by the deformation of the flexible zones, while the spread of damage is limited by the reinforced islands.

[0040] Adding tiny reinforcing structures to the corrugated substrate results in a minimal increase in weight, but in a significant improvement in overall and local rigidity.

[0041] The shape, density, and distribution of the strong structure can be precisely designed and adjusted according to specific load conditions, achieving performance customization and meeting the aircraft model's pursuit of high-performance structures.

[0042] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A carbon fiber corrugated sandwich panel for an aircraft model cabin, characterized in that: The wall panel includes two side panels and a corrugated sandwich layer disposed between the two side panels. The side panels are bonded to the corrugated sandwich layer. The corrugated sandwich layer is provided with a corrugated structure (1) and a local reinforcement structure (2). The corrugated structure (1) and the local reinforcement structure (2) are arranged in a non-uniform staggered manner.

2. The carbon fiber corrugated sandwich panel for an aircraft model cabin according to claim 1, characterized in that: The corrugated structure (1) is a trapezoidal structure (11) with a uniformly arranged cross section.

3. The carbon fiber corrugated sandwich panel for an aircraft model cabin according to claim 1, characterized in that: The local reinforcement structure (2) is a uniformly intersecting hemispherical shell structure (21).

4. The carbon fiber corrugated sandwich panel for an aircraft model cabin according to claim 1, characterized in that: The local reinforcement structure (2) is a uniformly intersecting semi-elliptical spherical shell structure (22).

5. The carbon fiber corrugated sandwich panel for an aircraft model cabin according to claim 1, characterized in that: The density of the local reinforcement structure (2) in the stress concentration part of the panel is greater than that in the stress non-stress concentration part of the panel.

6. The carbon fiber corrugated sandwich panel for an aircraft model cabin according to claim 1, characterized in that: The local reinforcement structure (2) and the corrugated structure (1) are both densely distributed in strips and interleaved with each other.

Images