Weapon station interface reinforcing structure suitable for composite material cabin framework and design method of weapon station interface reinforcing structure

Abstract

The invention provides a design method and a structure for a local reinforcing structure of a composite cabin framework, and relates to the technical field of reinforcing structures, and the design method comprises the following steps: firstly, carrying out topological optimization analysis according to the overall structure and boundary conditions of the cabin framework and specific local load requirements at weapon station mounting points, and identifying the optimal material distribution and force transmission path of the local load area. And then, based on a topological optimization result, carrying out geometric reconstruction design on the top surface of the cabin framework, and accurately generating a local reinforcing structure which is matched with the optimized force transfer path and meets the manufacturability and assembly interface requirements of a composite material. According to the method, a topological optimization result is guided to a specific and enforceable geometric configuration, the contradiction between the strength and rigidity requirements of the composite material framework in a local large-load area and the structural designability and process feasibility is effectively solved, and the local strength, rigidity and lightweight level of the cabin framework are remarkably improved.

Description

Technical Field

[0001] This invention relates to the technical field of reinforcement structures, and more particularly to a weapon station interface reinforcement structure and its design method applicable to composite material cabin frames. Background Technology

[0002] Composite material cabin frames are widely used in aerospace, special vehicles, and other fields due to their excellent specific strength, specific stiffness, and designability. However, in high-load interface areas such as weapon stations, composite materials face significant challenges: limited by the geometric matching requirements of laminate manufacturing processes and assembly interfaces, such as layup continuity and fiber orientation constraints, their local structures cannot be freely constructed with complex ribs or variable cross-section configurations to achieve efficient force transmission like metallic materials. Traditional design methods often rely on empirical reinforcement schemes, such as local thickening or simple stiffening, which easily leads to structural redundancy, reduced weight reduction, and difficulty in accurately matching load paths. While topology optimization technology can provide theoretical solutions for the optimal material distribution, the constraints of composite material manufacturing processes make it difficult to directly translate into manufacturable geometric features, resulting in a disconnect between optimization results and actual structures. This contradiction means that composite material cabin frames often face the problem of strength redundancy and insufficient stiffness in local high-load areas, limiting weight reduction potential. Therefore, a structural design method that balances the effectiveness of topology optimization and the manufacturability of composite materials is urgently needed. Summary of the Invention

[0003] Based on the above, in high-load interface areas such as weapon stations, composite materials are constrained by the laminate manufacturing process and geometric matching requirements of assembly interfaces, such as layup continuity and fiber orientation constraints. Their local structures cannot freely construct complex ribs or variable cross-section configurations to achieve efficient force transmission, unlike metallic materials. Traditional design methods typically rely on empirical reinforcement schemes, such as local thickening or simple stiffening, which easily leads to structural redundancy, reduced lightweighting, and difficulty in accurately matching load paths. While topology optimization technology can provide a theoretical solution for the optimal material distribution, the constraints of composite material manufacturing processes make it difficult to directly translate into manufacturable geometric features, resulting in a technical problem of decoupling between optimization results and actual structures. Therefore, this paper proposes a design method for weapon station interface reinforcement structures suitable for composite material cabin frames.

[0004] The technical means employed in this invention are as follows: A design method for a weapon station interface reinforcement structure suitable for composite material cabin skeletons, characterized by comprising the following steps: Step 1: Based on the predicted working conditions and combined with the overall structure of the cabin frame, boundary conditions, and local load requirements at the weapon station mounting point, perform topology optimization to identify the optimal material distribution and force transmission path in the local load area. Step 2: Based on the topology optimization results, the top surface of the cabin frame is geometrically reconstructed to generate a local reinforcement structure that matches the optimized force transmission path and meets the requirements of composite material manufacturability and assembly interface.

[0005] Furthermore, the materials of the cabin frame are as follows: unidirectional yarn is made of HF30 grade carbon fiber, fabric is made of HF10 grade reinforced epoxy resin, and medium-temperature epoxy resin curing system; there are 4 orthogonal lay-ups with a single layer curing thickness of 0.55~0.75mm, 6 unidirectional lay-ups with a single layer curing thickness of no more than 0.146mm, the outer fabric lay-up overlap width is 10~20mm, and the inner fabric adopts butt joint arrangement.

[0006] Furthermore, the predicted operating conditions are predicted for both the frontal and lateral directions of the cabin.

[0007] Furthermore, the topology optimization analysis employs one of the following methods: variable density method, level set method, or evolutionary structure optimization method. It uses material distribution density as a variable and maximizes stiffness or minimizes flexibility as the objective function to solve for the optimal force transmission path under the constraints of the local load region. Furthermore, the geometric reconstruction includes: transforming the continuous material distribution generated by topology optimization into discrete geometric features; smoothing the contour, thickness, and transition region of the geometric features according to the constraints of the composite material layup process; and verifying that the reconstructed geometric structure meets the spatial dimensions and connection accuracy requirements of the assembly interface.

[0008] Furthermore, the local reinforcement structure includes one or a combination of a boss, a reinforcing rib, a locally thickened area, or an embedded metal insert, the configuration of which is consistent with the spatial orientation of the force transmission path identified by topology optimization.

[0009] The present invention also includes a weapon station interface reinforcement structure suitable for composite material cabin frames, comprising: An integrated reinforcement region that matches the load path of the weapon station mounting point, wherein the reinforcement region achieves efficient load diffusion to the main body of the cabin frame through geometric configuration changes.

[0010] Furthermore, the composite material layup of the integrated reinforcement region is as follows: a unidirectional layup with a high fiber volume fraction is used in the core area of ​​the force transmission path; a gradually changing layup angle and decreasing layup thickness are used in the transition area; and a continuous transition interface with the main body layup of the cabin frame is set in the boundary area.

[0011] Furthermore, the structure is integrally formed with the main body of the cabin frame through co-curing or secondary bonding processes, and high-precision positioning metal bushings are pre-embedded at the weapon station installation points.

[0012] Compared with the prior art, the present invention has the following advantages: This invention provides a design method for a weapon station interface reinforcement structure applicable to composite material cabin frames. This method effectively resolves the contradiction between the strength and stiffness requirements of composite material frames in local high load areas and the structural designability and process feasibility by guiding the results of topology optimization to specific and feasible geometric configurations. This significantly improves the local strength, stiffness and lightweight level of the cabin frame. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0014] Figure 1 The topology optimization result of the cabin top skeleton for the predicted working conditions in the forward direction of this invention.

[0015] Figure 2 This is the topology optimization result of the cabin top skeleton for predicting working conditions in the lateral direction according to the present invention.

[0016] Figure 3 This is the result of the reconstruction of the top skeleton of the cabin in this invention.

[0017] Among them, 1 is the weapon warfare interface. Detailed Implementation

[0018] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0019] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0020] A design method for a weapon station interface reinforcement structure suitable for composite material cabin frames includes the following steps: First, based on the predicted working conditions and combined with the overall structure of the cabin frame, boundary conditions, and local load requirements at the weapon station mounting point, topology optimization is performed to identify the optimal material distribution and force transmission path in the local load area; then, based on the topology optimization results, the top surface of the cabin frame is geometrically reconstructed to generate a local reinforcement structure that matches the optimized force transmission path and meets the requirements of composite material manufacturability and assembly interface.

[0021] As a preferred embodiment, in this application, the skeleton material is as follows: the unidirectional yarn is made of HF30 grade carbon fiber, the fabric is made of HF10 grade reinforced epoxy resin, and the medium-temperature epoxy resin curing system is used; there are 4 orthogonal lay-ups with a single layer curing thickness of no more than 0.65 mm, 6 unidirectional lay-ups with a single layer curing thickness of no more than 0.146 mm, the outer fabric lay-up overlap width is 10~20 mm, and the inner fabric is arranged by butt joint.

[0022] The predicted operating conditions are respectively for the frontal and lateral directions of the cabin, such as Figure 1 and Figure 2 As shown.

[0023] The topology optimization analysis employs one of the following methods: variable density method, level set method, or evolutionary structure optimization method. It uses material distribution density as a variable and maximizes stiffness or minimizes flexibility as the objective function to solve for the optimal force transmission path under the constraints of the local load region.

[0024] The geometric reconstruction design specifically includes: transforming the continuous material distribution generated by topology optimization into discrete geometric features; smoothing the contour, thickness, and transition region of the geometric features according to the constraints of composite material layup process; and verifying that the reconstructed geometric structure meets the spatial dimensions and connection accuracy requirements of the assembly interface.

[0025] The local reinforcement structure includes one or a combination of bosses, reinforcing ribs, locally thickened areas, or embedded metal inserts, and its configuration is consistent with the spatial orientation of the force transmission path identified by topology optimization.

[0026] The localized reinforcement structure includes an integrated reinforcement region that matches the load path of the weapon station mounting point. This region achieves efficient load diffusion to the main body of the cabin frame through geometric configuration changes, such as... Figure 3 As shown.

[0027] The composite material layup of the integrated reinforcement region includes the following design: a high fiber volume fraction unidirectional layup in the core area of ​​the force transmission path; a gradual layup angle and decreasing layup thickness in the transition area; and a continuous transition interface with the main body layup of the cabin frame in the boundary area.

[0028] The localized reinforcing structure is integrally formed with the main body of the cabin frame through co-curing or secondary bonding processes, and high-precision positioning metal bushings are pre-embedded at the weapon station mounting points.

[0029] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments. In the above embodiments of the present invention, the descriptions of each embodiment have their own emphasis; parts not described in detail in a certain embodiment can be referred to in the relevant descriptions of other embodiments. It should be understood that the disclosed technical content in the several embodiments provided in this application can be implemented in other ways.

[0030] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention 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 or all of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A design method for a weapon station interface reinforcement structure suitable for composite material cabin skeletons, characterized in that, Includes the following steps: Step 1: Based on the predicted working conditions and combined with the overall structure of the cabin frame, boundary conditions, and local load requirements at the weapon station mounting point, perform topology optimization to identify the optimal material distribution and force transmission path in the local load area. Step 2: Based on the topology optimization results, the top surface of the cabin frame is geometrically reconstructed to generate a local reinforcement structure that matches the optimized force transmission path and meets the requirements of composite material manufacturability and assembly interface.

2. The weapon station interface reinforcement structure design method applicable to composite material cabin skeletons according to claim 1, characterized in that, The materials of the cabin frame are: unidirectional yarn is made of HF30 grade carbon fiber, fabric is made of HF10 grade reinforced epoxy resin, medium temperature epoxy resin curing system; there are 4 orthogonal lay-ups with a single layer curing thickness of 0.55~0.75mm, 6 unidirectional lay-ups with a single layer curing thickness of no more than 0.146mm, the outer fabric lay-up overlap width is 10~20mm, and the inner fabric adopts butt joint arrangement.

3. The design method for the weapon station interface reinforcement structure of the composite material cabin frame according to claim 1, characterized in that, The predicted operating conditions are predicted for both the frontal and lateral directions of the cabin.

4. The design method for the weapon station interface reinforcement structure of the composite material cabin frame according to claim 1, characterized in that: The topology optimization analysis employs one of the following methods: variable density method, level set method, or evolutionary structure optimization method. It uses material distribution density as a variable and maximizes stiffness or minimizes flexibility as the objective function to solve for the optimal force transmission path under the constraints of the local load region.

5. The design method for the weapon station interface reinforcement structure of the composite material cabin frame according to claim 1, characterized in that, The geometric reconstruction includes: transforming the continuous material distribution generated by topology optimization into discrete geometric features; smoothing the contour, thickness, and transition region of the geometric features according to the constraints of the composite material layup process; and verifying that the reconstructed geometric structure meets the spatial dimensions and connection accuracy requirements of the assembly interface.

6. The design method for the weapon station interface reinforcement structure of the composite material cabin frame according to claim 1, characterized in that, The local reinforcement structure includes one or a combination of bosses, reinforcing ribs, locally thickened areas, or embedded metal inserts, and its configuration is consistent with the spatial orientation of the force transmission path identified by topology optimization.

7. A weapon station interface reinforcement structure suitable for composite material hull frames, employing the design method described in any one of claims 1-6, characterized in that, include: An integrated reinforcement region that matches the load path of the weapon station mounting point, wherein the reinforcement region achieves efficient load diffusion to the main body of the cabin frame through geometric configuration changes.

8. A weapon station interface reinforcement structure suitable for composite material cabin skeletons according to claim 7, characterized in that, The composite material layup of the integrated reinforcement area is as follows: a high fiber volume fraction unidirectional layup is used in the core area of ​​the force transmission path; a gradual layup angle and decreasing layup thickness are used in the transition area; and a continuous transition interface with the main body layup of the cabin frame is set in the boundary area.

9. A weapon station interface reinforcement structure suitable for composite material cabin skeletons according to claim 7, characterized in that, The structure is integrally formed with the main body of the cabin frame through co-curing or secondary bonding processes, and high-precision positioning metal bushings are pre-embedded at the weapon station installation points.

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