Design method for light metal shear-resistant beam of large unmanned aerial vehicle
By using a lightweight metal shear beam design method for large UAVs, the problem of the lack of standardization in UAV wing spars design was solved, achieving efficient and lightweight structural design, improving utilization and reducing manufacturing costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-12-26
- Publication Date
- 2026-04-03
AI Technical Summary
In the existing technology, there is a lack of unified standards for the design of large UAV wing spars, resulting in low design efficiency, easy structural redundancy, low utilization rate, and increased weight of UAVs.
The design method of lightweight metal shear beam for large UAVs is adopted. By selecting the wing beam material, structural form and cross-sectional form, and combining the finite element parameter adjustment model, the wing beam is initially designed. The structural parameters, including web thickness, flange thickness and fastener diameter, are gradually determined and iteratively checked to meet the strength requirements.
The design of the wing spars structure was standardized and regulated, which improved the structural utilization rate, avoided redundancy, reduced design costs, and reduced the weight of the UAV.
Smart Images
Figure CN121786975A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft structural design, and specifically relates to a design method for a lightweight metal shear beam for large unmanned aerial vehicles. Background Technology
[0002] Drones are well-suited for performing tedious and dangerous tasks. Compared to manned aircraft, drones offer advantages such as ease of use, lower environmental requirements, and greater survivability. As the application scenarios for drones expand and their functions become more diverse, the demands on their payload capacity, size, and weight are also increasing, leading to a continuous trend towards larger drone sizes.
[0003] As the main load-bearing structure of the wing box section, the wing spars run the entire span of the wing. The increasing size requirements of UAVs inevitably lead to an extension of the wing spars span, with spars reaching lengths of 10 meters or more. Compared to the simpler structure and single load-bearing capacity of small UAV wing spars, large UAV wing spars have diverse loads, complex structural features, and numerous coordination relationships. In addition to bearing the bending moment and shear force of the wing, the wing spars of large UAVs also form a closed chamber with other structures to act as a fuel tank and bear the bending moment of the wing. Furthermore, the web of the wing spars often serves as a mounting platform for system components, providing installation pathways for the system. Meeting load-bearing requirements while ensuring matching of structural parameters, coordinated deformation, low weight, and good economic efficiency are important design indicators for large UAV wing spars.
[0004] Currently, there are many types and functions of drones, and there is no unified standard or process for the design of wing spars for large drones. As an important structural component, the design and coordination of wing spars mainly depend on the experience and understanding of designers, resulting in low design efficiency, which is not conducive to the refined design of the structure, easily leads to structural redundancy, low structural utilization, and causes the aircraft to carry excessive weight.
[0005] Therefore, there is an urgent need for a technical solution to overcome or mitigate at least one of the aforementioned defects in the existing technology. Summary of the Invention
[0006] The purpose of this application is to provide a design method for lightweight metal shear beams for large unmanned aerial vehicles (UAVs) to solve at least one problem existing in the prior art.
[0007] The technical solution of this application is:
[0008] A design method for a lightweight metal shear-resistant beam for large unmanned aerial vehicles (UAVs) includes:
[0009] Step S1: Select the wing spade material, wing spade structural form, and wing spade cross-sectional form;
[0010] Step S2: Based on the finite element parameter adjustment model of the wing box section, obtain the shear stress of the beam web, the thickness of the wing skin beam boss element, and the initial cross-sectional area of the wing beam edge bar element.
[0011] Step S3: Perform initial design of the wing beam based on the cross-sectional parameters of the spanwise direction of the wing beam according to the rib position. The wing beam includes upper horizontal flange, lower horizontal flange, upper vertical flange, lower vertical flange, web, inter-rib support, and rib support.
[0012] Step S4: Determine the web thickness t based on the shear stress of the beam web;
[0013] Step S5: Determine the thickness of the horizontal flange strip based on the thickness of the flange skin beam boss unit, including the thickness of the upper horizontal flange strip T1 and the thickness of the lower horizontal flange strip T2;
[0014] Step S6: Determine the fastener diameter d based on the thickness of the flange skin beam boss unit, the thickness of the horizontal flange strip, and the required wall panel countersink depth for the fastener;
[0015] Step S7: Determine the thickness of the vertical flange based on the web thickness and the thickness of the horizontal flange, including the thickness of the upper vertical flange t1 and the thickness of the lower vertical flange t2.
[0016] Step S8: Determine the width of the horizontal flange based on the fastener arrangement and the thickness of the vertical flange, including the upper horizontal flange width W1 and the lower horizontal flange width W2;
[0017] Step S9: Determine the vertical flange height based on the wing sparsity height, including the upper vertical flange height hd1 and the lower vertical flange height hd2;
[0018] Step S10: Determine the cross-sectional area of the horizontal flange by considering the horizontal flange thickness, horizontal flange width, vertical flange thickness, and vertical flange height. This includes the cross-sectional area of the upper horizontal flange S1 and the cross-sectional area of the lower horizontal flange S2. Also, determine whether the cross-sectional area of the horizontal flange is not less than the initial cross-sectional area of the wing beam flange rod unit. If not, return to step S5 and adjust the horizontal flange thickness.
[0019] Step S11: Determine the thickness tr of the rib support based on the web thickness at the rib station location. The height hr of the rib support is consistent with the width of the horizontal flange.
[0020] Step S12: Determine the height hu of the inter-rib support based on the width of the horizontal flange and the diameter of the fastener. The initial value of the inter-rib support thickness tu is given based on experience.
[0021] Step S13: Perform strength verification on the wing spars. Iterate through steps S2-S12 until the strength requirements are met.
[0022] In at least one embodiment of this application, in step S1, the spar material is selected based on load, material properties, manufacturability, economy, and material supply specifications.
[0023] In at least one embodiment of this application, in step S1, the wing beam structure is selected based on load, stiffness, weight, function, manufacturability, and raw material specifications. The wing beam structure is either a composite beam or an integral machined beam.
[0024] In at least one embodiment of this application, in step S1, the wing beam profile is selected according to the load, and the wing beam profile is one of the following: a channel beam, an I-beam, or a J-beam.
[0025] In at least one embodiment of this application, in step S5, the thicknesses of the horizontal flanges T1 and T2 are equal to α × the thickness of the flange skin beam boss unit, where α = 1.0 to 1.2.
[0026] In at least one embodiment of this application, the wing root portion α is 1.1 to 1.2, and the wingtip portion α is 1.0 to 1.1.
[0027] In at least one embodiment of this application, in step S6, the fastener diameter d ≤ (thickness of the wing skin beam boss unit + thickness of the horizontal flange) / 4, and the required wall panel countersink depth for the fastener ≤ 2 / 3 of the wing skin beam boss unit thickness.
[0028] In at least one embodiment of this application, in step S7, the thicknesses of the vertical flanges t1 and t2 = t + (1.5 to 2.5 mm), and t1 and t2 ≤ T1 and T2.
[0029] In at least one embodiment of this application, in step S8, the width of the horizontal flange includes:
[0030] The width of the upper horizontal edge strip is W1 = (2d+1)+3.5d+(d+2)+R+t1;
[0031] The width of the lower horizontal edge strip is W2 = (2d + 1) + 3.5d + (d + 2) + R + t2;
[0032] Where (2d+1) is the fastener edge distance, 3.5d is the fastener row spacing, R is the size of the fillet between the horizontal and vertical flanges, and d is the fastener diameter.
[0033] In at least one embodiment of this application, in step S9, the vertical flange heights hd1 and hd2 are (1 / 6 to 1 / 8)he, where he is the spar height.
[0034] In at least one embodiment of this application, in step S10, the cross-sectional area of the horizontal flange includes:
[0035] The cross-sectional area of the upper horizontal edge strip is S1 = T1 × W1 + (hd1 - T1)t1;
[0036] The cross-sectional area of the lower horizontal edge strip is S2 = T2 × W2 + (hd2 - T2)t2.
[0037] In at least one embodiment of this application, in step S11, the thickness of the rib support tr = (1.1~1.2)t.
[0038] In at least one embodiment of this application, in step S12, the height of the interrib support hu = W1 - (2d + 1), or hu = W2 - (2d + 1).
[0039] The invention has at least the following beneficial technical effects:
[0040] The lightweight metal shear beam design method for large UAVs in this application standardizes and regulates the structural design of the wing spars of large UAVs, which is conducive to improving structural utilization, avoiding structural redundancy, optimizing structural weight reduction, and reducing design and manufacturing costs. Attached Figure Description
[0041] Figure 1 This is a schematic diagram of a wing beam structure according to one embodiment of this application;
[0042] Figure 2 This is a schematic diagram of the parameter definition of the spar component in one embodiment of this application;
[0043] Figure 3 This is a schematic diagram showing the parameter definition of another part of the spar component in one embodiment of this application.
[0044] in:
[0045] 1-Upper horizontal flange; 2-Lower horizontal flange; 3-Upper vertical flange; 4-Lower vertical flange; 5-Web plate; 6-Intercostal support; 7-Rib support. Detailed Implementation
[0046] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.
[0047] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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 limiting the scope of protection of this application.
[0048] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.
[0049] This application provides a design method for a lightweight metal shear-resistant beam for large unmanned aerial vehicles (UAVs), including the following steps:
[0050] Step S1: Select the wing spar material, wing spar structure, and wing spar cross-section.
[0051] In this embodiment, the wing beam material is selected based on the load (the type and magnitude of the load borne by the structure), material properties, manufacturability, economy, and material supply specifications.
[0052] The wing beam structure is selected based on load, stiffness, weight, function, manufacturability, and raw material specifications. The wing beam structure can be a composite beam or a monolithic machined beam. With improved machining capabilities and advantages in load-bearing capacity, weight, sealing, and manufacturing processes, monolithic machined beams are generally chosen. Composite beams can be selected when the flange and web materials are inconsistent, or when there are requirements for material utilization and weight restrictions are relaxed.
[0053] The wing sparification profile is selected based on the load, and can be one of the following: channel beam, I-beam, or J-beam. When the bending moment borne by the wing spar is small, a channel beam is suitable; when the bending moment is large, an I-beam is advantageous. Large UAVs generally have a single-piece wing, where the panel is the main component transmitting bending moment. Since the bending moment borne by the wing spar is relatively small, a channel beam profile can be used. Considering the connection with the ribs, wing sparification, system installation layout, and fasteners connecting the panel and wing spar, the wing spar flanges are turned inwards towards the wing box. This embodiment only uses the design method of a channel beam as an example, which can be used as a reference for the design of I-beams and J-beams.
[0054] Step S2: Based on the finite element parameter adjustment model of the wing box section, obtain the shear stress of the beam web, the thickness of the wing skin beam boss element, and the initial cross-sectional area of the wing beam edge bar element.
[0055] Step S3: Perform initial design of the wing beam based on the cross-sectional parameters of the spanwise direction of the wing beam according to the rib position. The wing beam includes upper horizontal flange 1, lower horizontal flange 2, upper vertical flange 3, lower vertical flange 4, web 5, inter-rib support 6, and rib support 7.
[0056] like Figure 1 As shown, the wing spars are arranged from top to bottom as follows: upper horizontal flange 1, upper vertical flange 3, web 5, lower vertical flange 4, lower horizontal flange 2, inter-rib supports 6, and rib supports 7, all spaced at equal intervals. Inter-rib supports 6 are located on the inner side, and rib supports 7 are located on the outer side. The parameters of this wing spars are defined as follows: Figure 2-3 As shown.
[0057] Step S4: Determine the web thickness t of web 5 based on the shear stress of the beam web.
[0058] Step S5: Determine the thickness of the horizontal flange strip based on the thickness of the flange skin beam boss unit, including the thickness T1 of the upper horizontal flange strip 1 and the thickness T2 of the lower horizontal flange strip 2.
[0059] In this embodiment, the thicknesses of the horizontal flanges T1 and T2 are equal to α × the thickness of the wing skin beam boss unit, where α = 1.0 to 1.2. Specifically, α is 1.1 to 1.2 at the wing root and 1.0 to 1.1 at the wing tip.
[0060] Step S6: Determine the fastener diameter d based on the thickness of the flange skin beam boss unit, the thickness of the horizontal flange strip, and the required wall panel countersink depth for the fastener.
[0061] In this embodiment, the fastener diameter d ≤ (thickness of the wing skin beam boss unit + thickness of the horizontal flange) / 4, and the required wall panel countersink depth for the fastener ≤ 2 / 3 of the wing skin beam boss unit thickness.
[0062] Step S7: Determine the thickness of the vertical flange based on the web thickness and the thickness of the horizontal flange, including the thickness t1 of the upper vertical flange 3 and the thickness t2 of the lower vertical flange 4.
[0063] In this embodiment, the thicknesses of the vertical flanges are t1 and t2 = t + (1.5 to 2.5 mm), and t1 and t2 ≤ T1 and T2.
[0064] Step S8: Determine the width of the horizontal flange according to the fastener arrangement and the thickness of the vertical flange, including the width W1 of the upper horizontal flange 1 and the width W2 of the lower horizontal flange 2.
[0065] In this embodiment, the width W1 of the upper horizontal edge strip 1 is (2d+1)+3.5d+(d+2)+R+t1;
[0066] The width of the lower horizontal edge strip 2, W2, is calculated as follows: W2 = (2d + 1) + 3.5d + (d + 2) + R + t2.
[0067] Where (2d+1) is the fastener edge distance, 3.5d is the fastener row spacing, R is the size of the fillet between the horizontal and vertical flanges, and d is the fastener diameter.
[0068] When the difference between the calculated W1 and W2 is not large, the widths W1 and W2 of the horizontal edge strip can be uniformly selected according to the larger value.
[0069] Step S9: Determine the height of the vertical flange based on the spar height, including the height hd1 of the upper vertical flange 3 and the height hd2 of the lower vertical flange 4.
[0070] In this embodiment, the vertical flange heights hd1 and hd2 are (1 / 6 to 1 / 8)he, where he is the spar height.
[0071] Step S10: Determine the cross-sectional area of the horizontal flange by considering the horizontal flange thickness, horizontal flange width, vertical flange thickness, and vertical flange height. This includes the cross-sectional area S1 of the upper horizontal flange 1 and the cross-sectional area S2 of the lower horizontal flange 2. Then, determine whether the cross-sectional area of the horizontal flange is not less than the initial cross-sectional area of the wing beam flange rod unit. If not, return to step S5 and adjust the horizontal flange thickness.
[0072] In this embodiment, the cross-sectional area of the horizontal flange includes:
[0073] The cross-sectional area of the upper horizontal edge strip 1 is S1 = T1 × W1 + (hd1 - T1)t1;
[0074] The cross-sectional area of the lower horizontal edge strip 2 is S2 = T2 × W2 + (hd2 - T2)t2.
[0075] If S1 and S2 are not less than the initial cross-sectional area of the flange bar element output by the finite element model, then the parameter design is deemed to meet the requirements; otherwise, it is necessary to return to step S5 to adjust the horizontal flange thickness T1 and T2. It is understood that it is also possible to return to step S7 to adjust the vertical flange thickness, thereby adjusting the horizontal flange width W1 and W2 in step S8.
[0076] Step S11: Determine the thickness tr of the rib support 7 based on the web thickness at the rib station location. The height hr of the rib support 7 is consistent with the width of the horizontal flange.
[0077] In this embodiment, the thickness of the rib support 7 is tr = (1.1~1.2)t. The height of the rib support is hr = W1 or W2, and the widths W1 and W2 of the upper and lower horizontal flanges at the rib station are the same.
[0078] Step S12: Determine the height hu of the inter-rib support 6 based on the width of the horizontal flange and the diameter of the fastener. The initial value of the thickness tu of the inter-rib support 6 is given based on experience.
[0079] In this embodiment, the inter-rib supports 6 are arranged at equal intervals, and the number is generally 2. The height of the inter-rib supports hu is determined according to the width of the horizontal flange and the diameter of the fastener, which is either hu = W1 - (2d + 1) or hu = W2 - (2d + 1). The thickness of the rib supports tu is given as an initial value based on experience, which is generally 3 to 5 mm.
[0080] Step S13: Perform strength verification on the wing spars. Iterate through steps S2-S12 until the strength requirements are met.
[0081] Based on the calculation results of the finite element parameter tuning model of the wing box section and the engineering algorithm, the strength calculation is iterated until the strength requirements are met, and the final characteristic parameters of the wing spars are obtained.
[0082] The design method for lightweight metal shear beams of large unmanned aerial vehicles (UAVs) in this application selects the beam material, beam structure, and beam cross-sectional shape. Iterative calculations are performed based on the calculation results of the finite element parameter tuning model of the wing box section to finally obtain the characteristic parameters of the beam that meet the strength requirements.
[0083] This application presents a design method for lightweight metal shear beams for large unmanned aerial vehicles (UAVs). It proposes a complete design method and process for the wing spars of large UAVs, which improves the design efficiency of wing spars, avoids structural redundancy, increases structural utilization, and reduces design and manufacturing costs.
[0084] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.
Claims
1. A design method for a lightweight metal shear beam for large unmanned aerial vehicles (UAVs), characterized in that, include: Step S1: Select the wing spade material, wing spade structural form, and wing spade cross-sectional form; Step S2: Based on the finite element parameter adjustment model of the wing box section, obtain the shear stress of the beam web, the thickness of the wing skin beam boss element, and the initial cross-sectional area of the wing beam edge bar element. Step S3: Perform initial design of the wing beam according to the cross-sectional parameters of the spanwise direction of the wing beam based on the rib position. The wing beam includes upper horizontal flange (1), lower horizontal flange (2), upper vertical flange (3), lower vertical flange (4), web (5), inter-rib support (6), and rib support (7). Step S4: Determine the web thickness t of the web (5) based on the shear stress of the beam web; Step S5: Determine the thickness of the horizontal flange strip based on the thickness of the flange skin beam boss unit, including the thickness T1 of the upper horizontal flange strip (1) and the thickness T2 of the lower horizontal flange strip (2); Step S6: Determine the fastener diameter d based on the thickness of the flange skin beam boss unit, the thickness of the horizontal flange strip, and the required wall panel countersink depth for the fastener; Step S7: Determine the thickness of the vertical flange based on the web thickness and the thickness of the horizontal flange, including the thickness t1 of the upper vertical flange (3) and the thickness t2 of the lower vertical flange (4); Step S8: Determine the width of the horizontal flange according to the fastener arrangement and the thickness of the vertical flange, including the width W1 of the upper horizontal flange (1) and the width W2 of the lower horizontal flange (2); Step S9: Determine the height of the vertical flange according to the height of the wing spars, including the height hd1 of the upper vertical flange (3) and the height hd2 of the lower vertical flange (4); Step S10: Determine the cross-sectional area of the horizontal flange by the thickness of the horizontal flange, the width of the horizontal flange, the thickness of the vertical flange, and the height of the vertical flange, including the cross-sectional area S1 of the upper horizontal flange (1) and the cross-sectional area S2 of the lower horizontal flange (2), and determine whether the cross-sectional area of the horizontal flange is not less than the initial cross-sectional area of the flange rod unit of the wing beam. If not, return to step S5 and adjust the thickness of the horizontal flange. Step S11: Determine the thickness tr of the rib support (7) based on the web thickness at the rib station location. The height hr of the rib support (7) is consistent with the width of the horizontal flange. Step S12: Determine the height hu of the inter-rib support (6) based on the width of the horizontal flange and the diameter of the fastener. The initial value of the thickness tu of the inter-rib support (6) is given based on experience. Step S13: Perform strength verification on the wing spars. Iterate through steps S2-S12 until the strength requirements are met.
2. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 1, characterized in that, In step S1, the wing beam material is selected based on load, material properties, manufacturability, economy, and material supply specifications.
3. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 2, characterized in that, In step S1, the wing beam structure is selected based on load, stiffness, weight, function, manufacturability, and raw material specifications. The wing beam structure can be a composite beam or an integral machined beam.
4. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 3, characterized in that, In step S1, the wing beam profile is selected according to the load. The wing beam profile can be one of the following: channel beam, I-beam, or J-beam.
5. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 4, characterized in that, In step S5, the thicknesses of the horizontal flanges T1 and T2 are equal to α × the thickness of the flange skin beam boss unit, where α = 1.0 to 1.
2.
6. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 5, characterized in that, The α value at the wing root is 1.1 to 1.2, and the α value at the wingtip is 1.0 to 1.
1.
7. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 6, characterized in that, In step S6, the fastener diameter d ≤ (thickness of the flange skin beam boss unit + thickness of the horizontal flange strip) / 4, and the required wall panel countersink depth for the fastener ≤ 2 / 3 of the flange skin beam boss unit thickness.
8. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 7, characterized in that, In step S7, the thicknesses of the vertical flanges t1 and t2 are equal to t + (1.5 to 2.5 mm), and t1 and t2 are less than or equal to T1 and T2.
9. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 8, characterized in that, In step S8, the width of the horizontal flange includes: The width of the upper horizontal edge strip (1) is W1 = (2d+1)+3.5d+(d+2)+R+t1; The width of the lower horizontal edge strip (2) is W2 = (2d + 1) + 3.5d + (d + 2) + R + t2; Where (2d+1) is the fastener edge distance, 3.5d is the fastener row spacing, R is the size of the fillet between the horizontal and vertical flanges, and d is the fastener diameter.
10. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 9, characterized in that, In step S9, the vertical flange heights hd1 and hd2 are (1 / 6 to 1 / 8)he, where he is the spar height.
11. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 10, characterized in that, In step S10, the cross-sectional area of the horizontal flange includes: The cross-sectional area of the upper horizontal edge strip (1) is S1 = T1 × W1 + (hd1 - T1) t1; The cross-sectional area of the lower horizontal edge strip (2) is S2 = T2 × W2 + (hd2 - T2) t2.
12. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 11, characterized in that, In step S11, the thickness of the rib support (7) is tr = (1.1~1.2)t.
13. The design method for lightweight metal shear beams for large unmanned aerial vehicles according to claim 12, characterized in that, In step S12, the height of the interrib support (6) is hu=W1-(2d+1), or hu=W2-(2d+1).