Ribbed wallboard design method based on loading capacity

Abstract

The invention belongs to the field of design and calculation of aircraft wing stiffened wallboards, and particularly relates to a stiffened wallboard design method based on loading capacity, which comprises the following steps: S1, selecting equivalent thickness, stringer spacing, rib spacing and weight coefficient; s2, selecting a stringer profile parameter and a skin thickness based on the weight coefficient; s3, the load capacity is calculated; s4, when the load capacity meets the preset requirement, outputting the structural efficiency and the design parameters, and skipping to S5; otherwise, increasing the weight coefficient by a preset value, and returning to the step S2; and S5, when the equivalent thickness and the design parameters are smaller than the corresponding limit values, adding the corresponding step lengths to the equivalent thickness and the design parameters respectively, and skipping to the step S1, otherwise, ending the circulation, and listing the output values into a reference table for designing the stiffened wallboard.

Description

Technical Field

[0001] The present application belongs to the field of design and calculation of aircraft wing stiffened panels, and in particular to a stiffened panel design method based on pressure bearing capacity. Background Art

[0002] In the current aircraft structure design process, the calculation of the bearing capacity of the stiffened wall panel is used for strength verification in the detailed design stage, so the structural strength is calculated under a specific parameter (the spacing between the long girders, the rib spacing, and the long girders section parameters are all determined). If the structural strength does not meet the strength or weight index requirements, it is necessary to redesign the parameters or even return to the preliminary design stage to adjust the structural layout, which will cause a lot of rework and affect the aircraft design cycle.

[0003] In the calculation of the bearing capacity of the stiffened wall panel, the buckling instability of the skin and the column strength are controlled separately as design boundaries, and the correlation between buckling instability and column strength is not studied. Although the concept of effective skin width is used, in the calculation of bearing capacity, only the long stringer area and the effective skin area are used as the calculation units of bearing capacity, while other skin structures that can bear the critical buckling load are ignored. Therefore, the calculation results are relatively conservative, and the error with the test results is more than 10%.

[0004] The present invention can carry out structural layout optimization work under limited design input in the structural scheme design stage, and analyze the influence of rib spacing and long truss spacing on the bearing capacity of the wall panel. The bearing capacity of the wall panel is optimized based on the local stability of the skin, column strength, and full stress multiple design constraints.

[0005] The new concepts proposed in this invention: load concentration, equivalent thickness, weight coefficient, and structural efficiency, eliminate the influence of the inherent characteristics of the actual wing box width and height in the calculation, and use the unit chord load concentration and allowable stress as design inputs to calculate the equivalent thickness interval T[T min ,T max ]. The equivalent thickness T is a representation of both load concentration and material distribution. The concept of weight coefficient is used to describe the increase in structural area. The weight coefficient and structural efficiency are reciprocal, which is used to evaluate structural efficiency.

[0006] In the wall panel bearing capacity calculation method of the present invention, a comprehensive effect based on the skin anti-buckling capacity and the wall panel post-buckling capacity is proposed, and the calculation result is closer to the actual load distribution.

[0007] The present invention reasonably limits the stiffness matching between the stringer and the skin by designing the cross-section parameters of the stringer, so that the stringer does not locally buckle under the extreme load, and the stringer does not buckle before the skin, and the stringer provides the minimum stiffness requirement for the skin to be simply supported, thereby establishing a dynamic correlation between the area ratio of the stringer and the skin. Summary of the invention

[0008] In order to solve the above problems, the present application provides a design method of reinforced wall panels based on pressure bearing capacity, including:

[0009] Step S1: Selecting the equivalent thickness, truss spacing, rib spacing and weight coefficient required for designing the aircraft wing stiffened panel;

[0010] Step S2: selecting the cross-section parameters of the long stringer and the skin thickness based on the weight coefficient;

[0011] Step S3: calculating the critical instability stress of the skin, the compression failure stress of the stiffened wall panel and the ultimate working stress according to the equivalent thickness, the spacing between the long girders, the spacing between the ribs, the cross-section parameters of the long girders and the thickness of the skin;

[0012] Step S4: when the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel and the ultimate working stress meet the preset requirements, the structural efficiency and the skin area ratio of the long stringer are calculated and output, the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel, the skin thickness and the weight coefficient are output, and the process jumps to step S5;

[0013] When the preset requirement is not met, the weight coefficient is increased by a preset value, and the process returns to step S2;

[0014] Step S5: When the equivalent thickness, the spacing between long girders or the spacing between ribs are all less than their corresponding limit values, the equivalent thickness, the spacing between long girders or the spacing between ribs are respectively added with their corresponding step lengths, and the process jumps to step S1; otherwise, the loop ends, and the output values ​​are listed as a reference table for designing stiffened wall panels.

[0015] Preferably, the method for selecting the equivalent thickness includes:

[0016] Obtain the external loads on the wing, and divide the external loads by the wing box cross-sectional areas at different wing positions to obtain the load concentration interval per unit length along the chord direction at the wing rib position;

[0017] The load concentration interval is divided by the allowable stress of the stiffened wall panel structure to obtain the equivalent thickness interval, the minimum value of the equivalent thickness interval is used as the initial equivalent thickness in step S1, and the maximum value of the equivalent thickness interval is used as the limit value corresponding to the equivalent thickness in step S5.

[0018] Preferably, the method for selecting the long-truss spacing and the rib spacing includes: setting a long-truss spacing range value and a rib spacing range value;

[0019] The minimum value of the truss spacing range is used as the initial value of the truss spacing in step S1, and the maximum value of the truss spacing range is used as the limiting value corresponding to the truss spacing in step S5;

[0020] The minimum value of the rib spacing range is used as the initial value of the rib spacing in step S1, and the maximum value of the rib spacing range is used as the limiting value corresponding to the rib spacing in step S5.

[0021] Preferably, the calculation formula for the compressive failure stress of the reinforced wall panel is:

[0022] N 轴力 =∫ A有效宽度壁板面积 σ co +∫ A剩余蒙皮面积 σ cr ;

[0023] σ 压缩破坏 =N 轴力 / A 总面积 ;

[0024] Among them, σ 压缩破坏 is the destructive strength of the typical long-strand spacing reinforced wall panel, N 轴力 A is the axial force that the inner wall plate can bear within the long truss spacing. 总面积 is the cross-sectional area of ​​the inner wall plate within the long stringer spacing, σ co is the column strength of the stiffened slab with effective width, σ cr is the skin instability stress, A 有效宽度壁板面积 is the area of ​​the inner wall panel within the effective width, A 剩余蒙皮面积 The skin area where instability occurs.

[0026] Preferably, selecting the long stringer section parameters specifically includes: selecting the long stringer section type and the long stringer section size.

[0027] Preferably, the cross-section types of the long stringer include: I-shaped, T-shaped, Z-shaped, hat-shaped or J-shaped.

[0028] Preferably, the cross-sectional dimensions of the I-shaped long stringer include: long stringer height bw, long stringer web thickness tw, lower flange thickness ta, lower flange width ba, upper flange width bf, and upper flange thickness tf.

[0029] Preferably, the cross-sectional dimensions of the I-shaped long stringer are in the range of: when the average height of the wing box is H≥1000mm, bw=0.04~0.06H; when 1000>H≥600mm, bw=0.06~0.1H; when H<600mm, bw=0.09~0.13H; and bw=0.2~0.4bs; tw is 0.6~1ts (and (tw / bw) / (ts / bs)≥k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts; bf takes a value between 0.35bw and 0.5bw, and tf takes a value between 1ts and 1.2ts.

[0030] Preferably, the cross-sectional dimensions of the T-shaped long stringer are in the range of: when the average height of the wing box is H≥1000mm, bw=0.04-0.06H; when 1000>H≥600mm, bw=0.06-0.1H; when H<600mm, bw=0.09-0.13H; and bw=0.2-0.4bs; tw is 0.6-1ts (and (tw / bw) / (ts / bs)≥k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts.

[0031] Preferably, the load concentration Q=M / A, M is the wing box bending moment at the current station position, and A is the wing box cross-sectional area.

[0032] Preferably, T = Q / σ ad ;

[0033] σ ad is the allowable stress and T is the equivalent thickness.

[0034] Preferably, K w =T 壁板需求厚度 / T;

[0035] K w is the weight coefficient, T 壁板需求厚度 The thickness of the reinforced wall panel meets the design requirements.

[0036] The advantages of this application include: the present invention can carry out structural layout optimization work under limited design input in the structural scheme design stage, and analyze the influence of rib spacing and long truss spacing on the bearing capacity of the wall panel. The bearing capacity of the wall panel is optimized based on the local stability of the skin, column strength, and full stress multiple design constraints.

[0037] The new concepts proposed in this invention: load concentration, equivalent thickness, weight coefficient, and structural efficiency, eliminate the influence of the inherent characteristics of the actual wing box width and height in the calculation, and use the unit chord load concentration and allowable stress as design inputs to calculate the equivalent thickness interval T[T min ,T max]. The equivalent thickness T is a representation of both load concentration and material distribution. The concept of weight coefficient is used to describe the increase in structural area. The weight coefficient and structural efficiency are reciprocal, which is used to evaluate structural efficiency.

[0038] In the wall panel bearing capacity calculation method of the present invention, a comprehensive effect based on the skin anti-buckling capacity and the wall panel post-buckling capacity is proposed, and the calculation result is closer to the actual load distribution.

[0039] The present invention reasonably limits the stiffness matching between the girder and the skin by designing the cross-section parameters of the girder as shown in Table 1, so that the girder does not buckle locally under the extreme load, and the girder does not buckle before the skin, and the girder provides the minimum stiffness requirement for the skin to be simply supported, thereby establishing a dynamic correlation between the area ratio of the girder and the skin. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] Figure 1 This is a flow chart of a method for designing a reinforced wall panel based on pressure bearing capacity in a preferred embodiment of the present application.

[0041] Figure 2 It is a schematic diagram of the load-bearing of the wing box wall panel of the present application;

[0042] Figure 3 It is a schematic diagram of load distribution of the wall panel of the present application after being subjected to axial compression;

[0043] Figure 4 This is a schematic diagram of the overall "I"-shaped reinforced wall panel of this application;

[0044] Figure 5 It is a schematic diagram of the overall "T"-shaped reinforced wall panel of this application. DETAILED DESCRIPTION

[0045] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be further described in detail in detail and in detail in conjunction with the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments in the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0046] Before the present application method, the parameters used in the present application are explained, such as Figure 2 As shown:

[0047] Load concentration Q: The wing bending moment is distributed along the span direction. The load concentration per unit length along the chord direction at the wing rib station is: Q = M / (B×H) = M / A. Where M is the wing box bending moment at the current station, B is the current occupied wing box width, H is the average height of the wing box at the current station, and A is the cross-sectional area of ​​the wing box. M, B, H, and A are all variable quantities in the extension direction. The calculation of Q can determine the unit chord length load magnitude interval Q[Q min ,Q max ] to reflect the load magnitude distribution of the wing panel.

[0048] Equivalent thickness T: Equivalent thickness T and allowable stress of stiffened panel structure (σ ad ) is associated with T = Q / σ ad The equivalent thickness T of the wall panel refers to the thickness at full stress (i.e. when the structural load reaches the allowable stress σ ad ) state, including the skin area (A 蒙皮 ) and the area of ​​the stringer (A 长桁 ) is equivalent to the sum of the thickness, T = (A 蒙皮 +A 长桁 ) / Bs, where Bs is the truss spacing. The two formulas of equivalent thickness T show that equivalent thickness T is both a representation of load concentration and a representation of material distribution. Similarly, equivalent thickness T along the wing span is also expressed as an interval T[T min ,T max ].

[0049] Weight factor K w : Taking the equivalent thickness under full stress as the base number, the wall panel thickness required for no local instability and damage of the skin under the specified load (generally, the load conditions corresponding to instability and damage are different. Some aircraft require no skin instability under the limit load and no damage under the limit load) is the design required thickness. The ratio of the two is defined as the weight coefficient. The formula is derived as follows. The influence of the wing box width is eliminated in the formula, and only the thickness ratio is used to express the growth ratio of the wall panel area to measure the weight cost. In addition to using parameters such as wing box width and height when calculating the wall panel load concentration, this method has eliminated the correlation between wing box width and height in the formula in subsequent calculations and evaluations. Therefore, the calculation results have universal characteristics and are applicable to wings of different sizes.

[0050] K w =(A 壁板需求面积 ×ρ 材料密度 ) / (A 壁板当量面积 ×ρ 材料密度 )

[0051] =(T 壁板需求厚度 ×B 翼盒宽度 ×ρ 材料密度 ) / (T壁板当量厚度 ×B 翼盒宽度 ×ρ 材料密度 )

[0052] =T 壁板需求厚度 / T 壁板当量厚度

[0053] Structural efficiency K e :K e =σ 工作应力 / σ ad , defined as the working stress and full stress (i.e. allowable stress σ ad ), K e The smaller the value, the lower the structural efficiency and the lower the bearing capacity of the structure.

[0054] Cause: σ 工作应力 ×A 壁板需求面积 =σ ad ×A 壁板当量面积 ,

[0055] K e =σ 工作应力 / σ ad =A 壁板当量面积 / A 壁板需求面积

[0056] Then: =(T 壁板当量厚度 ×B 翼盒宽度 ) / (T 壁板需求厚度 ×B 翼盒宽度 ).

[0057] =T 壁板当量厚度 / T 壁板需求厚度 =1 / K w

[0058] The formula shows that the weight coefficient and structural efficiency are reciprocals of each other. The weight coefficient can reflect the structural efficiency. The larger its value, the greater the weight cost and the lower the structural efficiency.

[0059] like Figure 1 As shown in Figure 1, a design method for reinforced wall panels based on pressure bearing capacity is proposed.

[0060] Weight factor K w It can be used to measure the structural efficiency of different long-string spacing, rib spacing (layout optimization), different long-string forms and section parameters (parameter optimization).

[0061] Based on the above parameters, the design method of reinforced wall panels based on pressure bearing capacity of this application is obtained:

[0062] Step S1: Selecting the equivalent thickness, truss spacing, rib spacing and weight coefficient required for designing the aircraft wing stiffened panel;

[0063] Step S2: selecting the stringer section parameters and the skin thickness based on the weight coefficient; that is, reallocating the stringer and skin parameters based on the current thickness (equivalent thickness×weight coefficient);

[0064] Step S3: calculating the critical instability stress of the skin, the compression failure stress of the stiffened wall panel and the ultimate working stress according to the equivalent thickness, the spacing between the long girders, the spacing between the ribs, the cross-section parameters of the long girders and the thickness of the skin;

[0065] Step S4: when the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel and the ultimate working stress meet the preset requirements, the structural efficiency and the skin area ratio of the long stringer are calculated and output, the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel, the skin thickness and the weight coefficient are output, and the process jumps to step S5;

[0066] When the preset requirement is not met, the weight coefficient is increased by a preset value, and the process returns to step S2;

[0067] Step S5: When the equivalent thickness, the spacing between long girders or the spacing between ribs are all less than their corresponding limit values, the equivalent thickness, the spacing between long girders or the spacing between ribs are respectively added with their corresponding step lengths, and the process jumps to step S1; otherwise, the loop ends, and the output values ​​are listed as a reference table for designing stiffened wall panels.

[0068] Preferably, the method for selecting the equivalent thickness includes:

[0069] Obtain the external loads on the wing, and divide the external loads by the wing box cross-sectional areas at different wing positions to obtain the load concentration interval per unit length along the chord direction at the wing rib position;

[0070] The load concentration interval is divided by the allowable stress of the stiffened wall panel structure to obtain the equivalent thickness interval, the minimum value of the equivalent thickness interval is used as the initial equivalent thickness in step S1, and the maximum value of the equivalent thickness interval is used as the limit value corresponding to the equivalent thickness in step S5.

[0071] Preferably, the method for selecting the long-truss spacing and the rib spacing includes: setting a long-truss spacing range value and a rib spacing range value;

[0072] The minimum value of the truss spacing range is used as the initial value of the truss spacing in step S1, and the maximum value of the truss spacing range is used as the limiting value corresponding to the truss spacing in step S5;

[0073] The minimum value of the rib spacing range is used as the initial value of the rib spacing in step S1, and the maximum value of the rib spacing range is used as the limiting value corresponding to the rib spacing in step S5.

[0074] Preferably, the calculation method of the compressive failure stress of the reinforced wall panel is:

[0075] When the wall panel is subjected to axial compression, the load distribution on the cross section changes greatly with the increase of stress level. Before the skin buckles, the load on the cross section is evenly distributed. After the skin buckles, the load gradually concentrates on the ribs. The skin is supported by the long stringer. The closer to the long stringer, the higher the load-bearing capacity of the skin. Figure 3 shown.

[0076] The traditional method for calculating the bearing capacity of the wall panel is to equate the bearing capacity of the wall panel to the column strength of the wall panel within the effective skin width, and only calculate the bearing capacity of the shadow area I, that is,

[0077] N 轴力 =∫ A有效宽度壁板面积 σ co .

[0078] The method described in this patent is based on the combined effect of the skin anti-buckling capacity and the wall panel post-buckling capacity, and calculates the comprehensive bearing capacity of the shadow area I and the shadow area II:

[0079] N 轴力 =∫ A有效宽度壁板面积 σ co +∫ A剩余蒙皮面积 σ cr ;

[0080] σ 压缩破坏 =N 轴力 / A 总面积 .

[0081] Among them, σ 压缩破坏 is the destructive strength of the typical long-strand spacing reinforced wall panel, N 轴力 A is the axial force that the inner wall plate can bear within the long truss spacing. 总面积 is the cross-sectional area of ​​the inner wall plate between the long girders, σ co is the column strength of the stiffened slab with effective width, σ cr is the skin instability stress, A 有效宽度壁板面积 is the area of ​​the inner wall panel within the effective width, A 剩余蒙皮面积 The skin area where instability occurs.

[0082] Selecting the cross-section parameters of the long stringer and the thickness of the skin based on the weight coefficient; wherein selecting the cross-section parameters of the long stringer specifically includes: selecting the cross-section type of the long stringer and the cross-section size of the long stringer. The cross-section types of the long stringer include: I-shaped, T-shaped, Z-shaped, hat-shaped or J-shaped. The cross-section size of the I-shaped long stringer includes: the height of the long stringer bw, the thickness of the web of the long stringer tw, the thickness of the lower flange ta, the width of the lower flange ba, the width of the upper flange bf, and the thickness of the upper flange tf.

[0083] The selection constraints of the stringer section parameters and skin thickness are in addition to the weight coefficient, such as Figure 4-Figure 5 Also includes:

[0084] The range of the cross-section size of the I-shaped long girder is: when the average height of the wing box is H ≥ 1000mm, bw = 0.04 ~ 0.06H; when 1000> H ≥ 600mm, bw = 0.06 ~ 0.1H; when H < 600mm, bw = 0.09 ~ 0.13H; and bw = 0.2 ~ 0.4bs; tw takes the value of 0.6 ~ 1ts (and (tw / bw) / (ts / bs) ≥ k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts; bf takes a value between 0.35bw and 0.5bw, and tf takes a value between 1ts and 1.2ts.

[0085] The range of the cross-sectional dimensions of the T-shaped long stringer is: when the average height of the wing box is H ≥ 1000mm, bw = 0.04 ~ 0.06H; when 1000> H ≥ 600mm, bw = 0.06 ~ 0.1H; when H < 600mm, bw = 0.09 ~ 0.13H; and bw = 0.2 ~ 0.4bs; tw takes the value of 0.6 ~ 1ts (and (tw / bw) / (ts / bs) ≥ k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts.

[0086] Through the above-mentioned design of the long stringer section parameters, the stiffness matching between the long stringer and the skin is reasonably limited, so that the long stringer does not buckle locally under the extreme load, and the long stringer does not buckle before the skin, and the long stringer provides the minimum stiffness requirement for the skin to be simply supported, as shown in the following formula:

[0087]

[0088] Through the design of the long stringer section parameters, the long stringer to skin area ratio (A 长桁面积 / A 蒙皮面积 ) is not a simple ratio range (generally designed to be 0.4 to 0.6). This ratio changes with the changes in the cross-section form and spacing of the long stringers. The long stringer stiffness requirement is a constraint, the long stringer cross-section design is a process, and the long stringer to skin area ratio is the result. The traditional design uses the long stringer to skin area ratio as the design input and constraint.

[0089] Preferably, the load concentration Q=M / A, M is the wing box bending moment at the current station position, and A is the wing box cross-sectional area.

[0090] Preferably, T = Q / σ ad ;

[0091] σ ad is the allowable stress and T is the equivalent thickness.

[0092] Preferably, K w =T 壁板需求厚度 / T;

[0093] K w is the weight coefficient, T 壁板需求厚度 The thickness of the reinforced wall panel meets the design requirements.

[0094] Case: Taking a certain type of aircraft wing as the research object, the equivalent thickness range is calculated by external load as T[1,10]. The optimization range is 140~180 for the truss spacing and 600~800 for the rib spacing. The “I” shaped section is selected for the truss. The specific parameters are shown in the table below.

[0095] 1. Design input see Table 1:

[0096] Table 1 Case input table

[0097]

[0098] 2. Design constraints:

[0099] The design of reinforced wall panels must meet the following requirements:

[0100] a) The skin cannot buckle under the limit load, i.e. 1.5σ cr ≥σ 极限工作应力 ;

[0101] b) The reinforced wall panel does not fail under the ultimate load, that is, σ 压缩破坏 ≥σ 极限工作应力 ;

[0102] c) Full stress requirement: σ 极限工作应力 ≤370Mpa;

[0103] 3. Output parameters:

[0104]

[0105] The calculation results are shown in Table 2.

[0106] Table 2 Case output table

[0107]

[0108]

[0109]

[0110]

[0111]

[0112] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A design method for reinforced wall panels based on pressure bearing capacity, characterized in that: include: Step S1: Select the equivalent thickness, truss spacing, rib spacing and weight coefficient required for designing the aircraft wing stiffened panel; Step S2: selecting the cross-section parameters of the long stringer and the skin thickness based on the weight coefficient; Step S3: calculating the critical instability stress of the skin, the compression failure stress of the stiffened wall panel and the ultimate working stress according to the equivalent thickness, the spacing between the long girders, the spacing between the ribs, the cross-section parameters of the long girders and the thickness of the skin; Step S4: when the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel and the ultimate working stress meet the preset requirements, the structural efficiency and the skin area ratio of the long stringer are calculated and output, the critical instability stress of the skin, the compressive failure stress of the stiffened wall panel, the skin thickness and the weight coefficient are output, and the process jumps to step S5; When the preset requirement is not met, the weight coefficient is increased by a preset value, and the process returns to step S2; Step S5: When the equivalent thickness, the spacing between long girders or the spacing between ribs are all less than their corresponding limit values, the equivalent thickness, the spacing between long girders or the spacing between ribs are respectively added with their corresponding step lengths, and the process jumps to step S1; otherwise, the loop ends, and the output values ​​are listed as a reference table for designing stiffened wall panels.

2. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 1, characterized in that: include: The selection methods of equivalent thickness include: Obtain the external loads on the wing, and divide the external loads by the wing box cross-sectional areas at different wing positions to obtain the load concentration interval per unit length along the chord direction at the wing rib position; The load concentration interval is divided by the allowable stress of the stiffened wall panel structure to obtain the equivalent thickness interval, the minimum value of the equivalent thickness interval is used as the initial equivalent thickness in step S1, and the maximum value of the equivalent thickness interval is used as the limit value corresponding to the equivalent thickness in step S5.

3. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 1, characterized in that: include: The method for selecting the long-truss spacing and the rib spacing includes: setting the long-truss spacing range value and the rib spacing range value; The minimum value of the truss spacing range is used as the initial value of the truss spacing in step S1, and the maximum value of the truss spacing range is used as the limiting value corresponding to the truss spacing in step S5; The minimum value of the rib spacing range is used as the initial value of the rib spacing in step S1, and the maximum value of the rib spacing range is used as the limiting value corresponding to the rib spacing in step S5.

4. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 1, characterized in that: include: The calculation formula for the compressive failure stress of the reinforced wall panel is: N 轴力 =∫ A有效宽度壁板面积 s co +∫ A剩余蒙皮面积 s cr ; s 压缩破坏 =N 轴力 / A 总面积 ; Among them, σ 压缩破坏 is the destructive strength of the typical long-strand spacing reinforced wall panel, N 轴力 A is the axial force that the inner wall plate can bear within the long truss spacing. 总面积 is the cross-sectional area of ​​the inner wall plate within the long stringer spacing, σ co is the column strength of the stiffened slab with effective width, σ cr is the skin instability stress, A 有效宽度壁板面积 is the area of ​​the inner wall panel within the effective width, A 剩余蒙皮面积 The skin area where instability occurs.

5. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 1, characterized in that: include: Selecting the long stringer section parameters specifically includes: selecting the long stringer section type and the long stringer section size.

6. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 5, characterized in that: include: The types of long stringer profiles include: I-shaped, T-shaped, Z-shaped, hat-shaped or J-shaped.

7. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 6, characterized in that: include: The cross-sectional dimensions of the I-shaped girder include: girder height bw, girder web thickness tw, lower flange thickness ta, lower flange width ba, upper flange width bf, and upper flange thickness tf.

8. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 7, characterized in that: include: The range of the cross-section size of the I-shaped long stringer is: when the average height of the wing box H≥ When 1000mm, bw=0.04~0.06H; when 1000>H≥600mm, bw=0.06~0.1H; when H<600mm, bw=0.09~0.13H; and bw=0.2~0.4bs; The value of tw is 0.6~1ts (and (tw / bw) / (ts / bs)≥k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts; bf takes a value between 0.35bw and 0.5bw, and tf takes a value between 1ts and 1.2ts.

9. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 7, characterized in that: include: The range of the T-shaped long stringer section size is: when the average height of the wing box H≥ When 1000mm, bw=0.04~0.06H; when 1000>H≥600mm, bw=0.06~0.1H; when H<600mm, bw=0.09~0.13H; and bw=0.2~0.4bs; The value of tw is 0.6~1ts (and (tw / bw) / (ts / bs)≥k, k is generally taken as ), ts is the skin thickness; for overall reinforcement: ba takes a value between 0 and 6tw, for combined reinforcement: ba takes a value between 8-10D, D is the diameter of the connector; for overall reinforcement: ta takes a value between 0 and 0.5ts, for combined reinforcement: ta takes a value between 0.7 and 1ts.

10. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 2, characterized in that: Load concentration Q = M / A, M is the wing box bending moment at the current station, and A is the wing box cross-sectional area.

11. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 10, characterized in that: T=Q / σ ad ; σ ad is the allowable stress and T is the equivalent thickness.

12. The method for designing a reinforced wall panel based on pressure bearing capacity according to claim 10, characterized in that: K w =T 壁板需求厚度 / T; K w is the weight coefficient, T 壁板需求厚度 The thickness of the reinforced wall panel meets the design requirements.

Images