CN107878780B - Method for designing parameters of integral wing spar of wing - Google Patents
Method for designing parameters of integral wing spar of wing Download PDFInfo
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Abstract
本发明公开了一种设计机翼整体翼梁参数的方法。所述设计机翼整体翼梁参数的方法包括如下步骤：步骤1：提供设计机翼整体翼梁初始参数；步骤2：判断机翼整体翼梁单支柱是否满足最小剖面积计算公式以及判断是否满足支柱最小惯性矩计算公式；若不满足最小剖面积计算公式则进行步骤3；若不满足支柱最小惯性矩计算公式则进行步骤4；若同时不满足则进行步骤5；步骤3：引入有效宽度，并计算是否满足带有有效宽度的最小剖面积计算公式；步骤4：引入有效宽度，并计算是否满足带有有效宽度的支柱最小惯性矩计算公式；步骤5：引入有效宽度，重新判断是否满足带有有效宽度的最小剖面积计算公式以及判断是否满足带有有效宽度的支柱最小惯性矩计算公式。
The invention discloses a method for designing the parameters of an integral wing spar of an airfoil. The method for designing the parameters of the integral spar of a wing includes the following steps: Step 1: Provide initial parameters of the integral spar for the design of the wing; Step 2: Determine whether the single strut of the integral spar of the wing satisfies the minimum cross-sectional area calculation formula and determine whether it satisfies the Calculate the formula for the minimum moment of inertia of the pillar; if it does not meet the calculation formula for the minimum cross-sectional area, go to step 3; if it does not meet the calculation formula for the minimum moment of inertia of the pillar, go to step 4; And calculate whether it satisfies the calculation formula of the minimum cross-sectional area with effective width; Step 4: Introduce effective width, and calculate whether it satisfies the calculation formula of the minimum moment of inertia of the pillar with effective width; Step 5: Introduce effective width, and re-judg whether it satisfies the There is a calculation formula for the minimum sectional area with effective width and a calculation formula for determining whether the minimum moment of inertia of a pillar with effective width is satisfied.
Description
技术领域technical field
本发明涉及机翼整体翼梁技术领域，特别是涉及一种设计机翼整体翼梁参数的方法。The invention relates to the technical field of the integral spar of an airfoil, in particular to a method for designing the parameters of the integral spar of an airfoil.
背景技术Background technique
现有技术中关于设计机翼整体翼梁参数的方法计算过程繁琐，计算公式的参数多需要通过查图表取值确定，势必掺杂主观性影响，易于造成误差。此外，没有考虑支柱和腹板参数不合理时，该如何计算腹板临界失稳应力；也没有综合考虑梁腹板有效宽度对计算支柱惯性矩的影响。In the prior art, the calculation process of the method for designing the parameters of the overall wing spar is complicated, and the parameters of the calculation formula need to be determined by checking the values in the chart, which is bound to be mixed with subjective influence, which is easy to cause errors. In addition, it does not consider how to calculate the critical buckling stress of the web when the parameters of the pillar and web are unreasonable; nor does it comprehensively consider the influence of the effective width of the beam web on the calculation of the moment of inertia of the pillar.
因此，希望有一种技术方案来克服或至少减轻现有技术的至少一个上述缺陷。Therefore, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned deficiencies of the prior art.
发明内容SUMMARY OF THE INVENTION
本发明的目的在于提供一种设计机翼整体翼梁腹板厚度参数的方法来克服或至少减轻现有技术的至少一个上述缺陷。It is an object of the present invention to provide a method of designing a wing integral spar web thickness parameter that overcomes or at least mitigates at least one of the aforementioned drawbacks of the prior art.
为实现上述目的，本发明提供一种设计机翼整体翼梁参数的方法，所述机翼整体翼梁包括工字型机翼整体翼梁以及T型机翼整体翼梁，所述设计机翼整体翼梁参数的方法包括如下步骤：In order to achieve the above purpose, the present invention provides a method for designing the parameters of an integral spar of a wing. The method for global spar parameters includes the following steps:
步骤1：提供设计机翼整体翼梁初始参数，所述机翼整体翼梁初始参数包括梁腹板厚度参数；Step 1: Provide the initial parameters of the overall wing spar for the design, and the initial parameters of the overall wing spar of the wing include the thickness parameter of the beam web;
步骤2：判断是否满足最小剖面积计算公式以及判断是否满足支柱最小惯性矩计算公式；Step 2: Judging whether the calculation formula of the minimum cross-sectional area is satisfied and whether the calculation formula of the minimum moment of inertia of the pillar is satisfied;
若同时满足最小剖面积计算公式以及支柱最小惯性矩计算公式，则判断所述机翼整体翼梁初始参数设计合理；If the calculation formula of the minimum sectional area and the calculation formula of the minimum moment of inertia of the strut are satisfied at the same time, it is judged that the initial parameter design of the integral spar of the wing is reasonable;
若满足支柱最小惯性矩计算公式，不满足最小剖面积计算公式，则进行步骤3；If the calculation formula of the minimum moment of inertia of the pillar is satisfied, but the calculation formula of the minimum cross-sectional area is not satisfied, go to step 3;
若满足最小剖面积计算公式，不满足支柱最小惯性矩计算公式，则进行步骤4；If the calculation formula of the minimum cross-sectional area is satisfied, but the calculation formula of the minimum moment of inertia of the pillar is not satisfied, go to step 4;
若同时不满足最小剖面积计算公式以及支柱最小惯性矩计算公式，则进行步骤5；If the calculation formula of the minimum cross-sectional area and the calculation formula of the minimum moment of inertia of the pillar are not satisfied at the same time, go to step 5;
步骤3：引入有效宽度，并计算是否满足带有有效宽度的最小剖面积计算公式，若是，则判断所述机翼整体翼梁初始参数设计合理；若否，则所述机翼整体翼梁腹板厚度初始参数设计不合理，放弃设计；Step 3: Introduce the effective width, and calculate whether the calculation formula of the minimum cross-sectional area with the effective width is satisfied. If so, it is judged that the initial parameter design of the integral spar of the wing is reasonable; if not, the web of the integral spar of the wing is judged to be reasonable. The initial parameter design of plate thickness is unreasonable, and the design is abandoned;
步骤4：引入有效宽度，并计算是否满足带有有效宽度的支柱最小惯性矩计算公式，若是，则判断所述机翼整体翼梁初始参数设计合理；若否，根据惯性矩等效公式以及所述步骤1中的机翼整体翼梁腹板厚度初始参数进行计算，从而获得新的梁腹板厚度参数，将新的梁腹板厚度参数作为所述步骤1中的机翼整体翼梁初始参数；Step 4: Introduce the effective width, and calculate whether it satisfies the calculation formula of the minimum moment of inertia of the strut with the effective width. If so, judge that the initial parameter design of the overall spar of the wing is reasonable; if not, according to the equivalent formula of inertia moment and all Calculate the initial parameters of the overall spar web thickness of the wing in the above step 1, so as to obtain a new thickness parameter of the beam web, and use the new thickness parameter of the beam web as the initial parameter of the overall spar of the wing in the above step 1. ;
步骤5：引入有效宽度，重新判断是否满足带有有效宽度的最小剖面积计算公式以及判断是否满足带有有效宽度的支柱最小惯性矩计算公式；Step 5: Introduce the effective width, and re-judg whether the calculation formula of the minimum cross-sectional area with the effective width is satisfied and whether the calculation formula of the minimum moment of inertia of the pillar with the effective width is satisfied;
若同时满足带有有效宽度的最小剖面积计算公式以及带有有效宽度的支柱最小惯性矩计算公式，则判断所述机翼整体翼梁初始参数设计合理；If the calculation formula of the minimum cross-sectional area with effective width and the calculation formula of the minimum moment of inertia of the strut with effective width are satisfied at the same time, it is judged that the design of the initial parameters of the integral spar of the wing is reasonable;
若满足带有有效宽度的支柱最小惯性矩计算公式，不满足带有有效宽度的最小剖面积计算公式，则放弃设计；If the calculation formula of the minimum moment of inertia of the pillar with effective width is satisfied, and the calculation formula of the minimum cross-sectional area with effective width is not satisfied, the design shall be abandoned;
若满足带有有效宽度的最小剖面积计算公式，不满足带有有效宽度的支柱最小惯性矩计算公式，则根据惯性矩等效公式以及所述步骤1中的机翼整体翼梁腹板厚度初始参数进行计算，从而获得新的梁腹板厚度参数，将新的梁腹板厚度参数作为所述步骤1中的机翼整体翼梁初始参数；If the minimum sectional area calculation formula with effective width is satisfied, but the minimum inertia moment calculation formula for struts with effective width is not satisfied, then according to the equivalent formula of inertia moment and the initial web thickness of the overall wing spar in step 1 parameters are calculated to obtain new beam web thickness parameters, and the new beam web thickness parameters are used as the initial parameters of the wing overall spar in step 1;
若同时不满足带有有效宽度的最小剖面积计算公式以及带有有效宽度的支柱最小惯性矩计算公式，则放弃设计。If the calculation formula for the minimum cross-sectional area with effective width and the calculation formula for the minimum moment of inertia of the pillar with effective width are not satisfied at the same time, the design shall be abandoned.
优选地，所述步骤2中的最小剖面积计算公式具体为：Preferably, the minimum cross-sectional area calculation formula in the step 2 is specifically:
Iu为支柱本身的惯性矩，不包括腹板在内；I u is the moment of inertia of the pillar itself, excluding the web;
he为上缘条与下缘条形心间的距离；h e is the distance between the centroids of the upper edge bar and the lower edge bar;
ks为腹板的边界支持系数；k s is the boundary support coefficient of the web;
d为支柱间距；d is the distance between pillars;
t为梁腹板厚度。t is the thickness of the beam web.
优选地，所述最小剖面积计算公式具体为：Preferably, the minimum cross-sectional area calculation formula is specifically:
判断梁腹板厚度参数是否超过4毫米，若否，则需满足如下公式：Judge whether the beam web thickness parameter exceeds 4 mm, if not, the following formula must be satisfied:
Au≥0.3dt，其中，A u ≥ 0.3dt, where,
Au为支柱的剖面面积；A u is the cross-sectional area of the pillar;
d为支柱间距；d is the distance between pillars;
t为梁腹板厚度；t is the thickness of the beam web;
若判断为是，则采用如下公式：If it is judged to be yes, the following formula is used:
tu≥0.6t；其中，t u ≥0.6t; where,
t为梁腹板厚度；t is the thickness of the beam web;
tu为支柱的厚度。t u is the thickness of the strut.
优选地，所述带有有效宽度的支柱最小惯性矩计算公式具体为：Preferably, the formula for calculating the minimum moment of inertia of the pillar with effective width is as follows:
Iu’为带有有效宽度的支柱本身的惯性矩，不包括腹板在内；I u' is the moment of inertia of the strut itself with effective width, excluding the web;
he为上缘条与下缘条形心间的距离；h e is the distance between the centroids of the upper edge bar and the lower edge bar;
ks为腹板的边界支持系数；k s is the boundary support coefficient of the web;
d’为带有有效宽度的支柱间距；d' is the spacing between pillars with effective width;
t为梁腹板厚度。t is the thickness of the beam web.
优选地，所述带有有效宽度的最小剖面积计算公式具体为：Preferably, the calculation formula of the minimum cross-sectional area with effective width is as follows:
判断梁腹板厚度参数是否超过4毫米，若否，则采用如下公式：Judge whether the beam web thickness parameter exceeds 4 mm, if not, use the following formula:
Au，≥0.3d’t；其中，A u, ≥0.3d't; where,
Au’为带有有效宽度的支柱的剖面面积；A u' is the cross-sectional area of the strut with effective width;
d’为带有有效宽度的支柱间距；d' is the spacing between pillars with effective width;
t为梁腹板厚度；t is the thickness of the beam web;
若判断为是，则采用如下公式：If it is judged to be yes, the following formula is used:
tu’≥0.6t；其中，t u' ≥0.6t; where,
tu’为带有有效宽度的支柱的厚度；t u' is the thickness of the strut with effective width;
t为梁腹板厚度。t is the thickness of the beam web.
本申请的设计机翼整体翼梁参数的方法提高了设计后的翼梁腹板剪切稳定性计算的准确度，对结构安全性和可靠性有重要意义。The method for designing the parameters of the integral spar of the wing of the present application improves the accuracy of the calculation of the shear stability of the web of the spar after the design, which is of great significance to the safety and reliability of the structure.
附图说明Description of drawings
图1是本申请一实施例的机翼整体翼梁为工字型机翼整体翼梁的剖面示意图。FIG. 1 is a schematic cross-sectional view of an integral wing spar of an I-shaped wing according to an embodiment of the present application.
图2是本申请一实施例的机翼整体翼梁为T型机翼整体翼梁的剖面示意图。FIG. 2 is a schematic cross-sectional view of a T-shaped wing integral spar according to an embodiment of the present application.
图3是本申请一实施例的设计机翼整体翼梁参数的方法的流程示意图。FIG. 3 is a schematic flowchart of a method for designing the parameters of an integral spar of a wing according to an embodiment of the present application.
具体实施方式Detailed ways
为使本发明实施的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行更加详细的描述。在附图中，自始至终相同或类似的标号表示相同或类似的元件或具有相同或类似功能的元件。所描述的实施例是本发明一部分实施例，而不是全部的实施例。下面通过参考附图描述的实施例是示例性的，旨在用于解释本发明，而不能理解为对本发明的限制。基于本发明中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。下面结合附图对本发明的实施例进行详细说明。In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. Throughout the drawings, the same or similar reference numbers refer to the same or similar elements or elements having the same or similar functions. The described embodiments are some, but not all, of the embodiments of the present invention. The embodiments described below with reference to the accompanying drawings are exemplary, and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention. The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
在本发明的描述中，需要理解的是，术语“中心”、“纵向”、“横向”、“前”、“后”、“左”、“右”、“竖直”、“水平”、“顶”、“底”“内”、“外”等指示的方位或位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本发明和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本发明保护范围的限制。In the description of the present invention, it should be understood that the terms "center", "portrait", "horizontal", "front", "rear", "left", "right", "vertical", "horizontal", The orientation or positional relationship indicated by "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that The device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present invention.
图1是本申请一实施例的机翼整体翼梁为工字型机翼整体翼梁的剖面示意图。FIG. 1 is a schematic cross-sectional view of an integral wing spar of an I-shaped wing according to an embodiment of the present application.
图2是本申请一实施例的机翼整体翼梁为T型机翼整体翼梁的剖面示意图。FIG. 2 is a schematic cross-sectional view of a T-shaped wing integral spar according to an embodiment of the present application.
图3是本申请一实施例的设计机翼整体翼梁参数的方法的流程示意图。FIG. 3 is a schematic flowchart of a method for designing the parameters of an integral spar of a wing according to an embodiment of the present application.
参见图1，图1为机翼整体翼梁为工字型机翼整体翼梁。Referring to Fig. 1, Fig. 1 shows that the integral spar of the wing is an integral spar of an I-shaped wing.
参见图2，图2为机翼整体翼梁为T型机翼整体翼梁。Referring to Fig. 2, Fig. 2 shows that the integral spar of the wing is an integral spar of a T-shaped wing.
如图1所示的工字型机翼整体翼梁及图2所示的T型机翼整体翼梁均可以采用本申请的方法进行设计。The integral spar of the I-shaped wing shown in FIG. 1 and the integral spar of the T-shaped wing shown in FIG. 2 can be designed using the method of the present application.
参见图3，在本实施例中，设计机翼整体翼梁参数的方法包括如下步骤：Referring to Fig. 3, in this embodiment, the method for designing the parameters of the integral spar of the wing includes the following steps:
步骤1：提供设计机翼整体翼梁初始参数，所述机翼整体翼梁初始参数包括梁腹板厚度参数以及整体翼梁单支柱的刚度；Step 1: Provide initial parameters for the design of the integral spar of the wing, the initial parameters of the integral spar of the wing include the thickness parameter of the spar web and the stiffness of the single strut of the integral spar;
步骤2：判断机翼整体翼梁单支柱的刚度是否满足最小剖面积计算公式以及判断是否满足支柱最小惯性矩计算公式；Step 2: Judge whether the stiffness of the whole wing spar and single strut satisfies the calculation formula of the minimum cross-sectional area and whether it meets the calculation formula of the minimum moment of inertia of the strut;
若同时满足最小剖面积计算公式以及支柱最小惯性矩计算公式，则判断所述机翼整体翼梁初始参数设计合理；If the calculation formula of the minimum sectional area and the calculation formula of the minimum moment of inertia of the strut are satisfied at the same time, it is judged that the initial parameter design of the integral spar of the wing is reasonable;
若满足支柱最小惯性矩计算公式，不满足最小剖面积计算公式，则进行步骤3；If the calculation formula of the minimum moment of inertia of the pillar is satisfied, but the calculation formula of the minimum cross-sectional area is not satisfied, go to step 3;
若满足最小剖面积计算公式，不满足支柱最小惯性矩计算公式，则进行步骤4；If the calculation formula of the minimum cross-sectional area is satisfied, but the calculation formula of the minimum moment of inertia of the pillar is not satisfied, go to step 4;
若同时不满足最小剖面积计算公式以及支柱最小惯性矩计算公式，则进行步骤5；If the calculation formula of the minimum cross-sectional area and the calculation formula of the minimum moment of inertia of the pillar are not satisfied at the same time, go to step 5;
步骤3：引入有效宽度，并计算是否满足带有有效宽度的最小剖面积计算公式，若是，则判断所述机翼整体翼梁初始参数设计合理；若否，则所述机翼整体翼梁腹板厚度初始参数设计不合理，放弃设计；Step 3: Introduce the effective width, and calculate whether the calculation formula of the minimum cross-sectional area with the effective width is satisfied. If so, it is judged that the initial parameter design of the integral spar of the wing is reasonable; if not, the web of the integral spar of the wing is judged to be reasonable. The initial parameter design of plate thickness is unreasonable, and the design is abandoned;
步骤4：引入有效宽度，并计算是否满足带有有效宽度的支柱最小惯性矩计算公式，若是，则判断所述机翼整体翼梁初始参数设计合理；若否，根据惯性矩等效公式以及所述步骤1中的机翼整体翼梁腹板厚度初始参数进行计算，从而获得新的梁腹板厚度参数，将新的梁腹板厚度参数作为所述步骤1中的机翼整体翼梁初始参数；Step 4: Introduce the effective width, and calculate whether it satisfies the calculation formula of the minimum moment of inertia of the strut with the effective width. If so, judge that the initial parameter design of the overall spar of the wing is reasonable; if not, according to the equivalent formula of inertia moment and all Calculate the initial parameters of the overall spar web thickness of the wing in the above step 1, so as to obtain a new thickness parameter of the beam web, and use the new thickness parameter of the beam web as the initial parameter of the overall spar of the wing in the above step 1. ;
步骤5：引入有效宽度，重新判断是否满足带有有效宽度的最小剖面积计算公式以及判断是否满足带有有效宽度的支柱最小惯性矩计算公式；Step 5: Introduce the effective width, and re-judg whether the calculation formula of the minimum cross-sectional area with the effective width is satisfied and whether the calculation formula of the minimum moment of inertia of the pillar with the effective width is satisfied;
若同时满足带有有效宽度的最小剖面积计算公式以及带有有效宽度的支柱最小惯性矩计算公式，则判断所述机翼整体翼梁初始参数设计合理；If the calculation formula of the minimum cross-sectional area with effective width and the calculation formula of the minimum moment of inertia of the strut with effective width are satisfied at the same time, it is judged that the design of the initial parameters of the integral spar of the wing is reasonable;
若满足带有有效宽度的支柱最小惯性矩计算公式，不满足带有有效宽度的最小剖面积计算公式，则放弃设计；If the calculation formula of the minimum moment of inertia of the pillar with effective width is satisfied, and the calculation formula of the minimum cross-sectional area with effective width is not satisfied, the design shall be abandoned;
若满足带有有效宽度的最小剖面积计算公式，不满足带有有效宽度的支柱最小惯性矩计算公式，则根据惯性矩等效公式以及所述步骤1中的机翼整体翼梁腹板厚度初始参数进行计算，从而获得新的梁腹板厚度参数，将新的梁腹板厚度参数作为所述步骤1中的机翼整体翼梁初始参数；If the minimum sectional area calculation formula with effective width is satisfied, but the minimum inertia moment calculation formula for struts with effective width is not satisfied, then according to the equivalent formula of inertia moment and the initial web thickness of the overall wing spar in step 1 parameters are calculated to obtain new beam web thickness parameters, and the new beam web thickness parameters are used as the initial parameters of the wing overall spar in step 1;
若同时不满足带有有效宽度的最小剖面积计算公式以及带有有效宽度的支柱最小惯性矩计算公式，则放弃设计。If the calculation formula for the minimum cross-sectional area with effective width and the calculation formula for the minimum moment of inertia of the pillar with effective width are not satisfied at the same time, the design shall be abandoned.
在本实施例中，步骤2中的最小剖面积计算公式具体为：In this embodiment, the minimum cross-sectional area calculation formula in step 2 is specifically:
Iu为支柱本身的惯性矩，不包括腹板在内；I u is the moment of inertia of the pillar itself, excluding the web;
he为上缘条与下缘条形心间的距离；h e is the distance between the centroids of the upper edge bar and the lower edge bar;
ks为腹板的边界支持系数；k s is the boundary support coefficient of the web;
d为支柱间距；d is the distance between pillars;
t为梁腹板厚度。t is the thickness of the beam web.
在本实施例中，最小剖面积计算公式具体为：In this embodiment, the minimum cross-sectional area calculation formula is specifically:
判断梁腹板厚度参数是否超过4毫米，若否，则需满足如下公式：Judge whether the beam web thickness parameter exceeds 4 mm, if not, the following formula must be satisfied:
Au≥0.3dt，其中，A u ≥ 0.3dt, where,
Au为支柱的剖面面积；A u is the cross-sectional area of the pillar;
d为支柱间距；d is the distance between pillars;
t为梁腹板厚度；t is the thickness of the beam web;
若判断为是，则采用如下公式：If it is judged to be yes, the following formula is used:
tu≥0.6t；其中，t u ≥0.6t; where,
t为梁腹板厚度；t is the thickness of the beam web;
tu为支柱的厚度。t u is the thickness of the strut.
在本实施例中，带有有效宽度的支柱最小惯性矩计算公式具体为：In this embodiment, the formula for calculating the minimum moment of inertia of a pillar with an effective width is as follows:
Iu’为带有有效宽度的支柱本身的惯性矩，不包括腹板在内；I u' is the moment of inertia of the strut itself with effective width, excluding the web;
he为上缘条与下缘条形心间的距离；h e is the distance between the centroids of the upper edge bar and the lower edge bar;
ks为腹板的边界支持系数；k s is the boundary support coefficient of the web;
d’为带有有效宽度的支柱间距；d' is the spacing between pillars with effective width;
t为梁腹板厚度。t is the thickness of the beam web.
在本实施例中，带有有效宽度的最小剖面积计算公式具体为：In this embodiment, the minimum cross-sectional area calculation formula with effective width is specifically:
判断梁腹板厚度参数是否超过4毫米，若否，则采用如下公式：Judge whether the beam web thickness parameter exceeds 4 mm, if not, use the following formula:
Au，≥0.3d’t；其中，A u, ≥0.3d't; where,
Au’为带有有效宽度的支柱的剖面面积；A u' is the cross-sectional area of the strut with effective width;
d’为带有有效宽度的支柱间距；d' is the spacing between pillars with effective width;
t为梁腹板厚度；t is the thickness of the beam web;
若判断为是，则采用如下公式：If it is judged to be yes, the following formula is used:
tu’≥0.6t；其中，t u' ≥0.6t; where,
tu’为带有有效宽度的支柱的厚度；t u' is the thickness of the strut with effective width;
t为梁腹板厚度。t is the thickness of the beam web.
在本实施例中，有效宽度计算公式为：In this embodiment, the effective width calculation formula is:
Wsff为有效宽度；W sff is the effective width;
E为翼梁材料弹性模型；E is the elastic model of the spar material;
σ0.2为屈服强度；σ 0.2 is the yield strength;
t为梁腹板厚度。t is the thickness of the beam web.
可以理解的是，在本实施例中，最小剖面积计算公式以及支柱最小惯性矩计算公式均为已知公式。It can be understood that, in this embodiment, the formula for calculating the minimum cross-sectional area and the formula for calculating the minimum moment of inertia of the pillar are known formulas.
最后需要指出的是：以上实施例仅用以说明本发明的技术方案，而非对其限制。尽管参照前述实施例对本发明进行了详细的说明，本领域的普通技术人员应当理解：其依然可以对前述各实施例所记载的技术方案进行修改，或者对其中部分技术特征进行等同替换；而这些修改或者替换，并不使相应技术方案的本质脱离本发明各实施例技术方案的精神和范围。Finally, it should be pointed out that the above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it is still possible to modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements to some of the technical features; and these Modifications or substitutions do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.
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