WO2022068238A1 - 一种张拉整体龙骨的张拉方法 - Google Patents

一种张拉整体龙骨的张拉方法 Download PDF

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WO2022068238A1
WO2022068238A1 PCT/CN2021/097143 CN2021097143W WO2022068238A1 WO 2022068238 A1 WO2022068238 A1 WO 2022068238A1 CN 2021097143 W CN2021097143 W CN 2021097143W WO 2022068238 A1 WO2022068238 A1 WO 2022068238A1
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tensioning
longitudinal tie
position coordinates
tie rod
tension
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PCT/CN2021/097143
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English (en)
French (fr)
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陈务军
张祎贝
高成军
胡建辉
徐建东
刘晶
相海军
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上海交通大学
新誉集团有限公司
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Application filed by 上海交通大学, 新誉集团有限公司 filed Critical 上海交通大学
Publication of WO2022068238A1 publication Critical patent/WO2022068238A1/zh
Priority to US18/191,089 priority Critical patent/US11987388B2/en

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/06—Rigid airships; Semi-rigid airships
    • B64B1/08—Framework construction
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Definitions

  • the present application relates to the technical field of engineering structure design optimization analysis, in particular to a tensioning method for tensioning an integral keel.
  • the "tensioned integral keel” is mainly composed of a stiffening ring, a central truss and a longitudinal tie rod.
  • Each stiffening ring is stretched by radial rods to achieve a self-balanced state;
  • the tension rod produces a large tensile stress, and the central truss produces a large compressive stress, so that the overall keel achieves a self-balanced state with high stiffness.
  • the structure can provide skeleton support for large space structures, and has the advantages of less total number of components, high stiffness and stable equilibrium state.
  • the final shape and tension state of the "tensioned integral keel” are determined. How to achieve precise loading control of its final shape and tension state through a reasonable loading method is the core issue of the research on the tensioning strategy of "tensioned integral keel". There are two issues involved here, one is how to design a reasonable loading method; the other is how to realize the precise loading control of the final shape and tension state of the "tensile integral keel".
  • Chen Wujun, Fu Gongyi, Wang Xiaoliang and others published "a large-scale semi-rigid structure airship” (patent application number 201910275705.7), and invented a semi-rigid airship with a keel composed of stiffening rings and longitudinal tie rods as the main support structure. Further, Chen Wujun, Hu Jianhui, Zhao Bing, etc., "a pressure rod contact type tensioning overall structure and integration and tension application method" (patent application number 201910275699.5), proposed a specific "strengthening ring” and the tensioning of the overall keel. method. However, the precise loading control method for the final shape and tension state of the "tensioned integral keel" is not clear.
  • the technical problem to be solved by this application is how to realize precise loading control on the final shape and tension state of the "tensile integral keel".
  • the present application describes a tensioning method for tensioning an integral keel, which specifically includes the following steps:
  • Step 1 Determine the target value after the overall forming by tensioning, the target value includes the target value of the tensile force of the longitudinal tie rod after the overall forming by tensioning, the first final coordinate of the quantile point, the second final coordinate of the first end, and the second final coordinate of the first end. the third final coordinate of the end;
  • Step 2 placing a plurality of stiffening rings and a plurality of central trusses in turn to form the outline of the integral keel, and fix the locus point of each of the stiffening rings;
  • Step 3 Perform secondary tensioning on the first stiffening ring to achieve a self-balancing state
  • Step 4 A telescopic rod is arranged between the stiffening ring and the central truss, so that the stiffening rings and the central truss are connected together;
  • Step 5 Install the longitudinal tie rod
  • Step 6 Release the restraint on the sub-point and the central truss, and stretch the integral keel to realize the introduction of the tensile force of the longitudinal tie rod, so that the tensile force of the longitudinal tie rod after the integral forming is stretched. the tensile force target value;
  • Step 7 Perform secondary tensioning on other described stiffening rings except the first stiffening ring to reach a self-equilibrium state
  • Step 8 Adjust the initial position coordinates of the quantile point, the first end and the second end, so that the quantile point reaches the first final coordinate after the overall tension is formed, and the first end reaches the first final coordinate.
  • the second final coordinate, the second end reaches the third final coordinate.
  • step 3 secondary tensioning is performed on the first stiffening ring by extending the hub shaft.
  • the longitudinal tie rod is installed by means of stretching or compressing and then mounting.
  • step 5 the longitudinal tie rods are installed in sequence from the middle to both ends.
  • step 5 the longitudinal tie rods are installed in a symmetrical manner.
  • step 5 the initial stress-free length of the longitudinal tie rod is adjusted by a first iterative method, so that each of the stiffening rings after tension forming is not deflected.
  • the first iterative method includes: determining the coordinates of the first chord of the stiffening ring, determining the coordinates of the second chord of the stiffening ring, and determining the relationship between the first chord and the first chord. For the average position coordinate of the second chord, the iteration is stopped by adjusting the stress-free length of the longitudinal tie rod so that the difference between the average position coordinate and the first final coordinate is less than a specific value.
  • step 6 the integral keel is stretched in a manner of extending the telescopic rod.
  • step 6 a method of increasing the temperature is used to extend the telescopic rod.
  • step 6 the temperature load of the telescopic rod is adjusted by a second iterative method.
  • the second iterative method includes: determining the pulling force of the longitudinal tie rod, and adjusting the temperature load of the telescopic rod to make the difference between the pulling force of the longitudinal tie rod and the target tensile force target value. less than a certain value, stop iterating.
  • step 8 the initial position coordinates of the quantile point, the first end and the second end are adjusted by a third iterative method.
  • the third iterative method includes determining the position coordinates of the quantile points after the overall forming by tensioning, and adjusting the initial position coordinates of the quantile points so that the quantile points are stretched and integrally formed.
  • the difference between the position coordinates of and the first final coordinates is less than a certain value.
  • the third iterative method includes determining the position coordinates of the first end after the tension and integral forming, and adjusting the initial position coordinates of the first end so that the first end is stretched and integrally formed.
  • the difference between the position coordinates of and the second final coordinate is less than a certain value.
  • the third iterative method includes determining the position coordinates of the second end after the tension and integral forming, and adjusting the initial position coordinates of the second end so that the second end is stretched and integrally formed.
  • the difference between the position coordinates and the third final coordinate is less than a certain value.
  • the longitudinal tie rod is a tension member, and is linearly elastic in the tension stage.
  • the material of the longitudinal tie rod is carbon fiber.
  • the central truss is a thin-walled tube compression member.
  • central truss is in material linear elasticity during the compression stage
  • the central truss is made of carbon fiber.
  • the calculation process is optimized to make the calculation process clear and concise.
  • Each iteration calculation is only adjusted for a single variable, so the convergence of the optimization method is good, and the calculation is not easy to diverge.
  • Fig. 1 is the flow chart of the overall keel tensioning method of an embodiment of the present application
  • FIG. 2 is a schematic diagram of the overall keel structure of an embodiment of the present application.
  • FIG. 3 is a schematic structural diagram of a stiffening ring according to an embodiment of the present application.
  • FIG. 4 is a schematic diagram of the structural details of a stiffening ring according to an embodiment of the present application.
  • FIG. 5 is a schematic diagram of a longitudinal tie rod according to an embodiment of the present application.
  • FIG. 6 is a flowchart of a first iterative method according to an embodiment of the present application.
  • FIG. 7 is a flowchart of a second iterative method according to an embodiment of the present application.
  • FIG. 8 is a flowchart of a third iterative method according to an embodiment of the present application.
  • 1-stiffening ring 101-radial rod, 102-point point, 103-hub shaft, 104-telescopic rod, 105-first chord, 106-third chord, 107-second chord, 2- Tie rod, 201- Tie rod, 202- Tie rod, 203- Tie rod, 204- Tie rod, 205- Tie rod, 206- Tie rod, 207- Tie rod, 208- Tie rod, 3- Center truss, 4-first end, 5-second end.
  • the overall optimization calculation flow chart of a kind of tensioning overall keel tensioning strategy and optimization analysis method includes the following steps:
  • Step 1 determine the target value after the overall forming by tensioning, including determining the target value F z_opt of the tension force of the longitudinal tie rod 2 after the overall forming by tensioning, the final point 102 , the first end 4 and the final end 5 of the second end 5 . coordinate target value C f_opt ;
  • Step 2 Arrange the stiffening rings 1 and each central truss 3 mounted with the pre-tensioned radial rods 101 (as shown in Figure 3) in turn to form the outline of the overall keel (as shown in Figure 2); fix each stiffener The quantile point 102 of the ring 1 and each central truss 3, the coordinate values of the quantile point 102 and the first end 4 and the second end 5 are recorded as the initial value C f0 , and the stiffening ring is divided into an inner stiffening ring and an outer stiffening ring ring (as shown in Figure 4);
  • Step 3 For the first stiffening ring 1 located in the middle, secondary tensioning is performed by the method of elongating the hub shaft 103 to achieve a self-balancing state (as shown in Figure 4);
  • Step 4 Set up a telescopic rod 104 between the stiffening ring 1 and the central truss 3, so that each stiffening ring 1 and the central truss 3 are connected together;
  • Step 5 Install the longitudinal tie rods 2 by stretching or compressing them and mount them. Install the longitudinal tie rods 2 in sequence from the middle to both ends, and install the longitudinal tie rods in a left-right symmetrical manner. As shown in Figure 5, the longitudinal tie rods 204, 205, 203, 206, 202, 207, 201, and 208 are installed in sequence; the initial stress-free length L z0 of the longitudinal tie rod 2 needs to be optimally designed so that after the final tension forming Each stiffening ring 1 of the keel is basically not deflected;
  • the difference between the average transverse coordinate C xi_avg of the left chord 105 and the right chord 107 of the i-th stiffening ring and the coordinate C fi of the corresponding stiffening ring quantile point 102 is selected to describe whether the stiffening ring is skewed.
  • the average transverse coordinate C xi_avg of the left chord 105 and the right chord 107 of the i-th stiffening ring can be expressed as
  • C xi_1 is the lateral coordinate of the left chord 105 of the ith stiffening ring
  • C xi_2 is the lateral coordinate of the right chord 107 of the ith stiffening ring.
  • the initial stress-free length L z0 of the longitudinal tie rod 2 is adjusted, so that each stiffening ring is basically not deflected after tension forming. That is, it is required that for any i-th stiffening ring, the average lateral coordinate C xi_avg of the left chord 105 and the right chord 107 is substantially consistent with the coordinate C fi of the corresponding quantile point 102 .
  • C xi_avg and C fi satisfy formula (2), the optimization iteration is stopped, and it is considered that each stiffening ring 1 is basically not deflected at this time, and the initial stress-free length L z0 of the longitudinal tie rod 2 has met the design requirements.
  • Formula (2) is as follows:
  • ⁇ 1 is a small amount, and the specific settings are made according to the engineering requirements.
  • Step 6 Release the constraints of the sub-point 102 and the central truss 3, and stretch the entire keel in the way of extending the telescopic rod 104, so as to realize the introduction of the tensile force to the longitudinal tie rod 2, and the elongation of each telescopic rod 104 is recorded as L s ; After the final tension forming, the tensile force of the i-th group of longitudinal tie rods is recorded as F zi .
  • the telescopic rod 104 is elongated by increasing the temperature, so the temperature load T s applied to the telescopic rod 104 needs to be determined, so that the tensile force of each group of longitudinal tie rods 2 reaches the target value after the final tension forming .
  • the temperature load T s of the telescopic rod 104 is adjusted, and the average mean (F zi ) of the tensile force F zi of any i-th group of longitudinal tie rods 2 after the overall forming by tensioning and the corresponding target value F
  • zi_opt satisfies Equation (3) or in some other embodiments
  • the optimization iteration is stopped, and it is considered that the temperature load T s of the telescopic rod 104 has met the design requirements:
  • ⁇ 2 is a small amount, which should be set according to the engineering requirements.
  • Step 7 For the other stiffening rings 1 on the outside except the first stiffening ring, carry out secondary tensioning by the method of elongation of the hub shaft to achieve a self-balancing state;
  • Step 8 Since the extension of the telescopic rod 104 in Step 6, each quantile point 102 and the first end 4 and the second end 5 will deviate from the original coordinates, resulting in the transverse dimension of the keel after the overall forming by tensioning (the coordinates of the second end 5 The difference from the coordinates of the first end 4) is different from the initial value, and the position of each stiffening ring is also different from the initial position.
  • the initial coordinates C f0 of the quantile point 102 and the second end 5 of the first end 4 and the second end 5 are adjusted so that the coordinate value C f of the quantile point 102 and the second end 5 of the first end 4 and the second end 5 after the tensile integral forming is adjusted. reach the target value.
  • C f and the target value C f_opt satisfy the formula (5), the optimization iteration is stopped, and it is considered that the initial coordinates C f0 of the quantile 102 , the first end 4 and the second end 5 have met the design requirements:
  • ⁇ 3 is a small amount, and the specific settings are made according to the engineering requirements.
  • the outer stiffening ring 1 must be stretched a second time after the longitudinal tension rod 2 is stretched (ie, after the telescopic rod 104 is stretched). If the longitudinal tie rod 2 is stretched after the outer stiffening ring 1 is stretched for the second time, the radial rod 101 of the outer stiffening ring 1 is easily loosened.
  • the radial rod 101 and the longitudinal tie rod 2 are tension members made of high-strength, high-rigidity and light-weight carbon fiber, which are linearly elastic in the tension stage, regardless of material nonlinearity and strength damage.
  • the central truss is a compression member
  • the material is a high-strength, high-rigidity, lightweight carbon fiber truss, and a thin-walled tube compression member.
  • the material is linearly elastic. To calculate the compression length, geometric nonlinearity and stability need to be taken into account;
  • the structural force and deformation can be numerically analyzed and calculated by structural analysis software
  • the structural analysis software can be used for numerical nonlinear stability analysis and calculation.
  • the target value F z_opt of the tensile force of the longitudinal tie rod 2 the final coordinate target value C f_opt of the quantile point 102 , the first end 4 and the second end 5 can be determined for specific engineering applications.

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Abstract

一种张拉整体龙骨的张拉方法，包括以下步骤：步骤一、确定张拉整体成型后的目标值；步骤二、形成整体龙骨的轮廓；步骤三、对于内侧的加劲环，通过毂轴伸长的方法进行二次张拉，达到自平衡状态；步骤四、在加劲环和中心桁架之间预设伸缩杆，使各个加劲环和中心桁架连接在一起；步骤五、安装纵拉杆；步骤六、释放分位点及中心桁架的约束，按照伸长伸缩杆的方式对整体龙骨进行张拉，实现对纵拉杆的拉力导入；步骤七、对于外侧的加劲环，通过毂轴伸长的方法进行二次张拉，达到自平衡状态；步骤八、通过迭代方法进行调整，达到张拉整体成型后的目标值。

Description

一种张拉整体龙骨的张拉方法 技术领域
本申请涉及工程结构设计优化分析技术领域，尤其涉及一种张拉整体龙骨的张拉方法。
背景技术
“张拉整体龙骨”主要由加劲环、中心桁架以及纵拉杆构成，各个加劲环通过径向杆张拉达到自平衡状态；通过中心桁架与加劲环之间的伸缩杆伸长的方式，使得纵拉杆产生较大的拉应力、中心桁架产生较大的压应力，从而整体龙骨达到一个具有较大刚度的自平衡状态。该结构可为大型空间结构提供骨架支撑，并具有构件总数少、刚度较高以及平衡状态稳定等优点。
根据设计要求，“张拉整体龙骨”的最终形态和拉力状态是确定的。如何通过合理的加载方式，实现对其最终形态和拉力状态的精确加载控制，是“张拉整体龙骨”张拉策略研究的核心问题。这里涉及两个问题，一是如何设计一种合理的加载方式；二是如何实现对“张拉整体龙骨”最终形态和拉力状态的精确加载控制。
陈务军、付功义、王晓亮等著“一种大尺度半刚性结构飞艇”(专利申请号为201910275705.7)，发明了一种由加劲环和纵拉杆组成的龙骨作为主体支撑结构的半刚性飞艇。进一步，陈务军、胡建辉、赵兵等著“一种压杆接触型张拉整体结构与集成及张力施加方法”(专利申请号为201910275699.5)，提出了具体的“加劲环”及整体龙骨的张拉方法。但是，对“张拉整体龙骨”最终形态和拉力状态的精确加载控制方法没有明确。
因此，本领域的技术人员致力于开发一种张拉整体龙骨的张拉方法，可实现对“张拉整体龙骨”最终形态和拉力状态的精确加载控制。
发明内容
有鉴于现有技术的上述缺陷，本申请所要解决的技术问题是如何实现对“张拉整体龙骨”最终形态和拉力状态的精确加载控制。
为实现上述目的，本申请描述了一种张拉整体龙骨的张拉方法，具体包括以下步骤：
步骤一、确定张拉整体成型后的目标值，所述目标值包括张拉整体成型后纵拉杆的拉力目标值、分位点的第一最终坐标、第一端的第二最终坐标及第二端的第三最终坐标；
步骤二、将多个加劲环以及多个中心桁架依次摆放，形成所述整体龙骨的轮廓，固定每个所述加劲环的分位点；
步骤三、对第一加劲环进行二次张拉，达到自平衡状态；
步骤四、在所述加劲环和所述中心桁架之间设置伸缩杆，使所述各个加劲环和所述中心桁架连接在一起；
步骤五、安装纵拉杆；
步骤六、释放对所述分位点及所述中心桁架的约束，对所述整体龙骨进行张拉，实现对所述纵拉杆的拉力导入，使得张拉整体成型后所述纵拉杆的拉力达到所述拉力目标值；
步骤七、对于除了所述第一加劲环以外的其他所述加劲环进行二次张拉，达到自平衡状态；
步骤八、调整所述分位点、所述第一端以及所述第二端的初始位置坐标，使得张拉整体成型后所述分位点达到所述第一最终坐标，所述第一端达到所述第二最终坐标，所述第二端达到所述第三最终坐标。
可选地，其中步骤三中，对所述第一加劲环通过毂轴伸长的方法进行二次张拉。
可选地，其中步骤五中，采用拉伸或压缩后挂载的方式安装所述纵拉杆。
可选地，其中步骤五中，按照自中间向两端的顺序依次安装所述纵拉杆。
可选地，其中步骤五中，按照对称的方式安装所述纵拉杆。
可选地，其中步骤五中，通过第一迭代方法调整所述纵拉杆的初始无应力长度，使得张拉成型后的各个所述加劲环不偏斜。
可选地，其中所述第一迭代方法包括：确定所述加劲环的第一弦杆的坐标，确定所述加劲环的第二弦杆的坐标，确定所述第一弦杆与所述第二弦杆的平均位置坐标，通过调整所述纵拉杆的无应力长度，使得所述平均位置坐标与所述第一最终坐标的差小于特定值，则停止迭代。
可选地，其中步骤六中，按照伸长所述伸缩杆的方式对所述整体龙骨进行张拉。
可选地，其中步骤六中，采用升高温度的方法使得所述伸缩杆伸长。
可选地，其中步骤六中，通过第二迭代方法调整所述伸缩杆的温度荷载。
可选地，其中所述第二迭代方法包括，确定所述纵拉杆的拉力，通过调整所述伸缩杆的温度载荷，使得所述纵拉杆的拉力与所述目标拉力目标值之间的差值小于特定值，则停止迭代。
可选地，其中步骤八中，通过第三迭代方法调整所述分位点、所述第一端以及所述第二端的初始位置坐标。
可选地，其中所述第三迭代方法包括确定所述分位点张拉整体成型后的位置坐标，通过调整所述分位点的初始位置坐标，使得所述分位点张拉整体成型后的位置坐标与所述第一最终坐标的差小于特定值。
可选地，其中所述第三迭代方法包括确定所述第一端张拉整体成型后的位置坐标，通过调整所述第一端的初始位置坐标，使得所述第一端张拉整体成型后的位置坐标与所述第二最终坐标的差小于特定值。
可选地，其中所述第三迭代方法包括确定所述第二端张拉整体成型后的位置坐标，通过调整所述第二端的初始位置坐标，使得所述第二端张拉整体成型后的位置坐标与所述第三最终坐标的差小于特定值。
可选地，其中所述纵拉杆为受拉构件，在受拉阶段处于线弹性。
可选地，其中所述纵拉杆的材料为碳纤维。
可选地，其中所述中心桁架为薄壁管受压构件。
可选地，其中所述中心桁架在受压阶段处于材料线弹性
可选地，其中在计算所述中心桁架的压缩长度，需要将几何非线性和稳定性纳入考虑。
可选地，其中所述中心桁架由碳纤维制成。
本申请的一种张拉整体龙骨的张拉方法至少具有以下技术效果：
1、可实现对张拉整体龙骨最终形态和拉力状态的精确加载控制；
2、基于优化迭代计算，优化计算流程，使得计算流程清晰、简洁，每次迭代计算只针对单变量进行调整，因此该优化方法的收敛性较好，计算不易发散。
以下将结合附图对本申请的构思、具体结构及产生的技术效果作进一步说明，以充分地了解本申请的目的、特征和效果。
附图说明
图1是本申请的一个实施例的整体龙骨张拉方法流程图；
图2是本申请的一个实施例的整体龙骨结构示意图；
图3是本申请的一个实施例的加劲环结构示意图；
图4是本申请的一个实施例的加劲环结构细节示意图；
图5是本申请的一个实施例的纵拉杆示意图；
图6是本申请的一个实施例的第一迭代方法流程图；
图7是本申请的一个实施例的第二迭代方法流程图
图8是本申请的一个实施例的第三迭代方法流程图。
其中：1-加劲环，101-径向杆，102-分位点，103-毂轴，104-伸缩杆，105-第一弦杆，106-第三弦杆，107-第二弦杆，2-纵拉杆，201-纵拉杆，202-纵拉杆，203-纵拉杆，204-纵拉杆，205-纵拉杆，206-纵拉杆，207-纵拉杆，208-纵拉杆，3-中心桁架，4-第一端，5-第二端。
具体实施方式
以下参考说明书附图介绍本申请的多个优选实施例，使其技术内容更加清楚和便于理解。本申请可以通过许多不同形式的实施例来得以体现，本申请的保护范围并非仅限于文中提到的实施例。
在附图中，结构相同的部件以相同数字标号表示，各处结构或功能相似的组件以相似数字标号表示。附图所示的每一组件的尺寸和厚度是任意示出的，本申请并没有限定每个组件的尺寸和厚度。为了使图示更清晰，附图中有些地方适当夸大了部件的厚度。
如图1所示，为本申请的一个较佳实施例提供的一种张拉整体龙骨张拉策略及优化分析方法的整体优化计算流程图，包括步骤如下：
步骤一、根据工程要求，确定张拉整体成型后的目标值，包括确定张拉整体成型后纵拉杆2的拉力目标值F z_opt、分位点102、第一端4及第二端5的最终坐标目标值C f_opt；
步骤二、将各个挂载有预拉力径向杆101(如图3所示)的加劲环1以及各个中心桁架3依次摆放，形成整体龙骨的轮廓(如图2所示)；固定各个加劲环1的分位点102，以及各个中心桁架3，此时分位点102及第一端4第二端5的坐标值记为初始值C f0，加劲环分为内侧的加劲环和外侧的加劲环(如图4所示)；
步骤三、对于位于中间的第一加劲环1，通过毂轴103伸长的方法进行二次张拉，达到自平衡状态(如图4所示)；
步骤四、在加劲环1和中心桁架3之间设置伸缩杆104，使各个加劲环1和中心桁架3连接在一起；
步骤五、采用拉伸或压缩后挂载的方式安装纵拉杆2，按照自中间向两端的顺序依次安装纵拉杆2，同时按照左右对称的方式安装所述纵拉杆。如图5所示，按照纵拉杆204、205、203、206、202、207、201、208的顺序依次安装；纵拉杆2的初始无应力长度L z0需要进行优化设计，使得最终张拉成型后龙骨的各个加劲环1基本不偏斜；
选取张拉整体成型后第i个加劲环的左弦杆105、右弦杆107的平均横向坐标C xi_avg及对应的加劲环分位点102的坐标C fi的差值描述加劲环是否偏斜。第i个加劲环的左弦杆105、右弦杆107的平均横向坐标C xi_avg可表示为
Figure PCTCN2021097143-appb-000001
式中，C xi_1为第i个加劲环的左弦杆105的横向坐标，C xi_2为第i个加劲环的右弦杆107的横向坐标。
如图6所示，通过第一迭代方法，调整纵拉杆2的初始无应力长度L z0，使得张拉成型后各个加劲环基本不偏斜。也就是要求对于任意第i个加劲环，左弦杆105、右弦杆107的平均横向坐标C xi_avg与对应分位点102的坐标C fi基本一致。当C xi_avg与C fi满足式(2)时，则停止优化迭代，并认为此时各个加劲环1基本不偏斜，且纵拉杆2 的初始无应力长度L z0已满足设计要求。式(2)如下所示：
|C x_avg-C fi|＜ε 1     (2)
式中，ε 1为一小量，根据工程要求做具体设置。
步骤六、释放分位点102及中心桁架3的约束，按照伸长伸缩杆104的方式对整体龙骨进行张拉，实现对纵拉杆2的拉力导入，各个伸缩杆104伸长量记为L s；最终张拉成型后，第i组纵拉杆拉力记为F zi。
在结构分析软件计算中，通过升高温度的方法使伸缩杆104伸长，因此需要确定在伸缩杆104上施加的温度荷载T s，使得最终张拉成型后各组纵拉杆2拉力达到目标值。
如图7所示，通过第二迭代方法，调整伸缩杆104的温度荷载T s，当张拉整体成型后任意第i组纵拉杆2拉力F zi平均值mean(F zi)与对应目标值F zi_opt满足式(3)或在其他一些实施例中，满足(4)时，则停止优化迭代，并认为此伸缩杆104的温度荷载T s已满足设计要求：
Figure PCTCN2021097143-appb-000002
|mean(F zi)-F zi_opt|＜ε 2    (4)
式中，ε 2为一小量，根据工程要求做具体设置。
步骤七、对于外侧的除了第一加劲环以外的其他加劲环1，通过毂轴伸长的方法进行二次张拉，达到自平衡状态；
步骤八、由于步骤六中伸缩杆104伸长后，各个分位点102及第一端4第二端5将偏离原有的坐标，导致张拉整体成型后龙骨横向尺寸(第二端5坐标与第一端4坐标之差)与初始值不同，并且各个加劲环的位置也与初始位置不同。
通过第三迭代方法，调整分位点102及第一端4第二端5的初始坐标C f0，使得张拉整体成型后分位点102及第一端4第二端5的坐标值C f达到目标值。当C f与目标值C f_opt满足式(5)时，则停止优化迭代，并认为此分位点102、第一端4及第二端5的初始坐标C f0已满足设计要求：
|C f_opt-C f|＜ε 3    (5)
式中，ε 3为一小量，根据工程要求做具体设置。
其中，外侧的加劲环1必须在纵拉杆2张拉完成后(即伸缩杆104完成伸长后)再进行二次张拉。如果在外侧加劲环1完成二次张拉后再进行纵拉杆2张拉，则极易导致外侧加劲环1径向杆101松弛。
其中，径向杆101、纵拉杆2为受拉构件，材质为高强高刚性轻质碳纤维，在受拉阶段处于线弹性，不考虑材料非线性和强度破坏问题。
其中，中心桁架为受压构件，材质为高强高刚性轻质碳纤维桁架、薄壁管受压力构件，在受压阶段处于材料线弹性，计算压缩长度，需要将几何非线性和稳定 性纳入考虑；
其中，结构受力及变形情况，可采用结构分析软件进行数值分析计算；
其中，受压构件稳定性分析，可采用结构分析软件进行数值非线性稳定分析计算。
本申请的张拉整体成型后，纵拉杆2拉力的目标值F z_opt、分位点102、第一端4及第二端5的最终坐标目标值C f_opt可针对具体工程应用确定。
以上详细描述了本申请的较佳具体实施例。应当理解，本领域的普通技术无需创造性劳动就可以根据本申请的构思作出诸多修改和变化。因此，凡本技术领域中技术人员依本申请的构思在现有技术的基础上通过逻辑分析、推理或者有限的实验可以得到的技术方案，皆应在由权利要求书所确定的保护范围内。

Claims (20)

  1. 一种张拉整体龙骨的张拉方法，包括以下步骤：
    步骤一、确定张拉整体成型后的目标值，所述目标值包括张拉整体成型后纵拉杆的拉力目标值、分位点的第一最终坐标、第一端的第二最终坐标及第二端的第三最终坐标；
    步骤二、将多个加劲环以及多个中心桁架依次摆放，形成所述整体龙骨的轮廓，固定每个所述加劲环的分位点；
    步骤三、对第一加劲环进行二次张拉，达到自平衡状态；
    步骤四、在所述加劲环和所述中心桁架之间设置伸缩杆，使所述各个加劲环和所述中心桁架连接在一起；
    步骤五、安装纵拉杆；
    步骤六、释放对所述分位点及所述中心桁架的约束，对所述整体龙骨进行张拉，实现对所述纵拉杆的拉力导入，使得张拉整体成型后所述纵拉杆的拉力达到所述拉力目标值；
    步骤七、对于除了所述第一加劲环以外的其他所述加劲环进行二次张拉，达到自平衡状态；
    步骤八、调整所述分位点、所述第一端以及所述第二端的初始位置坐标，使得张拉整体成型后所述分位点达到所述第一最终坐标，所述第一端达到所述第二最终坐标，所述第二端达到所述第三最终坐标。
  2. 如权利要求1所述的张拉方法，其中步骤三中，对所述第一加劲环通过毂轴伸长的方法进行二次张拉。
  3. 如权利要求2所述的张拉方法，其中步骤五中，采用拉伸或压缩后挂载的方式安装所述纵拉杆。
  4. 如权利要求3所述的张拉方法，其中步骤五中，按照自中间向两端的顺序依次安装所述纵拉杆。
  5. 如权利要求4所述的张拉方法，其中步骤五中，按照对称的方式安装所述纵拉杆。
  6. 如权利要求5所述的张拉方法，其中步骤五中，通过第一迭代方法调整所述纵拉杆的初始无应力长度，使得张拉成型后的各个所述加劲环不偏斜。
  7. 如权利要求6所述的张拉方法，其中所述第一迭代方法包括：确定所述加劲环的第一弦杆的坐标，确定所述加劲环的第二弦杆的坐标，确定所述第一弦杆与所述第二弦杆的平均位置坐标，通过调整所述纵拉杆的无应力长度，使得所述平均位置坐标 与所述第一最终坐标的差小于特定值，则停止迭代。
  8. 如权利要求7所述的张拉方法，其中步骤六中，按照伸长所述伸缩杆的方式对所述整体龙骨进行张拉。
  9. 如权利要求8所述的张拉方法，其中步骤六中，采用升高温度的方法使得所述伸缩杆伸长。
  10. 如权利要求9所述的张拉方法，其中步骤六中，通过第二迭代方法调整所述伸缩杆的温度荷载。
  11. 如权利要求10所述的张拉方法，其中所述第二迭代方法包括，确定所述纵拉杆的拉力，通过调整所述伸缩杆的温度载荷，使得所述纵拉杆的拉力与所述目标拉力目标值之间的差值小于特定值，则停止迭代。
  12. 如权利要求11所述的张拉方法，其中步骤八中，通过第三迭代方法调整所述分位点、所述第一端以及所述第二端的初始位置坐标。
  13. 如权利要求12所述的张拉方法，其中所述第三迭代方法包括确定所述分位点张拉整体成型后的位置坐标，通过调整所述分位点的初始位置坐标，使得所述分位点张拉整体成型后的位置坐标与所述第一最终坐标的差小于特定值。
  14. 如权利要求13所述的张拉方法，其中所述第三迭代方法包括确定所述第一端张拉整体成型后的位置坐标，通过调整所述第一端的初始位置坐标，使得所述第一端张拉整体成型后的位置坐标与所述第二最终坐标的差小于特定值。
  15. 如权利要求14所述的张拉方法，其中所述第三迭代方法包括确定所述第二端张拉整体成型后的位置坐标，通过调整所述第二端的初始位置坐标，使得所述第二端张拉整体成型后的位置坐标与所述第三最终坐标的差小于特定值。
  16. 如权利要求15所述的张拉方法，其中所述纵拉杆为受拉构件，在受拉阶段处于线弹性。
  17. 如权利要求16所述的张拉方法，其中所述纵拉杆的材料为碳纤维。
  18. 如权利要求17所述的张拉方法，其中所述中心桁架为薄壁管受压构件。
  19. 如权利要求18所述的张拉方法，其中所述中心桁架在受压阶段处于材料线弹性。
  20. 如权利要求18所述的张拉方法，其中所述中心桁架由碳纤维制成。
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