WO2020107530A1 - 一种面向不同载荷水平的盒段对接组件、对接方法及应用 - Google Patents

一种面向不同载荷水平的盒段对接组件、对接方法及应用 Download PDF

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Publication number
WO2020107530A1
WO2020107530A1 PCT/CN2018/120273 CN2018120273W WO2020107530A1 WO 2020107530 A1 WO2020107530 A1 WO 2020107530A1 CN 2018120273 W CN2018120273 W CN 2018120273W WO 2020107530 A1 WO2020107530 A1 WO 2020107530A1
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Prior art keywords
box
docking
corner
load levels
segment
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PCT/CN2018/120273
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English (en)
French (fr)
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高举斌
孙见卓
彭志琦
肖志鹏
王专利
石越
张发
谢汶轩
王栋
刘传军
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中国商用飞机有限责任公司北京民用飞机技术研究中心
中国商用飞机有限责任公司
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Publication of WO2020107530A1 publication Critical patent/WO2020107530A1/zh

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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
    • B64F5/60—Testing or inspecting aircraft components or systems

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  • the invention belongs to the field of aircraft body test design, and particularly relates to a box segment docking component, docking method and application oriented to different load levels.
  • the structure of the dummy box section is generally divided into two types: one is to directly extend the composite material parts of the assessment section as a dummy box section; the other is to manufacture a metal box section, which is mechanically connected to the assessment section.
  • the former reduces the difficulty of assembly, but the cost of composite molds and materials is high, and the dummy box segment must be designed sufficiently strong, and the design and manufacture of composite materials are more difficult; the latter has lower costs, but the assembly is complicated, and the overall test piece increases. Heavy. Take the typical box section test of composite wing as an example. The purpose of the test is usually to verify the bearing capacity of the wing root structure. The dummy box section bears a higher equivalent load. It is generally designed as a metal box section and a composite box section. Docking.
  • test piece assessment box section and the fake box section are connected by inner and outer butt straps, front and rear butt side plates, and are close to the wings in the span
  • the sharp rib positions are integrally docked.
  • the wall panels are mechanically connected with the inner and outer butt straps.
  • the inner butt straps are designed with lap grooves to connect the ends of the long box truss of the assessment box; the front and rear spars are connected by the butt side panels for single shear; the wing ribs and the wall machinery at the butt joint connection.
  • the wall panels and spars of the test box section are cut off at the rib section and connected to the dummy box section; as shown in Figure 3, the test piece is fixed on both sides and a load is applied in the middle of the box section. No additional equivalent load is required for the dummy box segment, and the load level in the docking zone is relatively low.
  • the outer load of the box section should be equivalent to the dummy box section, and the load level of the docking zone is relatively high.
  • the existing docking design does not meet the requirements of large load tests. details as follows:
  • the wing spar is connected in a single-shear form, which is weak when subjected to a large shear load;
  • the wall plate adopts integral butt joint with clamping slot, which is difficult to assemble and position. Under the action of large load, the deformation coordination is difficult.
  • the present invention proposes a box segment docking assembly, docking method and application oriented to different load levels; when the box segment docking method is adopted, the wall panels and the spar are joined in sections, and the spar docking is adopted Double-shear form, the inner side of the wall panel butt joint adopts a segmented corner piece connection scheme.
  • This method is simple to assemble and can be applied to box section tests of different load levels, especially large load levels, reducing assembly difficulty and test risk.
  • the docking assembly is used in the field of box section testing at different load levels in an aircraft body.
  • the docking assembly includes:
  • a number of corner pieces for connecting the body box section spar and the dummy box section spar are provided.
  • the divided corner box is a U-shaped corner box.
  • the material of the U-shaped corner box is metal materials such as aluminum alloy, steel, and titanium alloy.
  • the material of the belt plate is metal materials such as aluminum alloy, steel, and titanium alloy.
  • the material of the skin is a composite material or aluminum alloy.
  • the material of the corner pieces is metal materials such as aluminum alloy, steel, and titanium alloy.
  • metal materials such as aluminum alloy, steel, and titanium alloy of the outer corner box.
  • the butted long truss is obtained by butting the body box section long truss and the dummy box section long truss.
  • the divided corner boxes, belt plates, corner pieces, and outer corner boxes are all provided with corresponding through holes that are convenient for screw fixing.
  • a box segment docking method for different load levels is to use the docking assembly to connect the body box segment and the dummy box segment, butt the wall and wing spar of the body and the dummy in cross-section.
  • the beam butt joint adopts the double-shear form, and the inner side of the wall panel butt joint adopts the corner piece connection.
  • box segment docking method specifically includes the following steps:
  • the adjacent butt truss of the docking area of the body box section wall panel and the dummy box section wall panel adopts an internal partial block corner box, and cooperates with the outer belt plate for fixing, the belt plate and the block Corner box realizes double-shear structure;
  • the body box section spar and the dummy box section spar are docked at the rib ribs, the internal connection joint and the outer corner box realize the double-shear structure of the spar web; the interior of the spar flange is connected by corner pieces, and the outside is The board is shared, and the double-shear structure is also realized.
  • the specific connection method of the internal block type corner box in the docking area between the body box section wall plate and the fake box section wall plate is as follows:
  • the long girders of the two box sections are also correspondingly joined to form a butted long truss, and then the divided corner box is used to connect the adjacent The inside connection between butt girders.
  • butt truss flanges and the web are arranged with fasteners, which reduces the number of assembly parts and reduces the difficulty of fastener arrangement.
  • the double-shear structure refers to the connection of three parts, there are two contact surfaces, that is, two shear surfaces for bolts; the box segment docking method of the present invention is used for large load horizontal box segment test At the docking position of the box section, the loading conditions are complex and the load is large.
  • the double-shear structure can make the box section more stable and safe during the test and reduce the risk of composite material failure.
  • the long stringer of the body box section is provided with a skin on the outside.
  • the long stringer of the dummy box section is also provided with a layer of skin on the outside.
  • Another object of the present invention is to provide a box segment docking method for different load levels applied to box segment tests at different load levels, especially large load levels, to reduce assembly difficulty and test risk.
  • a box segment docking method for different load levels of the present invention The use of a double-shear structure during docking can make the box segment more stable and safe during the test and reduce the risk of composite material failure.
  • a docking method for box segments of the present invention facing different load levels is simple to assemble and easy to operate.
  • the wall panels and spars of the box segment docking area are not butted at the same rib section, the stiffness changes are small, and the stress at the section is dispersed.
  • FIG. 1 is a schematic structural diagram of a transition section of a conventional method for docking test pieces of box sections.
  • FIG. 2 is a schematic view of the structure of the connection end of the test piece in the existing docking method of the box section test piece.
  • Fig. 3 is a schematic diagram of the installation of the transition section of the test piece in the existing docking method of the box section test piece.
  • FIG. 4 is a schematic diagram of the location of the docking area of the box segment in the embodiment of the present invention.
  • FIG. 5 is a schematic diagram of the structure of a docking zone in an embodiment of the present invention.
  • FIG. 6 is a schematic diagram of a docking structure of a wall panel in an embodiment of the present invention.
  • FIG. 7 is a schematic diagram of the joint structure of the spar in the embodiment of the present invention.
  • FIG. 8 is a schematic structural diagram of an outer corner box in an embodiment of the present invention.
  • This embodiment proposes a box segment docking assembly for different load levels. As shown in FIGS. 4-8, the docking assembly is used in the field of box segment testing of different load levels in an aircraft body.
  • the docking assembly includes:
  • One or more belt plates 13 that realize a double-shear structure inside and outside the divided corner boxes;
  • the block-type corner box is a U-shaped corner box 15.
  • the butt joint truss is obtained by butting the body box section long truss 9 and the dummy box section long truss.
  • Corresponding through holes are provided on the divided corner box, belt plate 13, corner piece 16 and outer corner box 18 to facilitate screw connection.
  • This embodiment also proposes a box segment docking method for different load levels.
  • the box segment docking method specifically includes the following steps:
  • the adjacent butt-joint girders of the butt-joint area 4 of the body box section wall panel 5 and the dummy box section wall panel 6 adopt an inner partial block corner box, and cooperate with the outer belt plate 13 for fixed connection.
  • the split corner box realizes a double-shear structure
  • the body box section spar 8 and the dummy box section spar 7 are butted at the wing rib 11, the internal connection joint and the outer corner box 18 enable the double-shear structure of the spar web; the corner piece 16 is used inside the spar flange The connection is externally shared with the belt plate 13 and also achieves a double-shear structure.
  • step S2 the specific connection method of the internal block-type corner box for the docking area 4 of the body box section wall plate 5 and the fake box section wall plate 6 is as follows:
  • the girders of the two box segments are also correspondingly joined to form a butted truss, and then the divided corner box is used to connect the The inside connection between adjacent butt girders.
  • the double-shear structure refers to the connection of three parts, there are two contact surfaces, that is, two shear surfaces for bolts; the box segment docking method of the present invention is used for large load horizontal box segment test, in the box The butt position of the segment is complicated and the load is large.
  • the double-shear structure can make the box segment more stable and safe during the test and reduce the risk of composite material failure.
  • a box segment docking method for different load levels is adopted.
  • the double-shear structure is used during docking to make the box segment more stable and safe during the test and reduce the risk of composite material failure.
  • the box segment docking method is simple to assemble and easy to operate.
  • the wall panels and spars of the box section butt joints are not butted at the same rib section, the stiffness changes are small, and the stress at the section is dispersed.
  • This embodiment provides the application of a box segment docking method for different load levels as described in Example 1.
  • the box segment docking method is applied to box segment tests of different load levels, especially large load levels, to reduce assembly difficulty and Test risk.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
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  • Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

一种面向不同载荷水平的盒段对接组件、对接方法及应用。所述盒段对接方法采用所述对接组件连接本体盒段和假件盒段，将本体和假件的壁板、翼梁分截面对接，翼梁对接采用双剪形式，壁板对接内侧采用角片连接。该方法装配简单，便于操作，此外，在对接时采用双剪结构可使盒段试验时更稳定、安全，并降低复合材料失效的风险。

Description

一种面向不同载荷水平的盒段对接组件、对接方法及应用 技术领域
本发明属于飞机机体试验设计领域，具体涉及一种面向不同载荷水平的盒段对接组件、对接方法及应用。
背景技术
目前，复合材料在民机上应用需经过全面的积木式试验验证，包括典型盒段级、大型部段级试验等，该类试验件往往在考核盒段外侧设计一个假件盒段，外部载荷等效施加在该假件盒段上，以保证考核盒段所承受载荷的真实性。假件盒段结构一般分为两种：一是将考核段复合材料零件直接延长作为假件盒段；另一种是制造一个金属盒段，采用机械连接形式与考核段对接。前者降低了装配难度，但是复材模具成本、材料成本较高，而且假件盒段必须设计得足够强，复合材料设计制造难度较大；后者成本较低，但是装配复杂，试验件整体增重较大。以复合材料机翼的典型盒段试验为例，试验目的通常为为验证翼根结构的承载能力，假件盒段承受的等效载荷较高，一般设计为金属盒段，与复材盒段对接。
现有盒段试验件对接方案如说明书附图1、图2和图3所示，试验件考核盒段与假件盒段采用内外侧对接带板、前后对接侧板连接，在展向靠近翼尖的翼肋位置进行整体对接。壁板采用内外侧对接带板机械连接，其中内对接带板设计搭接槽用以连接考核盒段长桁末端；前后翼梁采用对接侧板进行单剪连接；对接处翼肋与壁板机械连接。考核盒段壁板、翼梁均在肋截面处截断并与假件盒段连接；如图3所示，试验件两侧固支，在盒段中间施加载荷。假件盒段无需施加额外的等效载荷，对接区载荷水平相对较低。而对于类似考核翼根区结构的机翼盒段悬臂结构试验件，需将盒段外侧载荷等效至假件盒段，对接区承受载荷水平比较高。现有的对接设计不满足大载荷试验要求。具体如下：
1)盒段对接区壁板、翼梁在同一肋截面处对接，刚度变化过大，截面处应力集中严重；
2)翼梁对接采用单剪形式，在承受较大剪切载荷作用下，该连接形式偏弱；
3)壁板采用带卡槽式整体式对接，装配定位困难，大载荷作用下，变形协调困难。
发明内容
为解决上述问题，本发明提出一种面向不同载荷水平的盒段对接组件、对接方法及应用；所述盒段对接方法在盒段对接时，壁板、翼梁分截面对接，翼梁对接采用双剪形式，壁板对接内侧采用分块角片式连接方案，该方法装配简单，可以适用于不同载荷水平特别是大载荷水平的盒段试验、降低装配难度和试验风险。
本发明是通过以下技术方案实现的：
一种面向不同载荷水平的盒段对接组件，所述对接组件用于飞机机体中不同载荷水平的盒段试验领域，所述对接组件包括：
若干用于连接相邻对接长桁的分块式角盒；
一与若干所述分块式角盒内外实现双剪结构的带板；
若干用于连接本体盒段翼梁和假件盒段翼梁内部的角片；以及，
若干与所述角片内外实现双剪结构的外侧角盒。
进一步地，所述分块式角盒为U形角盒。
进一步地，所述U形角盒的材质为铝合金、钢、钛合金等金属材料。
进一步地，所述带板的材质为铝合金、钢、钛合金等金属材料。
进一步地，所述蒙皮的材质为复合材料或铝合金。
进一步地，所述角片的材质为铝合金、钢、钛合金等金属材料。
进一步地，所述外侧角盒的铝合金、钢、钛合金等金属材料。
进一步地，所述对接长桁为本体盒段长桁和假件盒段长桁对接后得到。
进一步地，所述分块式角盒、带板、角片和外侧角盒上均设置相应的便于螺钉固接的通孔。
一种面向不同载荷水平的盒段对接方法，所述盒段对接方法是采用所述对接组件连接本体盒段和假件盒段，将本体和假件的壁板、翼梁分截面对接，翼梁对接采用双剪形式，壁板对接内侧采用角片连接。
进一步地，所述盒段对接方法具体包括如下步骤：
S1，本体盒段壁板与假件盒段壁板先行对接；
S2，本体盒段壁板与假件盒段壁板对接区的相邻对接长桁采用内部分块式角盒，并配合外侧的带板进行固接，所述带板与所述分块式角盒实现双剪结构；
S3，本体盒段翼梁和假件盒段翼梁在翼肋处对接，内部连接接头与外侧角盒使翼梁腹板实现双剪结构；翼梁缘条内部采用角片连接，外部与所述带板共用， 同样实现双剪结构。
进一步地，所述步骤S2中所述本体盒段壁板与假件盒段壁板对接区采用内部分块式角盒的具体连接方法如下：
所述本体盒段壁板和所述假件盒段壁板对接后，此时，两盒段的长桁也相应对接形成对接长桁，再采用所述分块式角盒将所述相邻对接长桁间的内侧连接。
进一步地，所述对接长桁缘条和腹板均排布紧固件，减少装配零件数量，降低紧固件排布难度。
进一步地，所述双剪结构是指三个零件连接，存在两个接触面，对螺栓来说即两个剪切面；本发明的所述的盒段对接方法用于大载荷水平盒段试验，在盒段对接位置，受载情况复杂、载荷较大，采用双剪结构可使盒段试验时更稳定、安全，并降低复合材料失效的风险。
进一步地，本领域公知，所述本体盒段的长桁外侧带有蒙皮，同理，所述假件盒段的长桁外侧也带有一层蒙皮。
本发明的另一目的在于提供一种面向不同载荷水平的盒段对接方法应用于不同载荷水平特别是大载荷水平的盒段试验、降低装配难度和试验风险。
本发明的至少具有如下有益技术效果：
(1)本发明的一种面向不同载荷水平的盒段对接方法，对接时采用双剪结构可使盒段试验时更稳定、安全，并降低复合材料失效的风险。
(2)本发明的一种面向不同载荷水平的盒段对接方法装配简单，便于操作。
(3)本发明的一种面向不同载荷水平的盒段对接方法的盒段对接区壁板、翼梁不在同一肋截面处对接，刚度变化小，截面处应力分散。
附图说明
图1为现有盒段试验件对接方法过渡段的结构示意图。
图2为现有盒段试验件对接方法试验件连接端的结构示意图。
图3为现有盒段试验件对接方法试验件过渡段的安装示意图。
图4为本发明实施例中盒段对接区位置示意图。
图5为本发明实施例中对接区结构示意图。
图6为本发明实施例中壁板对接结构示意图。
图7为本发明实施例中翼梁对接结构示意图。
图8为本发明实施例中外侧角盒结构示意图。
附图标记说明：1-墙体，2-本体盒段，3-假件盒段，4-对接区，5-本体盒段壁板，6-假件盒段壁板，7-假件盒段翼梁，8-本体盒段翼梁，9-本体盒段长桁，10-假件盒段长桁，11-翼肋，12-蒙皮，13-带板，14-本体盒段长桁和假件盒段长桁对接处，15-U形角盒，16-角片，17-内部连接头，18-外侧角盒。
具体实施方式
为了使本发明的目的、技术方案及优点更加清楚明白，以下结合实施例及说明书附图，对本发明进行进一步详细描述。应当理解，此处所描述的具体实施例仅仅用于解释本发明，并不用于限定本发明。
相反，本发明涵盖任何由权利要求定义的在本发明的精髓和范围上做的替代、修改、等效方法以及方案。进一步，为了使公众对本发明有更好的了解，在下文对本发明的细节描述中，详尽描述了一些特定的细节部分。对本领域技术人员来说没有这些细节部分的描述也可以完全理解本发明。
实施例1
本实施例提出一种面向不同载荷水平的盒段对接组件，如图4～图8所示，所述对接组件用于飞机机体中不同载荷水平的盒段试验领域，所述对接组件包括：
若干用于连接相邻对接长桁的分块式角盒；
一与若干所述分块式角盒内外实现双剪结构的带板13；
若干用于连接本体盒段翼梁8和假件盒段翼梁7内部的角片16；以及，
若干与所述角片16内外实现双剪结构的外侧角盒18。
所述分块式角盒为U形角盒15。
所述对接长桁为本体盒段长桁9和假件盒段长桁对接后得到。
所述分块式角盒、带板13、角片16和外侧角盒18上均设置相应的便于螺钉固接的通孔。
本实施例还提出一种面向不同载荷水平的盒段对接方法，所述盒段对接方法具体包括如下步骤：
S1，本体盒段壁板5与假件盒段壁板6先行对接；
S2，本体盒段壁板5与假件盒段壁板6对接区4的相邻对接长桁采用内部分块式角盒，并配合外侧的带板13进行固接，所述带板13与所述分块式角盒实现 双剪结构；
S3，本体盒段翼梁8和假件盒段翼梁7在翼肋11处对接，内部连接接头与外侧角盒18使翼梁腹板实现双剪结构；翼梁缘条内部采用角片16连接，外部与所述带板13共用，同样实现双剪结构。
所述步骤S2中所述本体盒段壁板5与假件盒段壁板6对接区4采用内部分块式角盒的具体连接方法如下：
所述本体盒段壁板5和所述假件盒段壁板6对接后，此时，两盒段的长桁也相应对接形成对接长桁，再采用所述分块式角盒将所述相邻对接长桁间的内侧连接。
所述双剪结构是指三个零件连接，存在两个接触面，对螺栓来说即两个剪切面；本发明的所述的盒段对接方法用于大载荷水平盒段试验，在盒段对接位置，受载情况复杂、载荷较大，采用双剪结构可使盒段试验时更稳定、安全，并降低复合材料失效的风险。
本实施例的一种面向不同载荷水平的盒段对接方法，对接时采用双剪结构可使盒段试验时更稳定、安全，并降低复合材料失效的风险。
该盒段对接方法装配简单，便于操作。
此外，盒段对接区壁板、翼梁不在同一肋截面处对接，刚度变化小，截面处应力分散。
实施例2
本实施例提供如实施例1所述的一种面向不同载荷水平的盒段对接方法的应用，所述盒段对接方法应用于不同载荷水平特别是大载荷水平的盒段试验、降低装配难度和试验风险。

Claims (9)

  1. 一种面向不同载荷水平的盒段对接组件，所述对接组件用于飞机机体中不同载荷水平的盒段试验领域，其特征在于，所述对接组件包括：
    若干用于连接相邻对接长桁的分块式角盒；
    一与若干所述分块式角盒内外实现双剪结构的带板；
    若干用于连接本体盒段翼梁和假件盒段翼梁内部的角片；以及，
    若干与所述角片内外实现双剪结构的外侧角盒。
  2. 根据权利要求1所述的一种面向不同载荷水平的盒段对接组件，其特征在于，所述分块式角盒为U形角盒。
  3. 根据权利要求1所述的一种面向不同载荷水平的盒段对接组件，其特征在于，所述对接长桁为本体盒段长桁和假件盒段长桁对接后得到。
  4. 根据权利要求1所述的一种面向不同载荷水平的盒段对接组件，其特征在于，所述分块式角盒、带板、角片和外侧角盒上均设置相应的便于螺钉固接的通孔。
  5. 一种面向不同载荷水平的盒段对接方法，其特征在于，所述盒段对接方法是采用如权利要求1～4任一项所述对接组件连接本体盒段和假件盒段，将本体和假件的壁板、翼梁分截面对接，翼梁对接采用双剪形式，壁板对接内侧采用角片连接。
  6. 根据权利要求5所述的一种面向不同载荷水平的盒段对接方法，其特征在于，所述盒段对接方法具体包括如下步骤：
    S1，本体盒段壁板与假件盒段壁板先行对接；
    S2，本体盒段壁板与假件盒段壁板对接区的相邻对接长桁采用内部分块式角盒，并配合外侧的带板进行固接，所述带板与所述分块式角盒实现双剪结构；
    S3，本体盒段翼梁和假件盒段翼梁在翼肋处对接，内部连接接头与外侧角盒使翼梁腹板实现双剪结构；翼梁缘条内部采用角片连接，外部与所述带板共用，同样实现双剪结构。
  7. 根据权利要求6所述的一种面向不同载荷水平的盒段对接方法，其特征在于，所述步骤S2中所述本体盒段壁板与假件盒段壁板对接区采用内部分块式角盒的具体连接方法如下：
    所述本体盒段壁板和所述假件盒段壁板对接后，此时，两盒段的长桁也相应 对接形成对接长桁，再采用所述分块式角盒将所述相邻对接长桁间的内侧连接。
  8. 根据权利要求7所述的一种面向不同载荷水平的盒段对接方法，其特征在于，所述对接长桁缘条和腹板均排布紧固件，减少装配零件数量，降低紧固件排布难度。
  9. 根据权利要求5～8任一项所述的一种面向不同载荷水平的盒段对接方法应用于不同载荷水平特别是大载荷水平的盒段试验、降低装配难度和试验风险。
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