WO2021017235A1 - 民用飞机机翼上壁板根部连接角盒、连接结构及机翼 - Google Patents

民用飞机机翼上壁板根部连接角盒、连接结构及机翼 Download PDF

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WO2021017235A1
WO2021017235A1 PCT/CN2019/114629 CN2019114629W WO2021017235A1 WO 2021017235 A1 WO2021017235 A1 WO 2021017235A1 CN 2019114629 W CN2019114629 W CN 2019114629W WO 2021017235 A1 WO2021017235 A1 WO 2021017235A1
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wing
corner box
ribs
long
connection
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PCT/CN2019/114629
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English (en)
French (fr)
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刘超
周磊
王海军
马波
陈轩
徐吉峰
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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 WO2021017235A1 publication Critical patent/WO2021017235A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces

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  • the invention belongs to the technical field of aviation materials, and in particular relates to a connecting corner box and a connecting structure at the root of a civil aircraft wing upper wall plate and a wing.
  • the root connection structure of the wing of a civil aircraft is an important force transmission structure, which is the focus and difficulty in the aircraft design process.
  • the vertical symmetrical bending load of the wing is transmitted to the center wing through the connection structure of the outer wing and the center wing.
  • Loads such as shear force and torque are transmitted to the fuselage through the wing fuselage connection structure, and are balanced with the front fuselage and mid fuselage load.
  • connecting members such as butt joints, butt strap plates, and connecting corner boxes are often used in the connection area of the root of the wing of a civil aircraft, which is realized in the form of bolt connection.
  • the outer wing wall panels often use T-shaped long trusses, and the corresponding connecting corner boxes have various forms, mainly including the following:
  • a corner box is used between the two long stringers, as shown in Figure 2, the A350 adopts this corner box form;
  • the above-mentioned connecting corner box has a large number of parts and a large amount of assembly. Each long stringer needs to be assembled with one or two corner boxes. The number of positioning and assembly procedures are large, which is not conducive to the use of automated equipment and the assembly efficiency is low.
  • the present invention provides a corner box for connecting the root of the upper wall of a civil aircraft wing.
  • the corner box includes a bottom edge, a standing edge and a reinforcing rib.
  • the bottom edge is provided with a notch, and the notch It comprises a closed end and an open end, one side of the standing side is connected to the closed end by a reinforcing rib, and the open end is used for the insertion of the T-shaped long truss web of the outer wing wall panel;
  • the bottom side includes a first side and a second side, the first side is parallel to the second side, and the first side is provided with a notch and two fixing points;
  • the standing side includes a vertical side and A connecting side, the connecting side is simultaneously connected to the closed end of the notch and the two fixing points through reinforcing ribs, the vertical side is vertically connected to the second side, and the vertical side and the connecting side are in a parallel relationship;
  • the reinforcing ribs include two long ribs and a short rib, the short ribs are used to connect the closed end and the connecting side of the gap, and the two long ribs are used to connect two fixed Point and connection side;
  • connection structure for the roots of the upper wall panels of a civil aircraft wing, the connection structure comprising a plurality of connecting corner box groups, each of the connecting corner box groups is arranged in parallel by N connecting corner boxes, and the connection points are fixed.
  • N is a positive integer
  • the connecting structure further includes a long stringer, a skin and a connecting joint, the bottom side and the root flange of the long stringer, the skin and the connecting joint are connected in turn by bolts, and the width of the bottom side is the width of the N long stringers.
  • the sum of the width of the root flange, the length of the bottom edge is determined according to the size and quantity of bolts, and the thickness of the bottom edge is determined according to the strength check results;
  • the connecting structure further includes a rib web and a central wing side corner box.
  • the standing side is connected to the connecting joint, the rib web and the central wing side corner box by bolts in sequence, and the height of the standing side is determined according to the bolt specification and quantity, The thickness of the standing edge is determined according to the strength check result;
  • the projected length of the long ribs on the bottom side is consistent with the length of the bottom side
  • the projected length of the short ribs on the bottom side is the length of the bottom side minus the length of the notch
  • the thickness of the ribs is determined according to the strength check results ;
  • a civil aircraft wing includes a connecting structure and a wing body, and the connecting structure is used to connect the wing body and the fuselage;
  • the number of continuous corner box parts across the long truss is 1/N of the number of integral corner boxes and clamping corner box parts, which is an independent corner box. 1/2N of the number of box parts reduces the number of structural parts. During assembly, it can reduce the number of positioning and assembly procedures, simplify assembly, improve the efficiency of automated equipment, and improve assembly efficiency.
  • Figure 1 is a structural diagram of a split corner box in the background of the present invention.
  • Figure 2 is a structural diagram of an integral corner box in the background of the present invention.
  • Figure 3 is a structural diagram of a clamping corner box in the background of the present invention.
  • Figure 5 is a structural diagram of the connection corner box and the long stringer of the present invention when used together;
  • Fig. 6 is a diagram of the connection form of the mid-span long truss continuous corner box in the specific embodiment of the invention.
  • the present invention provides a connecting corner box and a connecting structure at the root of the upper wall of a civil aircraft wing.
  • the connecting corner box includes a bottom 9 (9 sides composed of two rectangular frames ), a standing side 10 (two rectangular frames composed of 7 sides) and a reinforcing rib 11, the bottom side includes a first side 91 and a second side 92, the first side 91 is parallel to the second side 92, The first side 91 is provided with a notch 93 and two fixing points 94.
  • the bottom side 9 is connected with the long stringer root flange 12, the skin and the connection joints by bolts.
  • the length of the bottom side is determined according to the size and quantity of the bolts.
  • the thickness of the bottom edge is determined according to the strength check results.
  • the standing side 10 includes a vertical side 101 and a connecting side 102.
  • the connecting side 102 is simultaneously connected to a notch 93 and two fixing points 94 through a reinforcing rib 11, and the vertical side 101 is vertically connected to the second side 91 , The vertical side 101 and the connecting side 102 are in a parallel relationship.
  • the standing side 10 is connected with the connecting joint, the rib web 5 and the central wing corner box 8 by bolts.
  • the height of the standing side 10 is determined according to the bolt specification and quantity. 10
  • the thickness is determined according to the strength check results.
  • the notch 93 is used to insert the T-shaped girder web (the girder root flange 12) of the outer wing wall panel.
  • the reinforcing rib 11 includes two long ribs 111 and a short rib 112.
  • the short rib 111 is used to connect the notch 93 and the standing edge 10
  • the two long ribs 112 are used to connect two
  • the fixed point 94 and the standing side 10 the projection length of the long rib 112 on the bottom side 9 is the same as the length of the bottom side 9, and the projection length of the short rib 111 on the bottom side 9 is the length of the bottom side minus the length of the gap.
  • the length of the side is the distance from the first side 91 to the second side 92
  • the length of the notch is the distance from the notch 93 to the first side 91
  • the thickness of the rib is determined according to the result of the strength check. All the above-mentioned strength check results are calculated by the strength check software after finite element simulation on the computer.
  • the width of the bottom side is the sum of the widths of the widened area of the flange roots of the N long stringers, connecting the corner boxes in the corner box group, and the other two sides except the first side and the second side of the bottom side are connected and fixed to each other .
  • the continuous corner box (connecting corner box group) 7 spans the long truss, and the bottom 9 is pressed on the widened area of the flange root 12 of the three continuous truss, as shown in FIG. 5.
  • Figure 6 shows the connection structure described in the present invention.
  • the connecting corner box set 7 is connected to the long stringer flange and skin 6, the lower T-joint 2, the upper T-joint 1 through the first row of bolts, and the second , 3 rows of bolts are connected with the long stringer flange and the skin 6, the lower T-shaped joint 2, and the three long stringer webs are inserted into the gap of the bottom edge at the root cut-off; the vertical side is connected with the T-shaped joint 2 through the bolts and the rib web
  • the plate 5 is connected with the corner boxes 8 on the side of the central wing, and each connecting corner box is connected with 3 long stringers.
  • the number of continuous corner box parts across the long truss is 1/3 of the number of integral corner boxes and clamping corner boxes, which is an independent corner box. 1/6 of the number of box parts, reducing the number of structural parts, during assembly, can reduce the number of positioning and assembly procedures, simplify assembly, improve the efficiency of automation equipment, and improve assembly efficiency.
  • a civil aircraft wing includes a connecting structure and a wing body, and the connecting structure is used for connecting the wing body and the fuselage.

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Abstract

一种民用飞机机翼上壁板根部连接角盒，所述连接角盒包括底边（9）、立边（10）和加强筋条（11），所述底边（9）上设有豁口（93），所述立边（10）一侧通过加强筋条（11）连接豁口（93），所述豁口（93）用于外翼壁板T型长桁腹板插入；还具有民用飞机机翼上壁板根部连接结构及机翼。减少了结构件数量，简化装配，提高了装配效率。

Description

民用飞机机翼上壁板根部连接角盒、连接结构及机翼 技术领域
本发明属于航空材料技术领域，具体涉及一种民用飞机机翼上壁板根部连接角盒及连接结构及机翼。
背景技术
民用飞机机翼根部连接结构是重要的传力结构，是飞机设计过程中的重点与难点，机翼垂向对称弯曲载荷通过外翼和中央翼连接结构传递到中央翼上自平衡，机翼垂向剪力和扭矩等载荷通过机翼机身连接结构传递到机身上，与前机身和中机身载荷平衡。
目前民用飞机机翼根部连接区常采用对接接头、对接带板、连接角盒等连接构件，利用螺栓连接的形式实现。外翼壁板常采用T型长桁，其相对应的连接角盒有多种形式，主要包括以下几种：
1、分体式角盒。每根长桁两侧均有一个角盒与之连接，如图1所示，C919复合材料机翼项目采用该形式角盒；
2、整体式角盒。两根长桁之间采用一个角盒，如图2所示，A350采用此种角盒形式；
3、夹持式角盒。波音专利US9731808B2提出一种夹持式角盒，每根长桁均有一个角盒与之连接，如图3中外翼侧零件66所示零件；
上述连接角盒形式零件数量多，装配量大，每根长桁需配合一到两个角盒进行装配，定位次数多，装配工序多，不利于自动化设备的使用，装配效率低。
发明内容
为了解决上述问题，本发明提供一种民用飞机机翼上壁板根部连接角盒，所述连接角盒包括底边、立边和加强筋条，所述底边上设有豁口，所述豁口包括封闭端和开口端，所述立边的一侧通过加强筋条连接封闭端，所述开口端用于外翼壁板T型长桁腹板插入；
进一步地，所述底边包括第一侧和第二侧，所述第一侧平行于第二侧，所述第一侧设有一个豁口和两个固定点；所述立边包括垂直侧和连接侧，所述连接侧通过加强筋条同时连接豁口的封闭端和两个固定点，所述垂直侧垂直连接于所述第二侧，所述垂直侧和连接侧为平行关系；
进一步地，所述加强筋条包括两根长筋条和一根短筋条，所述短筋条用于连接豁口的封闭端和连接侧，所述两根长筋条用于连接两个固定点和连接侧；
进一步地，一种民用飞机机翼上壁板根部连接结构，所述连接结构包括若干连接角盒组，每个所述连接角盒组由N个连接角盒平行放置并将相互连接处固定后形成，N为正整数；
进一步地，每个所述连接角盒组包括N个豁口、N根短筋条、M个固定点和M根短筋条，其中，M＝N+1；
进一步地，所述连接结构还包括长桁、蒙皮和连接接头，所述底边与长桁的根部凸缘、蒙皮及连接接头通过螺栓依次连接，底边的宽度为N根长桁的根部凸缘的宽度之和，底边的长度根据螺栓规格及数量确定，底边的厚度根据强度校核结果确定；
进一步地，所述连接结构还包括肋腹板和中央翼侧角盒，所述立边与连接接头、肋腹板及中央翼侧角盒通过螺栓依次连接，立边的高度根据螺栓规格及数量确定，立边的厚度根据强度校核结果确定；
进一步地，所述长筋条在底边的投影长度与底边长度一致，短筋条在底边的的投影长度为底边长度减去豁口长度，加强筋条的厚度根据强度校核结果确定；
进一步地，一种民用飞机机翼，所述机翼包括连接结构和翼身，所述连接结构用于连接翼身和机身；
本发明的有益效果如下：
与夹持式角盒形式相比，在同样长桁数量的情况下，跨长桁连续型角盒零件数量为整体式角盒、夹持式角盒零件数量的1/N,为独立式角盒零件数量的1/2N减少结构件数量，在装配时，可减少定位次数及装配工序，简化装配，提高了自动化设备的工作效率，提高装配效率。
附图说明
图1为本发明背景技术中分体式角盒结构图；
图2为本发明背景技术中整体式角盒结构图；
图3为本发明背景技术中夹持式角盒结构图；
图4为本发明中N＝3时，连接角盒组的结构图；
图5为本发明连接角盒与长桁配合使用时的结构图；
图6为本发明具体实施方式中跨长桁连续型角盒连接形式图。
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，以下结合附图及实施例，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。
下面结合附图和具体实施例对本发明作进一步说明，但不作为对本发明的限定。下面为本发明的举出最佳实施例：
如图4-图6所示，本发明提供一种民用飞机机翼上壁板根部连接角盒及连接结构，所述连接角盒包括底边9(9条边组成的类似两个矩形的框架)、立边10(7条边组成的两个矩形框架)和加强筋条11，所述底边包括第一侧91和第二侧92，所述第一侧91平行于第二侧92，所述第一侧91设有一个豁口93和两个固定点94，所述底边9与长桁根部凸缘12、蒙皮及连接接头通过螺栓连接，底边长度根据螺栓规格及数量确定，底边厚度根据强度校核结果确定。所述立边10包括垂直侧101和连接侧102，所述连接侧102通过加强筋条11同时连接一个豁口93和两个固定点94，所述垂直侧101垂直连接于所述第二侧91，所述垂直侧101和连接侧102为平行关系，所述立边10与连接接头、肋腹板5及中央翼侧角盒8通过螺栓连接，立边10高度根据螺栓规格及数量确定，立边10厚度根据强度校核结果 确定。所述豁口93用于外翼壁板T型长桁腹板(长桁根部凸缘12)插入。所述加强筋条11包括两根长筋条111和一根短筋条112，所述短筋条111用于连接豁口93和立边10，所述两根长筋条112用于连接两个固定点94和立边10，所述长筋条112在底边9的投影长度与底边9长度一致，短筋条111在底边9的投影长度为底边长度减去豁口长度，其中底边长度为第一侧91到第二侧92的距离，豁口长度为豁口93到第一侧91的距离，加筋厚度根据强度校核结果确定。上述所有强度校核结果均由强度校核软件在电脑上经过有限元仿真后计算而得。
N个连接角盒平行放置并将相互连接处固定后，形成一个连接角盒组，所述一个连接角盒组包括N个豁口、N根短筋条、M个固定点和M根短筋条，其中M＝N+1，N为正整数。底边宽度为N根长桁的凸缘根部加宽区域的宽度之和，连接角盒组中连接角盒之间，底边除去第一侧和第二侧的另外两侧之间相互连接固定。
本发明中，取N＝3，作为最佳实施方式，进行进一步说明，如图4所示。跨长桁连续型角盒(连接角盒组)7，底边9压在连续3根长桁凸缘根部12加宽区域上，如图5所示。图6所示为本发明中所述的连接结构，连接角盒组7通过第1排螺栓与长桁凸缘及蒙皮6、下T型接头2、上T型接头1连接，通过第2、3排螺栓与长桁凸缘及蒙皮6、下T型接头2相连接,三根长桁腹板在根部截止处插入底边的豁口处；立边通过螺栓与T型接头2、肋腹板5及中央翼侧角盒8相连接，每个连接角盒与3根长桁连接。与第三条角盒形式相比， 在同样长桁数量的情况下，跨长桁连续型角盒零件数量为整体式角盒、夹持式角盒零件数量的1/3,为独立式角盒零件数量的1/6,减少结构件数量，在装配时，可减少定位次数及装配工序，简化装配，提高了自动化设备的工作效率，提高装配效率。
一种民用飞机机翼，所述机翼包括连接结构和翼身，所述连接结构用于连接翼身和机身。
以上所述的实施例，只是本发明较优选的具体实施方式的一种，本领域的技术人员在本发明技术方案范围内进行的通常变化和替换都应包含在本发明的保护范围内。

Claims (9)

  1. 一种民用飞机机翼上壁板根部连接角盒，其特征在于，所述连接角盒包括底边、立边和加强筋条，所述底边上设有豁口，所述豁口包括封闭端和开口端，所述立边的一侧通过加强筋条连接封闭端，所述开口端用于外翼壁板T型长桁腹板插入。
  2. 根据权利要求1所述的连接角盒，其特征在于，所述底边包括第一侧和第二侧，所述第一侧平行于第二侧，所述第一侧设有一个豁口和两个固定点；所述立边包括垂直侧和连接侧，所述连接侧通过加强筋条同时连接豁口的封闭端和两个固定点，所述垂直侧垂直连接于所述第二侧，所述垂直侧和连接侧为平行关系。
  3. 根据权利要求2所述的连接角盒，其特征在于，所述加强筋条包括两根长筋条和一根短筋条，所述短筋条用于连接豁口封闭端和连接侧，所述两根长筋条用于连接两个固定点和连接侧。
  4. 一种民用飞机机翼上壁板根部连接结构，基于上述权利要求1-3之一所述的连接角盒，其特征在于，所述连接结构包括若干连接角盒组，每个所述连接角盒组由N个连接角盒平行放置并将相互连接处固定后形成，N为正整数。
  5. 根据权利要求4所述的连接结构，其特征在于，每个所述连接角盒组包括N个豁口、N根短筋条、M个固定点和M根短筋条，其中，M＝N+1。
  6. 根据权利要求5所述的连接结构，其特征在于，所述连接结构还包括长桁、蒙皮和连接接头，所述底边与长桁的根部凸缘、蒙皮及连接接头通过螺栓依次连接，底边的宽度为N根长桁的根部凸缘的宽度之和，底边的长度根据螺栓规格及数量确定，底边的厚度根据强度校核结果确定。
  7. 根据权利要求5所述的连接结构，其特征在于，所述连接结构还包括肋腹板和中央翼侧角盒，所述立边与连接接头、肋腹板及中央翼侧角盒通过螺栓依次连接，立边的高度根据螺栓规格及数量确定，立边的厚度根据强度校核结果确定。
  8. 根据权利要求4所述的连接结构，其特征在于，所述长筋条在底边的投影长度与底边长度一致，短筋条在底边的的投影长度为底边长度减去豁口长度，加强筋条的厚度根据强度校核结果确定。
  9. 一种民用飞机机翼，基于上述权利要求4-8之一所述的连接结构，其特征在于，所述机翼包括连接结构和翼身，所述连接结构用于连接翼身和机身。
PCT/CN2019/114629 2019-07-31 2019-10-31 民用飞机机翼上壁板根部连接角盒、连接结构及机翼 WO2021017235A1 (zh)

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1512169A (en) * 1975-05-06 1978-05-24 Neuhierl H Model aeroplane
FR2390331B1 (zh) * 1977-05-13 1983-10-28 Messerschmitt Boelkow Blohm
EP1619116A1 (fr) * 2004-07-22 2006-01-25 AIRBUS France Dispositif d'éclissage d'éléments de structure composite avec des éléments de structure métallique
CN104229119A (zh) * 2013-06-07 2014-12-24 波音公司 飞机机翼组件的外侧翼盒和中心翼段之间的下接头
CN105716888A (zh) * 2014-12-03 2016-06-29 中国飞机强度研究所 一种机翼盒段试验装置及其方法
CN110775248A (zh) * 2019-10-21 2020-02-11 深圳市道通智能航空技术有限公司 一种无人机

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9272769B2 (en) * 2012-11-13 2016-03-01 The Boeing Company Joint for composite wings
GB2516830A (en) * 2013-07-31 2015-02-11 Airbus Operations Ltd Aircraft Structure
CN106314759A (zh) * 2016-09-06 2017-01-11 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种飞机机翼的翼梁连接结构
CN207045684U (zh) * 2017-07-19 2018-02-27 中国航空工业集团公司西安飞机设计研究所 飞机翼面组合肋
CN109436372A (zh) * 2018-11-27 2019-03-08 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种面向不同载荷水平的盒段对接组件、对接方法及应用

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1512169A (en) * 1975-05-06 1978-05-24 Neuhierl H Model aeroplane
FR2390331B1 (zh) * 1977-05-13 1983-10-28 Messerschmitt Boelkow Blohm
EP1619116A1 (fr) * 2004-07-22 2006-01-25 AIRBUS France Dispositif d'éclissage d'éléments de structure composite avec des éléments de structure métallique
CN104229119A (zh) * 2013-06-07 2014-12-24 波音公司 飞机机翼组件的外侧翼盒和中心翼段之间的下接头
CN105716888A (zh) * 2014-12-03 2016-06-29 中国飞机强度研究所 一种机翼盒段试验装置及其方法
CN110775248A (zh) * 2019-10-21 2020-02-11 深圳市道通智能航空技术有限公司 一种无人机

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