Aircraft wing rib assembly tool

Abstract

The utility model discloses an aircraft wing rib assembly tool which comprises a bearing mechanism and a positioning mechanism, the bearing mechanism comprises a bearing platform, the bearing platform is provided with an installation opening, and the shape of the installation opening is the same as that of a wing plate of a wing rib; the positioning mechanism comprises a first baffle and two second baffles, the first baffle is arranged on the side of any long edge of the mounting opening and used for abutting against any long edge of a wing plate of a wing rib and a first plate face of a rib strip of the wing rib, and the two second baffles are oppositely arranged on the two sides of two short edges of the mounting opening and used for abutting against any long edge of the wing plate of the wing rib and abutting against a second plate face of a rib strip of the wing rib. The two short edges of the wing plate and the two ends of the rib are connected in an abutting mode respectively. The aircraft wing rib assembly tool has the advantages that wing plates and rib strips of wing ribs of the structure can be rapidly positioned, and the assembly efficiency of the wing plates and the rib strips of the wing ribs of the structure is improved.

Description

Technical Field

[0001] This utility model relates to the field of aircraft wing rib assembly technology, and in particular to an aircraft wing rib assembly tooling. Background Technology

[0002] Wing ribs are an important component of aircraft wings. As the lateral load-bearing framework of the wing, they generally conform to the shape of the airfoil and are used to support the wing skin and maintain the wing's cross-sectional shape. Existing aircraft wing ribs include... Figure 1 - Figure 2 As shown, the wing rib 100 includes a wing plate 110, two ribs 120, and two ear plates 130. The two long sides of the wing plate 110 are curved, and the two short sides are straight. Two rows of first mounting holes 111 are formed on the wing plate 110 along its two long sides. The ribs 120 are curved, and the curvature of the ribs 120 is the same as the curvature of the long sides of the wing plate 110. The length of the ribs 120 is equal to the length of the long sides of the wing plate 110. A row of second mounting holes 121 is formed on the ribs 120 along their length. Rib 120 includes a first plate surface 122 and a second plate surface 123 connected to each other. The first plate surface 122 and the second plate surface 123 are perpendicular to each other. A row of second mounting holes 121 is formed on the second plate surface 123 along its length. Each of the second mounting holes 121 in the two rows corresponds one-to-one with each of the first mounting holes 111 in the two rows. The two ear plates 130 are fixedly connected to the two straight edges of the wing plate 110 by welding. The ear plates 130 are provided with third mounting holes 131. Assembling the wing rib means assembling the two ribs to the wing plate. First, place the two ribs on the wing plate and make each of the second mounting holes in the two rows correspond one-to-one with each of the first mounting holes in the two rows. Then, pass each bolt through the corresponding first mounting hole and second mounting hole in sequence and tighten each nut in sequence, thereby fixing the two ribs to the wing plate. When assembling the ribs of the above structure, positioning fixtures are required to quickly position the wing plates and ribs to ensure that each second mounting hole in a row of second mounting holes corresponds one-to-one with each first mounting hole in a row of first mounting holes. Existing positioning fixtures (such as a rib assembly positioning device disclosed in application number 201110449253.3) cannot quickly position the ribs of this structure. Utility Model Content

[0003] The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose an aircraft wing rib assembly fixture to solve the technical problem that the existing positioning fixtures cannot quickly position the wing ribs of this structure.

[0004] To achieve the above technical objectives, the present invention provides an aircraft wing rib assembly fixture, comprising:

[0005] The load-bearing mechanism includes a load-bearing platform, on which a mounting opening is provided, the shape of which is the same as the shape of the wing plate of the wing rib;

[0006] The positioning mechanism includes a first baffle and two second baffles. The first baffle is disposed on the side of any long side of the mounting opening and is used to abut against any long side of the wing plate of the wing rib and the first plate surface of the rib. The two second baffles are disposed opposite to each other on both sides of the two short sides of the mounting opening and are used to abut against the two short sides of the wing plate and the two ends of the rib, respectively.

[0007] Furthermore, the bearing mechanism also includes two supports and two rotating shafts. The two supports are arranged opposite to each other and spaced apart. The two rotating shafts are arranged horizontally and coaxially. One end of each rotating shaft is rotatably connected to the two supports, and the other end of each rotating shaft is fixedly connected to the two side walls of the two bearing platforms, so that the bearing platform can rotate around the rotating shaft and switch back and forth between a horizontal and a vertical state.

[0008] Furthermore, the positioning mechanism includes two: two first baffles are disposed opposite to each other on both sides of the two long sides of the mounting opening, and four second baffles are disposed opposite to each other on both sides of the two short sides of the mounting opening. The two first baffles and the four second baffles together enclose a positioning space. The shape of the positioning space is the same as that of the wing plate, and the area of ​​the positioning space is equal to that of the wing plate. The two first baffles are respectively used to abut against the two long sides of the wing plate and the first plate surface of the two ribs, and the four second baffles are respectively used to abut against the two short sides of the wing plate and the two ends of the two ribs.

[0009] Furthermore, the first baffle is arc-shaped, and the arc of the first baffle is the same as the arc of the long side of the wing, and the length of the first baffle is equal to the length of the long side of the wing.

[0010] Furthermore, the aircraft wing rib assembly fixture also includes a locking mechanism, which is detachably connected to the bracket and the rotating shaft to keep the bearing platform in a horizontal or vertical state.

[0011] Furthermore, the locking mechanism includes two pins, each being a latch. A through hole extending vertically is formed at the top of the bracket. A first, second, and third insertion hole extending radially are formed on the rotating shaft. The first insertion hole is perpendicular to the supporting platform, while the second and third insertion holes are parallel to the supporting platform. During rotation of the rotating shaft, the first, second, and third insertion holes sequentially communicate with the through hole. The latch is used to insert into the through hole and the corresponding first, second, or third insertion hole. When the first insertion hole communicates with the through hole, the supporting platform is horizontal. When the second insertion hole communicates with the through hole, the supporting platform is vertical with one side wall facing upwards. When the third insertion hole communicates with the through hole, the supporting platform is vertical with the other side wall facing upwards.

[0012] Furthermore, the aircraft wing rib assembly fixture also includes a clamping mechanism, which is connected to the bearing platform and used to clamp the ribs.

[0013] Furthermore, the pressing mechanism includes multiple components, each of which is disposed on the outer side of the first baffle. Each pressing mechanism includes a fixed base, an abutment, a movable frame, and a locking component. One end of the abutment is rotatably connected to the fixed base, and the abutment can reciprocate in a vertical plane around its axis of rotation so that its other end abuts or separates from the second plate surface of the rib. One end of the movable frame is rotatably connected to the fixed base, and the axis of rotation of the movable frame is located inside the axis of rotation of the abutment. The movable frame can reciprocate in a vertical plane around its axis of rotation so that its other end reaches above or to the side of the abutment. The locking component is connected to the other end of the movable frame and is used to press down on the other end of the abutment so that the other end of the abutment presses against the rib.

[0014] Furthermore, the abutment member is an L-shaped rod with a mating hole. When the other end of the abutment member abuts against the second plate surface of the rib, the mating hole faces upward. The movable frame has a screw hole, and the locking member is a screw rod that passes through the screw hole and is threadedly connected to it. When the other end of the movable frame reaches above the abutment member, the locking member is in a vertical position and corresponds to the mating hole. The lower end of the locking member is used to slide into the mating hole.

[0015] Furthermore, the abutting member includes a first connecting rod, a second connecting rod, and a pressure block. One end of the first connecting rod is rotatably connected to the fixed seat via a pin. One end of the second connecting rod is fixedly connected to the other end of the first connecting rod, and the second connecting rod is perpendicular to the first connecting rod. The second connecting rod has the mating hole. The pressure block is fixedly connected to the other end of the second connecting rod. The pressure block is used to abut or separate from the second plate surface of the rib.

[0016] Compared with the prior art, the beneficial effects of this utility model include: In use, the wing plate of the wing rib is placed on the bearing platform, and any long side of the wing plate abuts against the first baffle, and the two short sides of the wing plate abut against the two second baffles respectively. Then, one of the ribs is placed on the wing plate, and the first plate surface of the rib abuts against the first baffle, and the two ends of the rib abut against the two second baffles respectively. At this time, each of the second mounting holes in a row of second mounting holes on the rib corresponds one-to-one with each of the first mounting holes in a row of first mounting holes on the wing plate, thereby enabling rapid positioning of the wing plate and rib. This aircraft wing rib assembly fixture can quickly position the wing plate and rib of this structure, improving the assembly efficiency of the wing plate and rib of this structure. Attached Figure Description

[0017] Figure 1 This is a three-dimensional structural diagram of the existing ribs;

[0018] Figure 2 This is a three-dimensional structural diagram of the existing wing ribs from another perspective;

[0019] Figure 3 This is a three-dimensional structural schematic diagram of an aircraft wing rib assembly tool provided by this utility model;

[0020] Figure 4 This is a three-dimensional structural diagram of an aircraft wing rib assembly tool for positioning wing ribs, provided by this utility model.

[0021] Figure 5 yes Figure 3 A three-dimensional structural diagram of an aircraft wing rib assembly tooling without the support bracket;

[0022] Figure 6 yes Figure 5 A sectional view of the rotating shaft in the middle;

[0023] In the diagram: 100 - wing rib, 110 - wing plate, 111 - first mounting hole, 120 - rib, 121 - second mounting hole, 122 - first plate surface, 123 - second plate surface, 130 - ear plate, 131 - third mounting hole, 200 - load-bearing mechanism, 210 - load-bearing platform, 211 - mounting port, 220 - bracket, 221 - through hole, 230 - pivot, 231 - first insertion hole, 232 - second insertion hole, 233 - third insertion hole, 300 - positioning mechanism, 310 - first baffle, 320 - second baffle, 330 - positioning space, 400 - clamping mechanism, 410 - fixed seat, 420 - abutment part, 421 - docking hole, 430 - movable frame, 440 - locking part. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain this utility model and are not intended to limit this utility model.

[0025] This utility model provides an assembly fixture for aircraft wing ribs, the structure of which is as follows: Figure 3 - Figure 5 As shown, the device includes a support mechanism 200 and a positioning mechanism 300. The support mechanism 200 includes a support platform 210 with an installation opening 211. The shape of the installation opening 211 is the same as that of the wing plate 110 of the wing rib 100. The positioning mechanism 300 includes a first baffle 310 and two second baffles 320. The first baffle 310 is disposed on the side of any long side of the installation opening 211 and is used to abut against any long side of the wing plate 110 of the wing rib 100 and the first plate surface 122 of the rib 120 of the wing rib 100. The two second baffles 320 are disposed opposite to each other on both sides of the two short sides of the installation opening 211 and are used to abut against the two short sides of the wing plate 110 and the two ends of the rib 120, respectively.

[0026] In use, the wing plate 110 of the wing rib 100 is placed on the bearing platform 210, with any long side of the wing plate 110 abutting against the first baffle 310, and the two short sides of the wing plate 110 abutting against the two second baffles 320 respectively. Then, one of the ribs 120 of the wing rib 100 is placed on the wing plate 110, with the first plate surface 122 of the rib 120 abutting against the first baffle 310, and both ends of the rib 120 abutting against the two second baffles 320 respectively. At this time, each of the second mounting holes 121 in a row of second mounting holes 121 on the rib 120 and each of the first mounting holes 111 in a row of first mounting holes 111 on the wing plate 110 are connected to each of the second mounting holes 121 in a row of first mounting holes 111 on the wing plate 110. Each of the first mounting holes 111 corresponds to a specific rib, enabling rapid positioning of the wing plate 110 and the rib 120. Then, each bolt is sequentially passed through the corresponding first mounting hole 111 and second mounting hole 121, and each nut is tightened sequentially, thus fixing the rib 120 to the wing plate 110. After the rib 120 and wing plate 110 are assembled, the above steps are repeated to complete the assembly of another rib 120 to the wing plate 110. This aircraft wing rib assembly fixture can quickly position the wing plate 110 and rib 120 of the wing rib 100, improving the assembly efficiency of the wing plate 110 and rib 120 of the wing rib 100.

[0027] As a preferred embodiment, please refer to Figure 3 and Figure 5 The supporting mechanism 200 further includes two supports 220 and two rotating shafts 230. The two supports 220 are arranged opposite to each other and spaced apart. The two rotating shafts 230 are arranged horizontally and coaxially. One end of each of the two rotating shafts 230 is rotatably connected to the two supports 220, and the other end of each of the two rotating shafts 230 is fixedly connected to the two side walls of the two supporting platforms 210, so that the supporting platform 210 can rotate around the rotating shafts 230 and switch back and forth between the horizontal and vertical states. This facilitates the placement of the wing plate 110 and the rib 120 on the supporting platform 210 and facilitates the assembly of the wing plate 110 and the rib 120.

[0028] As a preferred embodiment, please refer to Figure 4 and Figure 5The positioning mechanism 300 includes two components: two first baffles 310 are disposed opposite each other on both sides of the two long sides of the mounting opening 211, and four second baffles 320 are disposed opposite each other on both sides of the two short sides of the mounting opening 211. The two first baffles 310 and the four second baffles 320 together enclose a positioning space 330. The shape of the positioning space 330 is the same as the shape of the wing plate 110, and the area of ​​the positioning space 330 is equal to the area of ​​the wing plate 110. The two first baffles 310 are respectively used to abut against the two long sides of the wing plate 110 and the first plate surface 122 of the two ribs 120, and the four second baffles 320 are respectively used to abut against the two short sides of the wing plate 110 and the two ends of the two ribs 120. In use, the wing plate 110 is placed in the positioning space 330. Because the shape of the positioning space 330 is the same as that of the wing plate 110, the positioning space 330 is positioned opposite each other on both sides of the mounting opening 211. The shapes of the 10 are the same, and the area of ​​the positioning space 330 is equal to the area of ​​the wing plate 110. At this time, the two long sides of the wing plate 110 abut against the two first baffles 310 respectively, and the two short sides of the wing plate 110 abut against the two second baffles 320 respectively. Then, the two ribs 120 are placed on the wing plate 110, and the first plate surface 122 of the two ribs 120 abut against the two first baffles 310 respectively. At this time, the two ends of the two ribs 120 abut against the corresponding second baffles 320 respectively, and each of the second mounting holes 121 in the two rows of second mounting holes 121 corresponds one-to-one with each of the first mounting holes 111 in the two rows of first mounting holes 111. This enables the wing plate 110 and the two ribs 120 to be quickly positioned, and the wing plate 110 and the two ribs 120 can be quickly positioned at one time, avoiding the need to quickly position the two ribs 120 separately.

[0029] As a preferred embodiment, please refer to Figure 5 The first baffle 310 is arc-shaped, and the arc of the first baffle 310 is the same as the arc of the long side of the wing plate 110. The length of the first baffle 310 is equal to the length of the long side of the wing plate 110, so that the first baffle 310 can completely abut against the long side of the wing plate 110, thereby improving the positioning effect of the wing plate 110.

[0030] As a preferred embodiment, please refer to Figure 5 and Figure 6The aforementioned aircraft wing rib assembly fixture also includes a locking mechanism. The locking mechanism is detachably connected to the bracket 220 and the rotating shaft 230 to keep the bearing platform 210 in a horizontal or vertical state. When the bearing platform 210 is in a horizontal state, it is convenient to place the wing plate 110 and the rib 120 on the bearing platform 210 and complete the quick positioning of the wing plate 110 and the rib 120. When the bearing platform 210 is in a vertical state, it is convenient to pass each bolt through the corresponding first mounting hole 111 and second mounting hole 121 in sequence and tighten each nut in sequence, thereby completing the assembly of the wing plate 110 and the rib 120. If the bearing platform 210 is not adjusted to a vertical state, the operator needs to bend over and straighten up repeatedly when assembling the wing plate 110 and the rib 120, which is very troublesome and may cause certain injuries to the operator's body.

[0031] As a preferred embodiment, please refer to Figure 6 The locking mechanism includes two pins, each being a latch. A vertically extending through hole 221 is formed at the top of the bracket 220. A first insertion hole 231, a second insertion hole 232, and a third insertion hole 233 extending radially are formed on the rotating shaft 230. The first insertion hole 231 is perpendicular to the supporting platform 210, while the second insertion hole 232 and the third insertion hole 233 are parallel to the supporting platform 210. During rotation of the rotating shaft 230, the first insertion hole 231, the second insertion hole 232, and the third insertion hole 233 sequentially communicate with the through hole 221. The latch is used to insert into the through hole 221 and the corresponding first insertion hole 231, second insertion hole 232, and third insertion hole 233. Within the second insertion hole 232 or the third insertion hole 233, when the first insertion hole 231 is connected to the through hole 221, the supporting platform 210 is in a horizontal state; when the second insertion hole 232 is connected to the through hole 221, the supporting platform 210 is in a vertical state with one side wall of the supporting platform 210 facing upwards; when the third insertion hole 233 is connected to the through hole 221, the supporting platform 210 is in a vertical state with the other side wall of the supporting platform 210 facing upwards. This allows the operator to maintain an upright state during the assembly of the wing plate 110 and the two ribs 120 without having to constantly bend over, and it also facilitates the locking operation of the position of the supporting platform 210.

[0032] As a preferred embodiment, please refer to Figure 3 and Figure 4The aircraft wing rib assembly fixture also includes a clamping mechanism 400, which is connected to the bearing platform 210 and used to clamp the rib 120. When the clamping mechanism 400 clamps the rib 120, it also clamps the wing plate 110 below the rib 120, thereby preventing the position of the rib 120 from moving during the rotation of the bearing platform 210.

[0033] As a preferred embodiment, please refer to Figure 4 and Figure 5 The pressing mechanism 400 includes multiple components, each of which is disposed on the outer side of the first baffle 310. Each pressing mechanism 400 includes a fixed base 410, an abutment member 420, a movable frame 430, and a locking member 440. One end of the abutment member 420 is rotatably connected to the fixed base 410, and the abutment member 420 can reciprocate in a vertical plane around its rotation axis 230 so that its other end abuts or separates from the second plate surface 123 of the rib 120. The movable frame 430... One end of the movable frame 430 is rotatably connected to the fixed base 410, and the rotation axis 230 of the movable frame 430 is located inside the rotation axis 230 of the abutment 420. The movable frame 430 can reciprocate in the vertical plane around its rotation axis 230 so that its other end reaches above or to the side of the abutment 420. The locking member 440 is connected to the other end of the movable frame 430 and is used to press down on the other end of the abutment 420 so that the abutment 420... The other end of the abutment 420 is pressed against the rib 120. In the initial state, the other end of the abutment 420 is located outside the first baffle 310, and the other end of the movable frame 430 is located outside the abutment 420, which facilitates the placement of the wing plate 110 in the positioning space 330 and the placement of the two ribs 120 on the wing plate 110. When it is necessary to press the rib 120, first rotate the abutment 420 so that the other end of the abutment 420 enters the positioning space 330 until the rib 120 is pressed against the rib 120. The other end of the abutment 420 abuts against the second plate surface 123 of the rib 120. Then, the movable frame 430 is rotated so that the other end of the movable part reaches above the abutment 420. At this time, the locking part 440 simultaneously reaches above the abutment 420. Then, the locking part 440 is operated so that it can press down on the other end of the abutment 420, thereby pressing the other end of the abutment 420 against the rib 120, thus fixing the rib 120 to the wing plate 110.

[0034] As a preferred embodiment, please refer to Figure 5The abutment member 420 is an L-shaped rod with a mating hole 421. When the other end of the abutment member 420 abuts against the second plate surface 123 of the rib 120, the mating hole 421 faces upward. The movable frame 430 has a screw hole, and the locking member 440 is a screw rod that passes through the screw hole and is threadedly connected to it. When the other end of the movable frame 430 reaches above the abutment member 420, the locking member 440 is in a vertical position and corresponds to the mating hole 421. The lower end of the locking member 440 is used to slide into the mating hole 421. When the lower end of the locking member 440 slides into the mating hole 421, the mating hole 421 can limit the locking member 440, so that the locking member 440 can maintain the clamping force on the abutment member 420.

[0035] As a preferred embodiment, please refer to Figure 5 The abutting member 420 includes a first connecting rod, a second connecting rod, and a pressure block. One end of the first connecting rod is rotatably connected to the fixed base 410 via a pin. One end of the second connecting rod is fixedly connected to the other end of the first connecting rod, and the second connecting rod is perpendicular to the first connecting rod. The second connecting rod has a mating hole 421. The pressure block is fixedly connected to the other end of the second connecting rod. The pressure block is used to abut or separate from the second plate surface 123 of the rib 120. When the first connecting rod is in a horizontal state, the second connecting rod is in a vertical state, the mating hole 421 faces upward, and the pressure block abuts against the second plate surface 123 of the rib 120.

[0036] In a preferred embodiment, the pressure block is made of rubber to prevent it from scratching the rib 120 and to further increase the friction between the pressure block and the rib 120.

[0037] As a preferred embodiment, please refer to Figure 5 The movable frame 430 is a portal frame, and the screw holes are provided on the crossbar of the movable frame 430, which can improve the support effect of the movable frame 430 on the locking member 440.

[0038] To better understand this utility model, the following is combined with... Figure 1 - Figure 6 The working principle of the technical solution of this utility model will be described in detail below:

[0039] In use, the bearing platform 210 is in a horizontal state. The wing plate 110 is placed in the positioning space 330. Since the shape of the positioning space 330 is the same as that of the wing plate 110, the area of ​​the positioning space 330 is equal to that of the wing plate 110. At this time, the two long sides of the wing plate 110 abut against the two first baffles 310 respectively, and the two short sides of the wing plate 110 abut against the two second baffles 320 respectively. Then, two ribs 120 are placed on the wing plate 110, and the first plate surface 122 of the two ribs 120 abut against the two first baffles 310 respectively. At this time, the two ends of the two ribs 120 abut against the corresponding second baffles 320 respectively, and the two rows of second mounting holes are also present. Each of the second mounting holes 121 in 121 corresponds one-to-one with each of the first mounting holes 111 in the two rows of first mounting holes 111, thereby enabling quick positioning of the wing plate 110 and the two ribs 120. Then, the ribs 120 are pressed down, and the abutment member 420 is rotated so that the other end of the abutment member 420 enters the positioning space 330 until the other end of the abutment member 420 abuts against the second plate surface 123 of the rib 120. At this time, the docking hole 421 faces upward. Then, the movable frame 430 is rotated so that the other end of the movable member reaches above the abutment member 420. At this time, the locking member 440 simultaneously reaches above the abutment member 420, and the locking member 440 is aligned with the docking hole 421. Correspondingly, rotate the locking member 440 to slide it into the mating hole 421. Continue rotating the locking member 440 so that it can press down on the other end of the abutment member 420, thereby pressing the other end of the abutment member 420 against the rib 120, thus fixing the rib 120 and the wing plate 110. Then rotate the bearing platform 210 so that the second insertion hole 232 connects with the through hole 221. At this time, the bearing platform 210 is in a vertical state, with one side wall of the bearing platform 210 facing upwards and one of the ribs 120 facing upwards. Assemble the rib 120 and the wing plate 110. When the assembly of the rib 120 and the wing plate 110 is completed... Then, rotate the support platform 210 so that the third insertion hole 233 connects with the through hole 221. At this time, the support platform 210 is in a vertical state, and the other side wall of the support platform 210 is facing upward, and the other rib 120 is facing upward. Assemble the rib 120 and the wing plate 110. When the support platform 210 is in a vertical state, the operator can always maintain an upright state during the assembly of the wing plate 110 and the two ribs 120 without having to bend over. The wing rib assembly fixture of this aircraft can quickly position the wing plate 110 and the rib 120 of the wing rib 100 of this structure, which improves the assembly efficiency of the wing plate 110 and the rib 120 of the wing rib 100 of this structure.

[0040] The aircraft wing rib assembly fixture provided by this utility model has the following beneficial effects:

[0041] (1) When the bearing platform 210 is in a horizontal state, it is convenient to place the wing plate 110 and the rib 120 on the bearing platform 210. When the bearing platform 210 is in a vertical state, the operator can always maintain an upright state during the assembly of the wing plate 110 and the two ribs 120 without having to bend over constantly, which is convenient for assembling the wing plate 110 and the rib 120.

[0042] (2) When the clamping mechanism 400 clamps the rib 120, it will also clamp the wing plate 110 below the rib 120, thereby preventing the position of the rib 120 from moving during the rotation of the bearing platform 210;

[0043] (3) The wing rib assembly tooling of this aircraft can quickly position the wing plate 110 and rib 120 of the wing rib 100 of this structure, thereby improving the assembly efficiency of the wing plate 110 and rib 120 of the wing rib 100 of this structure.

[0044] The specific embodiments of this utility model described above do not constitute a limitation on the scope of protection of this utility model. Any other corresponding changes and modifications made based on the technical concept of this utility model should be included within the scope of protection of the claims of this utility model.

Claims

1. An assembly fixture for aircraft wing ribs, characterized in that, include: The load-bearing mechanism includes a load-bearing platform, on which a mounting opening is provided, the shape of which is the same as the shape of the wing plate of the wing rib; The positioning mechanism includes a first baffle and two second baffles. The first baffle is disposed on the side of any long side of the mounting opening and is used to abut against any long side of the wing plate of the wing rib and the first plate surface of the rib. The two second baffles are disposed opposite to each other on both sides of the two short sides of the mounting opening and are used to abut against the two short sides of the wing plate and the two ends of the rib, respectively.

2. The aircraft wing rib assembly fixture according to claim 1, characterized in that, The bearing mechanism further includes two supports and two rotating shafts. The two supports are arranged opposite to each other and spaced apart. The two rotating shafts are arranged horizontally and coaxially. One end of each rotating shaft is rotatably connected to the two supports, and the other end of each rotating shaft is fixedly connected to the two side walls of the two bearing platforms, so that the bearing platform can rotate around the rotating shaft and switch back and forth between a horizontal and a vertical state.

3. The aircraft wing rib assembly fixture according to claim 1, characterized in that, The positioning mechanism includes two: two first baffles are disposed opposite each other on both sides of the two long sides of the mounting opening, and four second baffles are disposed opposite each other on both sides of the two short sides of the mounting opening. The two first baffles and the four second baffles together enclose a positioning space. The shape of the positioning space is the same as that of the wing plate, and the area of ​​the positioning space is equal to that of the wing plate. The two first baffles are respectively used to abut against the two long sides of the wing plate and the first plate surface of the two ribs, and the four second baffles are respectively used to abut against the two short sides of the wing plate and the two ends of the two ribs.

4. The aircraft wing rib assembly fixture according to claim 1, characterized in that, The first baffle is arc-shaped, and the arc of the first baffle is the same as the arc of the long side of the wing plate, and the length of the first baffle is equal to the length of the long side of the wing plate.

5. The aircraft wing rib assembly fixture according to claim 2, characterized in that, It also includes a locking mechanism, which is detachably connected to the bracket and the pivot to keep the support platform in a horizontal or vertical state.

6. The aircraft wing rib assembly fixture according to claim 5, characterized in that, The locking mechanism includes two pins. A through hole extending vertically is formed at the top of the bracket. A first, second, and third insertion hole extending radially are formed on the rotating shaft. The first insertion hole is perpendicular to the supporting platform, while the second and third insertion holes are parallel to the supporting platform. During rotation of the rotating shaft, the first, second, and third insertion holes sequentially communicate with the through hole. The pin is inserted into the through hole and the corresponding first, second, or third insertion hole. When the first insertion hole communicates with the through hole, the supporting platform is horizontal. When the second insertion hole communicates with the through hole, the supporting platform is vertical with one side wall facing upwards. When the third insertion hole communicates with the through hole, the supporting platform is vertical with the other side wall facing upwards.

7. The aircraft wing rib assembly fixture according to claim 1, characterized in that, It also includes a clamping mechanism, which is connected to the support platform and is used to clamp the ribs.

8. The aircraft wing rib assembly fixture according to claim 7, characterized in that, The clamping mechanism includes multiple components, each of which is disposed on the outer side of the first baffle. Each clamping mechanism includes a fixed base, an abutment, a movable frame, and a locking component. One end of the abutment is rotatably connected to the fixed base, and the abutment can reciprocate in a vertical plane around its axis of rotation so that its other end abuts or separates from the second plate surface of the rib. One end of the movable frame is rotatably connected to the fixed base, and the axis of rotation of the movable frame is located inside the axis of rotation of the abutment. The movable frame can reciprocate in a vertical plane around its axis of rotation so that its other end reaches above or to the side of the abutment. The locking component is connected to the other end of the movable frame and is used to press down on the other end of the abutment so that the other end of the abutment presses against the rib.

9. The aircraft wing rib assembly fixture according to claim 8, characterized in that, The abutment member is an L-shaped rod with a mating hole. When the other end of the abutment member abuts against the second plate surface of the rib, the mating hole faces upward. The movable frame has a screw hole, and the locking member is a screw rod that passes through the screw hole and is threadedly connected to it. When the other end of the movable frame reaches above the abutment member, the locking member is in a vertical position and corresponds to the mating hole. The lower end of the locking member is used to slide into the mating hole.

10. The aircraft wing rib assembly fixture according to claim 9, characterized in that, The abutting member includes a first connecting rod, a second connecting rod, and a pressure block. One end of the first connecting rod is rotatably connected to the fixed seat via a pin. One end of the second connecting rod is fixedly connected to the other end of the first connecting rod, and the second connecting rod is perpendicular to the first connecting rod. The second connecting rod has the mating hole. The pressure block is fixedly connected to the other end of the second connecting rod. The pressure block is used to abut or separate from the second plate surface of the rib.

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