A positioning method for the internal skeleton ribs of an aircraft box section structure

Abstract

A positioning method for the internal skeleton ribs of an aircraft box section structure. According to the theoretical digital models of the skeleton ribs and the front and rear beam connection components, as well as the template holes of the beam positioning holes and the rib positioning holes, a first auxiliary process drill template and a second auxiliary process drill template for connecting each skeleton rib with the front beam and the rear beam are made. The first auxiliary process drill template is provided with drill mold holes for the beam positioning holes, and the second auxiliary process drill template is provided with drill mold holes for the rib positioning holes. Beam positioning holes are made on the side walls of the beam vertical ribs of each front and rear beam. Rib positioning holes are made at both ends of each skeleton rib. The rib positioning holes at both ends of the skeleton rib are connected and positioned with the beam positioning holes on the side walls of the corresponding front and rear beam vertical ribs through positioning pins, so as to achieve the rapid positioning of the internal skeleton ribs of the aircraft box section structure.

Description

Technical Field

[0001] This application relates to the technical field of aircraft assembly, and specifically relates to a method for quickly positioning the internal frame ribs of a box section structure. Background Art

[0002] During the aircraft assembly process, there is a large amount of assembly work in the form of box section structures. The box section structure includes a front beam, a rear beam, and a plurality of frame ribs connected between the front beam and the rear beam. When assembling the box section structure, the internal frame ribs need to be accurately positioned at the connection parts of the front and rear beams. The rib positioning accuracy affects the positioning of the panel, and thus affects the aerodynamic shape accuracy of the entire box section. The traditional method for positioning the frame ribs is as follows: the ribs are provided with positioning holes in the part state, and the tooling locators are set with the positioning holes on the ribs as the reference on the assembly tooling. This method requires tooling crossbeams to be set on the upper and lower surfaces of the box section, and tooling locators are set on the crossbeams. The assembly tooling is too complex, the operating space is small, and the tooling locators will also affect the positioning of the panel to a certain extent. During the process of repeatedly loading and unloading the product, the tooling crossbeams need to be disassembled and assembled repeatedly, the process is cumbersome, and the assembly cycle is prolonged. In order to increase the construction passage and reduce the manufacturing cost. Therefore, there is an urgent need to design a method for quickly positioning the internal frame ribs of a box section structure. When positioning the internal frame ribs of a box section structure, it can not only ensure the positioning accuracy of the frame ribs, but also accurately and quickly realize the positioning of the frame ribs, avoid repeatedly disassembling and assembling the locators, and improve the assembly efficiency. Summary of the Invention

[0003] The purpose of this application is to provide a method for positioning the internal frame ribs of an aircraft box section structure.

[0004] A positioning method for the internal frame ribs of an aircraft box section structure. The box section structure includes a front beam, a rear beam, and multiple frame ribs connected between the front beam and the rear beam. The theoretical digital models of each frame rib and the front and rear beam connection components are known. The theoretical digital models include the theoretical outer shapes of the frame ribs, the theoretical outer shapes of the front and rear beams, the design data of the web surfaces of the front and rear beams, and the docking hole positions between the frame ribs and the front and rear beams. It is characterized by the following contents: 1) Select two docking holes on the theoretical digital models of the frame rib and the front and rear beam connection components as the beam positioning hole template hole and the rib positioning hole template hole respectively; 2) According to the theoretical digital models of the frame rib and the front and rear beam connection components and the beam positioning hole template hole and the rib positioning hole template hole, make the first auxiliary process drill template and the second auxiliary process drill template for connecting each frame rib with the front beam and the rear beam. There are drill mold holes for beam positioning holes on the first auxiliary process drill template, and drill mold holes for rib positioning holes on the second auxiliary process drill template; 3) Use the first auxiliary process drill template respectively to make beam positioning holes on the side walls of the beam vertical ribs of each front and rear beam; 4) Use the second auxiliary process drill template respectively to make rib positioning holes at both ends of each frame rib; 5) Then connect and position the rib positioning holes at both ends of the frame rib with the beam positioning holes on the side walls of the corresponding front and rear beam vertical ribs through positioning pins to achieve the rapid positioning of the internal frame ribs of the aircraft box section structure.

[0005] The positioning method for the internal frame ribs of the aircraft box section structure is characterized in that the body of the first auxiliary process drill template is a frame-shaped plate structure. There are three reference planes and two drill mold holes for beam positioning holes on the first auxiliary process drill template. The side surface of the first auxiliary process drill template is the first reference plane that fits the side wall of the beam vertical rib. The front end face of the first auxiliary process drill template is the second reference plane that matches the web surface of the beam. There is a horizontal open slot at the lower end of the first auxiliary process drill template, and the open slot matches the lower side flange of the beam. The inner side surface below the open slot is the third reference plane that matches the outer side surface of the lower side flange of the beam. The positional relationship between the two drill mold holes for beam positioning holes and each positioning surface matches the theoretical digital model of the beam and the beam positioning hole template hole. There are also installation holes for fixing with the beam on the first auxiliary process drill template.

[0006] The positioning method for the internal frame ribs of the aircraft box section structure is characterized in that there are two pre-made positioning holes at both ends of the frame rib. The second auxiliary process drill template matches the end of the frame rib. There are two drill template positioning holes corresponding to the pre-made positioning holes and two drill mold holes for rib positioning holes on the second auxiliary process drill template.

[0007] The positioning method for the internal frame ribs of the aircraft box section structure is characterized in that there are multiple drill mold holes on the connecting line of the two drill mold holes for rib positioning holes on the second auxiliary process drill template. These drill mold holes are used to make the connecting holes for fixing the frame rib and the side wall of the beam vertical rib.

[0008] The beneficial effects of the present application are as follows: Two auxiliary process drill templates are used to make beam positioning holes on the side walls of the beam vertical ribs of the front and rear beams respectively, and rib positioning holes are made at both ends of the frame ribs, which reduces the complexity of the tooling and makes the operation space more open; at the same time, the process of repeatedly mounting and dismounting the tooling is avoided, and the auxiliary process drill template is light and easy to disassemble, making the assembly process more convenient and shortening the assembly cycle; using the auxiliary process drill template to drill the connection holes between the ribs and the beam vertical ribs improves the hole-making quality; most importantly, the number of positioners on the assembly tooling is reduced, which can save costs.

[0009] The following further describes the present application in detail with reference to the accompanying drawings of the embodiments. Description of the Drawings

[0010] Figure 1 It is a schematic diagram of the connection structure between the internal frame ribs of the aircraft box section and the front and rear beams.

[0011] Figure 2 It is a schematic diagram of the structure of the first auxiliary process drill template.

[0012] Figure 3 It is a schematic diagram of drilling the connection positioning holes between the beam and the frame ribs on the beam vertical rib.

[0013] Figure 4 It is a schematic diagram of the frame rib structure

[0014] Figure 5 It is a schematic diagram of the structure of the second auxiliary process drill template

[0015] Figure 6 It is a schematic diagram of drilling the rib positioning holes for the connection between the ribs and the beam vertical ribs on the frame ribs

[0016] Figure 7 It is a schematic diagram of positioning the frame ribs using the second auxiliary process drill template

[0017] Description of the numbers in the figure: 1 Rear beam, 2 Frame rib, 3 Front beam, 4 Drill die hole for beam positioning hole, 5 First auxiliary process drill template, 6 First reference plane, 7 Mounting hole, 8 Second reference plane, 9 Third reference plane, 10 Beam vertical rib, 11 Beam web, 12 Flange on the lower side of the front beam, 13 Predetermined positioning hole, 14 Drill template positioning hole, 15 Second auxiliary process drill template, 16 Drill die hole for rib positioning hole, 17 Drill die hole, 18 Locating pin. Detailed Embodiment

[0018] Referring to the accompanying drawings, the box section structure of the present application includes a front beam 3, a rear beam 1, and a plurality of frame ribs 2 connected between the front beam 3 and the rear beam 1, as Figure 1As shown in the figure. The two ends of the skeleton rib 2 are connection surfaces. One end of the skeleton rib 2 is connected to the rear beam 1, and the other end of the skeleton rib 2 is connected to the front beam 3. Given the theoretical digital model of each connection component of the skeleton rib 2 with the front and rear beams, this theoretical digital model includes the theoretical outer shape of the skeleton rib 2, the theoretical outer shapes of the front beam 3 and the rear beam, as well as the design data of the abdominal plate surfaces of the front and rear beams, and the position of the docking holes between the skeleton rib 2 and the beam stirrups 10 of the front and rear beams.

[0019] The following further demonstrates the present invention by selecting the positioning process of one end of a skeleton rib 2 corresponding to the beam web 11 on the front beam 3 in an embodiment:

[0020] Taking the two docking holes on the theoretical digital model of the connection component of the skeleton rib 2 and the front beam 3 as the beam positioning hole template hole and the rib positioning hole template hole respectively, fabricate the first auxiliary process drill template 5 and the second auxiliary process drill template 15 for connecting the skeleton rib 2 and the front beam.

[0021] The first auxiliary process drill template 5 is provided with a drill die hole 4 for the beam positioning hole, as Figure 2 shown;

[0022] As Figure 2 shown, the body of the first auxiliary process drill template 5 is a frame-shaped plate structure. The first auxiliary process drill template 5 is provided with three reference planes and two drill die holes 4 for the beam positioning holes. The side surface of the first auxiliary process drill template 5 is the first reference plane 6 that fits the side wall of the beam stirrup 10. The front end face of the first auxiliary process drill template 5 is the second reference plane that matches the beam web 11. The lower end of the first auxiliary process drill template 5 is provided with a horizontal open slot, which matches the lower side flanging 12 of the front beam. The inner side surface below the open slot is the third reference plane 9 that matches the outer surface of the lower side flanging 12 of the front beam. The positional relationship between the two drill die holes 4 for the beam positioning holes and each positioning surface matches the theoretical digital model of the front beam and the beam positioning hole template hole. The first auxiliary process drill template 5 is also provided with mounting holes 7 for fixing to the front beam.

[0023] Using the first auxiliary process drill template 5, fabricate the beam positioning hole on the side wall of the beam stirrup 10 of the front beam, as Figure 3 shown; when fabricating the beam positioning hole, it is necessary to fit the first reference plane 6 of the first auxiliary process drill template 5 on the side wall of the beam stirrup 10, fit the second reference plane 8 on the beam web 11, fit the third reference plane 9 on the outer surface of the lower side flanging 12 of the front beam, fix the relative position of the first auxiliary process drill template 5 and the front beam 3 through the mounting holes 7, and fabricate the beam positioning hole on the side wall of the beam stirrup 10 according to the drill die hole 4 for the beam positioning hole on the first auxiliary process drill template 5. After the beam positioning hole is completed, separate the first auxiliary process drill template 5 from the front beam.

[0024] The second auxiliary process drill template 15 is provided with a drill die hole 16 for the rib positioning hole, as Figure 5As shown; during implementation, two pre - determined positioning holes 13 are provided at both ends of the skeleton rib 2. The second auxiliary process drill template 15 matches the end of the skeleton rib 2. Two drill template positioning holes 14 corresponding to the pre - determined positioning holes 13 and two drill die holes 16 of the rib positioning holes are provided on the second auxiliary process drill template 15. A plurality of drill die holes 17 are provided on the connection line of the two drill die holes 16 of the rib positioning holes on the second auxiliary process drill template 15. The drill die hole 17 is used to make connection holes for fixing the skeleton rib 2 to the side wall of the beam vertical rib 10.

[0025] Use the second auxiliary process drill template 15 to make rib positioning holes at one end of the skeleton rib 2, as Figure 6 shown; to make rib positioning holes, first, fix the connection between the drill template positioning hole 14 on the second auxiliary process drill template 15 and the pre - determined positioning hole 13 on the skeleton rib 2, so that the second auxiliary process drill template 15 is fixed to the end of the skeleton rib 2. Then, make the rib positioning holes of the skeleton rib 2 at the end of the skeleton rib 2 according to the drill die holes 16 of the rib positioning holes on the second auxiliary process drill template 15.

[0026] Finally, connect and position the rib positioning holes at the end of the skeleton rib 2 with the beam positioning holes on the side wall of the corresponding beam vertical rib 10 through the positioning pin 18 to achieve the rapid positioning of the skeleton rib 2 and the front beam. After positioning, make connection holes on the end of the skeleton rib 2 and the side wall of the corresponding beam vertical rib 10 according to the drill die holes 17 on the second auxiliary process drill template 15 to realize the connection and assembly of the skeleton rib and the beam.

[0027] It should be noted that according to the design digital models of each skeleton rib and the front and rear beams, corresponding auxiliary process drill templates are made. The mounting holes on the auxiliary process drill templates are used to fixedly connect the auxiliary process drill templates with the front and rear beams. The number and positions of the drill membrane holes on the auxiliary process drill templates meet the design requirements for the connection of the skeleton rib and the front and rear beams.

Claims

1. A positioning method for the internal skeleton ribs of an aircraft box section structure. The box section structure includes a front beam, a rear beam, and a plurality of skeleton ribs connected between the front beam and the rear beam. The theoretical digital model of each skeleton rib and the front and rear beam connection components is known. This theoretical digital model includes the theoretical outer shape of the skeleton rib, the theoretical outer shapes of the front and rear beams, the design data of the front and rear beam web plates, and the docking hole positions between the skeleton rib and the front and rear beams. It is characterized in that It includes the following steps: 1) Select two docking holes on the theoretical digital model of the skeleton rib and the front and rear beam connection components as the beam positioning hole template hole and the rib positioning hole template hole respectively; 2) Make the first auxiliary process drill template and the second auxiliary process drill template for connecting each skeleton rib with the front beam and the rear beam according to the theoretical digital model of the skeleton rib and the front and rear beam connection components, the beam positioning hole template hole and the rib positioning hole template hole. The first auxiliary process drill template is provided with drill die holes for beam positioning holes, and the second auxiliary process drill template is provided with drill die holes for rib positioning holes; 3) Use the first auxiliary process drill template to make beam positioning holes on the side walls of the beam vertical ribs of each front and rear beam respectively; 4) Use the second auxiliary process drill template to make rib positioning holes at both ends of each skeleton rib respectively; 5) Then connect and position the rib positioning holes at both ends of the skeleton rib with the beam positioning holes on the side walls of the corresponding front and rear beam vertical ribs through positioning pins to achieve the rapid positioning of the internal skeleton ribs of the aircraft box section structure.

2. The positioning method of the internal skeleton rib of the aircraft box section structure according to claim 1, characterized in that The body of the first auxiliary process drill template is a frame-shaped plate structure. The first auxiliary process drill template is provided with three reference planes and two drill die holes for beam positioning holes. The side surface of the first auxiliary process drill template is the first reference plane that fits with the side wall of the beam vertical rib. The front end face of the first auxiliary process drill template is the second reference plane that matches the beam web surface. The lower end of the first auxiliary process drill template is provided with a horizontal opening groove, which matches the lower flanging of the beam. The inner side surface below the opening groove is the third reference plane that matches the outer side surface of the lower flanging of the beam. The positional relationship between the two drill die holes for beam positioning holes and each positioning surface matches the theoretical digital model of the beam and the beam positioning hole template hole. The first auxiliary process drill template is also provided with installation holes for fixing with the beam.

3. The positioning method of the internal skeleton rib of the aircraft box section structure according to claim 1, characterized in that, Two pre-made positioning holes are provided at both ends of the skeleton rib. The second auxiliary process drill template matches the end of the skeleton rib. The second auxiliary process drill template is provided with two drill template positioning holes corresponding to the pre-made positioning holes and two drill die holes for rib positioning holes.

4. The positioning method of the internal skeleton rib of the aircraft box section structure according to claim 1, characterized in that A plurality of drill die holes are provided on the connection line of the two drill die holes for rib positioning holes of the second auxiliary process drill template. These drill die holes are used to make connection holes for fixing the skeleton rib and the side wall of the beam vertical rib.

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