Assembly method of semi-enclosed bulkhead panel for aircraft nose

Abstract

The present invention discloses a method for assembling a semi-enclosed bulkhead panel of an aircraft nose, wherein a first semi-enclosed bulkhead panel assembly tool and a second semi-enclosed bulkhead panel assembly tool are used to assemble a left side wall component and a right side wall component spaced apart in the semi-enclosed bulkhead panel of the aircraft nose. The present invention decomposes the process of the semi-enclosed bulkhead panel of the aircraft nose during the assembly process, and then optimizes the assembly method and allocates tolerances to ensure that the position tolerances of each intersection point, intersection coaxiality, intersection parallelism, and opening size in the semi-enclosed bulkhead panel of the aircraft nose meet the design requirements, thereby effectively improving the accuracy of installation and assembly. In addition, the present invention can also support and maintain the shape of the wall panel components on both sides through the assembly tool, thereby preventing the wall panel components from being deformed during the assembly and transportation of aircraft components, thereby effectively ensuring that the shape and position tolerances are not affected.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft assembly, in particular to an assembly method of a semi-enclosed bulkhead panel at an aircraft nose. Background Art

[0002] During aircraft manufacturing, the semi-enclosed cabin structure at the bottom of the nose requires multiple sets of functional axis installation intersections due to special functional requirements. Since the geometric tolerances of these installation intersections are as low as 0.01mm, high installation precision is required, manufacturing is difficult, and the structural characteristics of the semi-enclosed cabin easily lead to deformation after assembly. To improve installation precision, the existing technology leaves margins when machining bushings at the installation intersections of the semi-enclosed cabin structure, and uses special tooling to assemble the semi-enclosed cabin assembly. After the semi-enclosed cabin assembly and the rest of the aircraft fuselage form a complete structure, the special tooling is removed, the bushings are installed, and the installation holes at each intersection are fine-machined using special equipment to ensure geometric tolerances. The above-mentioned prior art assembly method requires the use of additional special equipment, resulting in increased production costs. Moreover, the semi-enclosed cabin assembly has already been assembled when fine-machining is performed. The fine-machining is limited by the construction space, which increases the difficulty of processing and is prone to quality accidents.

[0003] Chinese patent document with publication number CN1171828824A discloses a flexible tooling for assembling aircraft wall panels, which includes an operating table, two movable boxes are provided above the operating table, and a counter-directional sliding mechanism cooperating with the two movable boxes is provided on the operating table. A plurality of prisms are provided above the movable boxes, and a damping adjustment lifting structure cooperating with the prisms is provided on the movable boxes. The top of the prism is fixedly connected to a clamping plate for fixing the skeleton, and the cross-section of the clamping plate is a U-shaped structure. A rectangular ring is provided above the movable box, and a clamping unit for clamping the skin is provided on the rectangular ring. A first rotating seat is provided below the rectangular ring, and the first rotating seat and the rectangular ring are connected by an elastic reset unit.

[0004] The technical solution disclosed in the above patent application assembles aircraft wall panels by using flexible tooling, but it can only increase the scope of application of the assembly but not the accuracy of the assembly. Therefore, it cannot meet the assembly accuracy requirements of the semi-enclosed cabin of the aircraft, and cannot prevent deformation during assembly or transportation. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide an assembly method for a semi-enclosed bulkhead panel of an aircraft nose, which can effectively improve the assembly accuracy of the semi-enclosed bulkhead panel of the aircraft nose.

[0006] To solve the above-mentioned technical problems, the present invention adopts a technical solution: a method for assembling a semi-enclosed bulkhead panel of an aircraft nose, comprising: using a first semi-enclosed bulkhead panel assembly tool and a second semi-enclosed bulkhead panel assembly tool to assemble a left side wall assembly and a right side wall assembly spaced apart in the semi-enclosed bulkhead panel of the aircraft nose, wherein the left side wall assembly and the right side wall assembly are symmetrical structures consisting of side walls and a crossbeam, wherein the side walls are provided with a crossbeam mounting hole and two intersection holes, wherein bushings are provided in the crossbeam mounting hole and the two intersection holes, and the ends of the crossbeams are fixedly connected to the crossbeam mounting holes via the bushings;

[0007] The assembly method of the aircraft nose semi-enclosed bulkhead panel is carried out according to the following steps:

[0008] Step 1: Process the initial hole for the beam mounting hole on the side wall;

[0009] Step 2: Use the first aircraft nose semi-enclosed bulkhead panel assembly tool to position the side wall. The first aircraft nose semi-enclosed bulkhead panel assembly tool uses the initial hole of the crossbeam mounting hole as the main positioning point and the remaining intersection holes as auxiliary positioning points. The crossbeam is positioned based on the initial hole of the crossbeam mounting hole. The initial hole of the crossbeam mounting hole is processed into a final hole and a bushing is installed. Then, the crossbeam is connected to the side wall through the crossbeam mounting hole.

[0010] Step 3: Process the remaining intersection holes and install the bushings, and then perform additional processing on the bushings;

[0011] Step 4: Complete the assembly of the left and right wall assemblies according to steps 1 to 3 above.

[0012] Step 5: Use the second aircraft nose semi-enclosed bulkhead panel assembly tool to position the left side wall assembly and the right side wall assembly. A positioning assembly consisting of a first positioning member, a second positioning member, and a third positioning member is symmetrically provided on both sides of the second aircraft nose semi-enclosed bulkhead panel assembly tool. The first positioning member corresponds to the crossbeam mounting hole, and the second positioning member and the third positioning member correspond to the remaining two intersection holes respectively.

[0013] Step 6: Assemble the assembled left and right side wall assemblies onto the second aircraft nose semi-enclosed bulkhead panel assembly fixture, fix them by engaging the locating pins with the intersection holes, and then hoist them as a whole to the subsequent assembly station.

[0014] As an improvement to the above solution: in step 1, a 1mm margin is reserved when machining the initial hole of the beam mounting hole, and the initial hole position tolerance of the beam mounting hole is controlled to be 2 / 3 of the tolerance of the semi-enclosed bulkhead panel of the aircraft nose.

[0015] As an improvement to the above solution: in step 2, a plurality of positioning columns are provided on the first aircraft nose semi-enclosed bulkhead panel assembly tooling, the positioning columns are vertically fixed on the first aircraft nose semi-enclosed bulkhead panel assembly tooling, and the tops of the plurality of positioning columns are horizontally aligned with the crossbeam mounting holes and the remaining intersection holes respectively.

[0016] As an improvement to the above solution: in step five, a plurality of tooling positioning reference parts are evenly distributed on the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling, and when the left side wall assembly and the right side wall assembly are installed on the second aircraft nose semi-enclosed bulkhead panel assembly tooling, the bottoms of the side walls of the left side wall assembly and the right side wall assembly are flush with the bottoms of the tooling positioning reference parts.

[0017] As an improvement to the above solution: three tooling positioning reference parts are arranged at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling, and the three tooling positioning reference parts are distributed in a triangular shape and fixed at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling; a lifting ring is also fixed at the top of the second aircraft nose semi-enclosed bulkhead panel assembly tooling.

[0018] As an improvement to the above scheme: in step five, the positioning reference coaxiality of the first positioning member is controlled to be 1 / 3 of the tolerance of the aircraft's front landing gear assembly, the positioning reference position of the second positioning member and the third positioning member relative to the first positioning member is controlled to be 1 / 4 of the tolerance of the aircraft's front landing gear assembly, and the opening size tolerance between the two groups of positioning assemblies is controlled to be 0-0.1mm.

[0019] The beneficial effects of the present invention are as follows: the present invention adopts two assembly tools to assemble the wall panel assemblies on both sides of the aircraft nose semi-enclosed bulkhead panel separately and to assemble the wall panel assemblies on both sides, decomposes the process of the aircraft nose semi-enclosed bulkhead panel during the assembly process, and then optimizes the assembly method and allocates tolerances to ensure that the shape and position tolerances such as the position tolerance of each intersection, the coaxiality of the intersection, the parallelism of the intersection and the opening size of the aircraft nose semi-enclosed cabin wall panel meet the design requirements, thereby effectively improving the installation and assembly accuracy; and the present invention can also support and preserve the shape of the wall panel assemblies on both sides through the assembly tool, which can avoid deformation of the wall panel assemblies during the assembly and transportation of aircraft parts, thereby effectively ensuring that the shape and position tolerances will not be affected. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the semi-enclosed bulkhead panel at the nose of an aircraft;

[0021] Figure 2 A schematic diagram of the left side wall assembly and the right side wall assembly after being assembled with the first aircraft nose semi-enclosed bulkhead panel assembly tool;

[0022] Figure 3Schematic diagram of the assembly tool for the semi-enclosed bulkhead panel of the nose of the second aircraft;

[0023] Figure 4 This is a schematic diagram of the left side wall assembly and the right side wall assembly after being assembled with the second aircraft nose semi-enclosed bulkhead panel assembly tool.

[0024] Markings in the figure are: 100 - left side wall assembly, 200 - right side wall assembly, 310 - side wall, 320 - crossbeam, 330 - crossbeam mounting hole, 340 - intersection hole, 350 - bushing, 400 - first aircraft nose semi-enclosed bulkhead panel assembly tool, 410 - positioning column, 500 - second aircraft nose semi-enclosed bulkhead panel assembly tool, 510 - first positioning member, 520 - second positioning member, 530 - third positioning member, 540 - tool positioning reference member, 550 - lifting ring. DETAILED DESCRIPTION

[0025] To facilitate understanding of the present invention, the present invention is further described below with reference to the accompanying drawings.

[0026] In the description of the present invention, it should be noted that the directions or positional relationships indicated by terms such as "front", "rear", "left", "right", "up", "down", and "inside" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of description. They do not indicate or imply that the device or component referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limitations on the present invention.

[0027] like Figure 1 As shown, the aircraft nose semi-enclosed bulkhead panel according to the present invention includes a left sidewall assembly 100 and a right sidewall assembly 200. The left sidewall assembly 100 and the right sidewall assembly 200 have identical symmetrical structures. Both the left sidewall assembly 100 and the right sidewall assembly 200 comprise a sidewall 310 and a crossbeam 320. The sidewall 310 is provided with a crossbeam mounting hole 330 and two intersection holes 340, which are dispersed throughout the sidewall 310. The crossbeam mounting hole 330 is used to mount the crossbeam 320 on the sidewall 310, while the remaining intersection holes 340 serve as mounting holes for other mounting shafts. Bushings 350 are installed in both the crossbeam mounting hole 330 and the intersection holes 340. After the assembly of the aircraft nose semi-enclosed bulkhead panel is completed, the left side wall assembly 100 and the right side wall assembly 200 are spaced apart and symmetrical. The aircraft nose semi-enclosed bulkhead panel assembly method disclosed in the present invention uses the first aircraft nose semi-enclosed bulkhead panel assembly tool 400 and the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 to assemble the aircraft nose semi-enclosed bulkhead panel.

[0028] Specifically, the first aircraft nose semi-enclosed bulkhead panel assembly tool 400 used in the present invention is as follows: Figure 2As shown, the first aircraft nose semi-enclosed bulkhead panel assembly jig 400 has a base structure capable of supporting the ground, with multiple positioning posts 410 mounted on the base structure. The base structure's shape is not limited, as long as it can stably support the entire jig structure to ensure the stability of the first aircraft nose semi-enclosed bulkhead panel assembly jig 400. To save costs and improve the strength of the base structure, the present invention utilizes a horizontally arranged triangular frame as the base structure. A corresponding triangular frame is provided for each of the left sidewall assembly 100 and the right sidewall assembly 200, and the corresponding triangular frames of the two sidewall assemblies are connected and fixed. The number of positioning posts 410 used in the first aircraft nose semi-enclosed bulkhead panel assembly jig 400 is determined based on the number of locations to be positioned. In the present invention, at least three positioning posts 410 are used to locate different intersections. The positioning posts 410 are vertically fixed to the base structure, with their tops aligned with the crossbeam mounting holes 330 and the different intersection holes 340. In order to simplify the structure, a crossbar axially aligned with the crossbeam mounting holes 330 of the side wall assemblies on both sides can be directly used as the connecting part of the two triangular frames. At the same time, this crossbar can be used to directly position the crossbeam mounting holes 330 of the side wall assemblies on both sides.

[0029] Specifically, the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 used in the present invention is as follows: Figure 2 and Figure 3As shown, the second aircraft nose semi-enclosed bulkhead panel assembly fixture 500 is a frame structure. Two sets of positioning assemblies corresponding to the left sidewall assembly 100 and the right sidewall assembly 200 are fixedly mounted on the second aircraft nose semi-enclosed bulkhead panel assembly fixture 500. The two sets of positioning assemblies are respectively arranged on either side of the frame structure of the second aircraft nose semi-enclosed bulkhead panel assembly fixture 500. The positioning assemblies are used to locate the crossbeam mounting holes 330 and the intersection holes 340. Therefore, the number of positioning members in the positioning assembly should be consistent with the number of locations to be positioned. In the present invention, three positioning members are used to form the positioning assembly: a first positioning member 510, a second positioning member 520, and a third positioning member 530. The first positioning member 510 corresponds to the crossbeam mounting hole 330, and the second positioning member 520 and the third positioning member 530 correspond to the remaining two intersection holes 340, respectively. The positioning members can adopt conventional positioning structures in the prior art, such as positioning holes, positioning shafts, positioning sleeves, and other structures. In addition, in order to ensure the accuracy of positioning of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, the present invention further provides a tool positioning reference component 540 at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500. The number of the tool positioning reference components 540 is three, and the three tool positioning reference components 540 are distributed in a triangular shape and fixed to the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500. By providing the tool positioning reference components 540, a stable positioning foundation is provided for the second aircraft nose semi-enclosed bulkhead panel assembly tool 500; when the left side wall assembly 100 and the right side wall assembly 200 are installed on the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, the bottom of the side wall 310 of the left side wall assembly 100 and the right side wall assembly 200 are flush with the bottom of the tool positioning reference component 540. A lifting ring 550 is also fixed to the top of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 to facilitate lifting and transporting the side wall assembly and the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 to a subsequent assembly station after assembly.

[0030] The assembly method of the aircraft nose semi-enclosed bulkhead panel of the present invention is performed according to the following steps:

[0031] Step 1: Decompose the semi-enclosed bulkhead panel of the aircraft nose into a left side wall assembly 100 and a right side wall assembly 200, and then decompose the two sets of side wall assemblies into a side wall 310, a crossbar 320, and a bushing 350; then, according to the decomposition process, allocate tolerances to the components and side wall assemblies and adopt corresponding process control methods; machine the initial hole of the crossbeam mounting hole 330 on the side wall 310, and reserve a 1mm margin when machining the initial hole of the crossbeam mounting hole 330. The initial hole position tolerance of the crossbeam mounting hole 330 is controlled to be 2 / 3 of the tolerance of the semi-enclosed bulkhead panel of the aircraft nose.

[0032] Step 2: Use the first aircraft nose semi-enclosed bulkhead panel assembly tool 400 to position the side wall 310. The first aircraft nose semi-enclosed bulkhead panel assembly tool 400 uses the initial hole of the beam mounting hole 330 as the main positioning point and the remaining intersection holes 340 as auxiliary positioning points. The beam 320 is positioned based on the initial hole of the beam mounting hole 330. After the initial hole of the beam mounting hole 330 is processed into a final hole and the bushing 350 is installed, the beam 320 is connected to the side wall 310 through the beam mounting hole 330.

[0033] Step 3: Process the remaining intersection holes 340 and install the bushing 350, and then perform additional processing on the bushing 350; the beam mounting hole 330 and the remaining intersection holes 340 are processed using the same equipment for CNC processing to ensure that the beam 320 is coaxial with the beam mounting hole 330 and the position of the remaining intersection holes 340.

[0034] Step 4: Complete the assembly of the left wall assembly 100 and the right wall assembly 200 according to the above steps 1 to 3;

[0035] Step 5: Use the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 to position the left side wall assembly 100 and the right side wall assembly 200. The second aircraft nose semi-enclosed bulkhead panel assembly tool 500 is symmetrically provided with positioning assemblies consisting of a first positioning member 510, a second positioning member 520 and a third positioning member 530. The first positioning member 510 corresponds to the crossbeam mounting hole 330, and the second positioning member 520 and the third positioning member 530 correspond to the remaining two intersection holes 340 respectively; the positioning reference coaxiality of the first positioning member 510 is controlled to be 1 / 3 of the tolerance of the aircraft nose landing gear assembly, and the positioning reference position accuracy of the second positioning member 520 and the third positioning member 530 relative to the first positioning member 510 is controlled to be 1 / 4 of the tolerance of the aircraft nose landing gear assembly. The opening size tolerance between the two groups of positioning assemblies is controlled to be 0-0.1mm.

[0036] Step 6: Assemble the assembled left side wall assembly 100 and right side wall assembly 200 onto the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, and fix them by matching the locating pins with the intersection holes 340. The diameter tolerance of the locating pins is controlled according to G7, and bolts with threaded matching are provided on the locating pins to achieve thread tightening. After the assembly is completed, the completed aircraft nose semi-enclosed bulkhead panel is hoisted as a whole to the subsequent assembly station.

Claims

1. A method for assembling a semi-enclosed bulkhead panel at the nose of an aircraft, characterized by: A first aircraft nose semi-enclosed bulkhead panel assembly tool (400) and a second aircraft nose semi-enclosed bulkhead panel assembly tool (500) are used to assemble a left side wall assembly (100) and a right side wall assembly (200) spaced apart in the aircraft nose semi-enclosed bulkhead panel. The left side wall assembly (100) and the right side wall assembly (200) are symmetrical structures consisting of a side wall (310) and a crossbeam (320). A crossbeam mounting hole (330) and two intersection holes (340) are provided on the side wall (310). Bushings (350) are provided in the crossbeam mounting hole (330) and the two intersection holes (340). The end of the crossbeam (320) is fixedly connected to the crossbeam mounting hole (330) through the bushing (350). The assembly method of the aircraft nose semi-enclosed bulkhead panel is carried out according to the following steps: Step 1: machining a preliminary hole for the beam mounting hole (330) on the side wall (310); Step 2: Using the first aircraft nose semi-enclosed bulkhead panel assembly tool (400) to position the side wall (310), the first aircraft nose semi-enclosed bulkhead panel assembly tool (400) uses the initial hole of the beam mounting hole (330) as the main positioning point, and the remaining intersection holes (340) as auxiliary positioning points, and positions the beam (320) based on the initial hole of the beam mounting hole (330), and after the initial hole of the beam mounting hole (330) is processed into a final hole and the bushing (350) is installed, the beam (320) is connected to the side wall (310) through the beam mounting hole (330); Step 3: Process the remaining intersection holes (340) and install the bushing (350), and then perform additional processing on the bushing (350); Step 4: Complete the assembly of the left side wall assembly (100) and the right side wall assembly (200) according to the above steps 1 to 3; Step 5: Use the second aircraft nose semi-enclosed bulkhead panel assembly tool (500) to position the left side wall assembly (100) and the right side wall assembly (200). Positioning assemblies consisting of a first positioning member (510), a second positioning member (520) and a third positioning member (530) are symmetrically provided on both sides of the second aircraft nose semi-enclosed bulkhead panel assembly tool (500). The first positioning member (510) corresponds to the crossbeam mounting hole (330), and the second positioning member (520) and the third positioning member (530) respectively correspond to the remaining two intersection holes (340); Step 6: Assemble the assembled left side wall assembly (100) and right side wall assembly (200) onto the second aircraft nose semi-enclosed bulkhead panel assembly tool (500), fix them by matching the positioning pins with the intersection holes (340), and then hoist them as a whole to the subsequent assembly station.

2. The method for assembling a semi-enclosed bulkhead panel for an aircraft nose according to claim 1, wherein: In the step 1, a 1mm margin is reserved when machining the initial hole of the beam mounting hole (330), and the initial hole position tolerance of the beam mounting hole (330) is controlled to be 2 / 3 of the tolerance of the semi-enclosed bulkhead plate of the aircraft nose.

3. The method for assembling a semi-enclosed bulkhead panel for an aircraft nose according to claim 1, wherein: In the second step, a plurality of positioning posts (410) are provided on the first aircraft nose semi-enclosed bulkhead panel assembly tool (400), the positioning posts (410) are vertically fixed on the first aircraft nose semi-enclosed bulkhead panel assembly tool (400), and the tops of the plurality of positioning posts (410) are horizontally aligned with the crossbeam mounting holes (330) and the remaining intersection holes (340).

4. The method for assembling a semi-enclosed bulkhead panel for an aircraft nose according to claim 1, wherein: In the step 5, a plurality of tooling positioning reference pieces (540) are evenly distributed on the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool (500), and when the left side wall assembly (100) and the right side wall assembly (200) are installed on the second aircraft nose semi-enclosed bulkhead panel assembly tool (500), the bottoms of the side walls (310) of the left side wall assembly (100) and the right side wall assembly (200) are flush with the bottoms of the tooling positioning reference pieces (540).

5. The method for assembling a semi-enclosed bulkhead panel for an aircraft nose according to claim 4, wherein: The number of tooling positioning reference members (540) provided at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling (500) is three, and the three tooling positioning reference members (540) are distributed in a triangular shape and fixed at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling (500); A lifting ring (550) is also fixed on the top of the second aircraft nose semi-enclosed bulkhead panel assembly tool (500).

6. The method for assembling a semi-enclosed bulkhead panel for an aircraft nose according to claim 1, wherein: In step five, the positioning reference coaxiality of the first positioning member (510) is controlled to be 1 / 3 of the tolerance of the aircraft's front landing gear assembly, the positioning reference position of the second positioning member (520) and the third positioning member (530) relative to the first positioning member (510) is controlled to be 1 / 4 of the tolerance of the aircraft's front landing gear assembly, and the opening size tolerance between the two groups of positioning assemblies is controlled to be 0 to 0.1 mm.

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