Method for assembling semi-closed bulkhead plate of aircraft nose

Abstract

The invention discloses an aircraft nose semi-closed bulkhead plate assembling method. A left side wall assembly and a right side wall assembly which are arranged in an aircraft nose semi-closed bulkhead plate in a spaced mode are assembled through a first aircraft nose semi-closed bulkhead plate assembling tool and a second aircraft nose semi-closed bulkhead plate assembling tool. According to the method, the aircraft nose semi-closed cabin wall plate is subjected to process decomposition in the assembly process, and then the assembly method is optimized and subjected to tolerance distribution, so that it is guaranteed that the form and location tolerances such as the position tolerance, the coaxiality, the parallelism and the opening size of all intersection points in the aircraft nose semi-closed cabin wall plate meet the design requirements; therefore, the mounting and assembling precision is effectively improved; in addition, the supporting and shape preserving effects can be achieved on the wall plate assemblies on the two sides through the assembly tool, the wall plate assemblies can be prevented from deforming in the assembly and transportation process of the aircraft parts, and then it is effectively guaranteed that the form and location tolerance is 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 plate at an aircraft nose. Background Art

[0002] In the manufacture of aircraft, the semi-enclosed cabin structure at the bottom of the nose needs to be equipped with multiple groups of functional axis installation intersections due to special functional requirements. Since the shape and position tolerances of these installation intersections are as low as 0.01mm, the installation precision is required to be high and the manufacturing difficulty is great. In addition, due to the structural characteristics of the semi-enclosed cabin, it is easy to deform after assembly. In order to improve the installation precision, the prior art leaves a margin when processing the 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 of each intersection are fine-machined using special equipment to ensure the shape and position tolerances. The above-mentioned prior art assembly method requires the use of additional special equipment, which increases the production cost. In addition, the semi-enclosed cabin assembly has been assembled when fine machining is performed. The fine machining is limited by the construction space, which will increase the difficulty of machining and easily cause quality accidents.

[0003] A 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 non-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, a clamping plate for fixing the skeleton is fixedly connected to the top of the prism, 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, and 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 improve the scope of application of the assembly but not the accuracy of the assembly. Therefore, it cannot meet the assembly accuracy requirements of the aircraft semi-enclosed cabin 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 cabin wall panel at the nose of an aircraft, which can effectively improve the assembly accuracy of the semi-enclosed cabin wall panel at the nose of the aircraft.

[0006] In order to solve the above technical problems, the technical solution adopted by the present invention is: an assembly method of a semi-enclosed bulkhead panel of an aircraft nose, using a first semi-enclosed bulkhead panel assembly tool and a second semi-enclosed bulkhead panel assembly tool to assemble a left wall assembly and a right wall assembly arranged in the semi-enclosed bulkhead panel of the aircraft nose, the left wall assembly and the right wall assembly are symmetrical structures composed of side walls and cross beams, a cross beam mounting hole and two intersection holes are provided on the side walls, bushings are provided in the cross beam mounting hole and the two intersection holes, and the end of the cross beam is fixedly connected to the cross beam mounting hole through the bushing;

[0007] The assembly method of the semi-enclosed bulkhead panel of the aircraft nose 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 locate the side wall. The first aircraft nose semi-enclosed bulkhead panel assembly tool uses the initial hole of the beam mounting hole as the main positioning point, and the other intersection holes as auxiliary positioning points. The initial hole of the beam mounting hole is used as a reference to locate the beam. After the initial hole of the beam mounting hole is processed into a final hole and a bushing is installed, the beam is connected to the side wall through the beam mounting hole.

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

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

[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. Positioning components consisting of a first positioning member, a second positioning member and a third positioning member are symmetrically arranged 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 side wall assembly and right side wall assembly onto the second aircraft nose semi-enclosed bulkhead panel assembly tooling, fix them by matching the positioning pins with the intersection holes, and then hoist them as a whole to the subsequent assembly station.

[0014] As an improvement of the above scheme: in the step 1, a 1mm margin is reserved when processing 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 of the above scheme: in the 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 of the above scheme: in the 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 bottom of the side walls of the left side wall assembly and the right side wall assembly are flush with the bottom of the tooling positioning reference parts.

[0017] As an improvement of the above scheme: the number of tooling positioning reference parts arranged at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tooling is three, and the three tooling positioning reference parts are distributed in a triangle 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 of the above scheme: in the 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 and third positioning members 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 kinds of assembly tools to assemble the wall panel assemblies on both sides of the aircraft nose semi-enclosed bulkhead panel respectively and to assemble the wall panel assemblies on both sides, decomposes the process of the semi-enclosed bulkhead panel on the aircraft nose 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 point, the coaxiality of the intersection point, the parallelism of the intersection point and the opening size in the wall panel of the aircraft nose semi-enclosed cabin meet the design requirements, thereby effectively improving the accuracy of installation and assembly; and the present invention can also play a role of supporting and preserving 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 It is a schematic diagram of the semi-enclosed bulkhead panel at the nose of an aircraft;

[0021] Figure 2 It is 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 It 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 tooling.

[0024] Marked in the figure: 100-left side wall assembly, 200-right side wall assembly, 310-side wall, 320-cross beam, 330-cross beam 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 piece, 520-second positioning piece, 530-third positioning piece, 540-tool positioning reference piece, 550-lifting ring. DETAILED DESCRIPTION

[0025] In order to facilitate the understanding of the present invention, the present invention is further described below in conjunction with 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 involved in the present invention includes a left wall assembly 100 and a right wall assembly 200, and the left wall assembly 100 and the right wall assembly 200 are symmetrical structures of the same assembly. The components of the left wall assembly 100 and the right wall assembly 200 both include a side wall 310 and a crossbeam 320, and a crossbeam mounting hole 330 and two intersection holes 340 are provided on the side wall 310, and the crossbeam mounting hole 330 and the two intersection holes 340 are dispersedly distributed on the side wall 310; the crossbeam mounting hole 330 is used to realize the installation of the crossbeam 320 on the side wall 310, and the remaining intersection holes 340 are used as installation holes for other installation shafts, and bushings 350 are installed in the crossbeam mounting hole 330 and the intersection holes 340. After the assembly of the semi-enclosed bulkhead panel of the aircraft nose is completed, the left side wall assembly 100 and the right side wall assembly 200 are arranged at intervals and are bilaterally symmetrical. The assembly method of the semi-enclosed bulkhead panel of the aircraft nose disclosed in the present invention realizes the assembly of the semi-enclosed bulkhead panel of the aircraft nose by adopting the first semi-enclosed bulkhead panel assembly tool 400 and the second semi-enclosed bulkhead panel assembly tool 500 of the aircraft nose.

[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 tool 400 has a base structure that can be supported on the ground, and a plurality of positioning columns 410 are installed on the base structure. The shape of the base structure is not limited, as long as it can stably support the entire tool structure to ensure the stability of the entire first aircraft nose semi-enclosed bulkhead panel assembly tool 400. In order to save costs and improve the strength of the base structure, the present invention adopts a horizontally arranged triangular frame as the base structure, and the left side wall assembly 100 and the right side wall assembly 200 are respectively provided with a triangular frame as the base structure, and the triangular frames corresponding to the two side wall assemblies are connected and fixed. The number of positioning columns 410 used in the first aircraft nose semi-enclosed bulkhead panel assembly tool 400 is set according to the number of parts to be positioned. In the present invention, at least three positioning columns 410 are used to position different intersections respectively; the positioning columns 410 are vertically fixed on the base structure, and the tops of the positioning columns 410 are respectively aligned with the beam mounting holes 330 and 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, and 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 tool 500 is a frame structure, and two sets of positioning components corresponding to the left wall assembly 100 and the right wall assembly 200 are fixedly arranged on the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, and the two sets of positioning components are respectively arranged on both sides of the frame structure of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500. The positioning component is used to position the crossbeam mounting hole 330 and the intersection hole 340, so the number of positioning members in the positioning component should be consistent with the number of positions to be positioned. In the present invention, three positioning members are used to form the positioning component, namely, the first positioning member 510, the second positioning member 520 and the 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 member can adopt a conventional positioning structure in the prior art, such as a positioning hole, a positioning shaft, a positioning sleeve and the like. 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 also sets a tool positioning reference part 540 at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, and the number of the tool positioning reference parts 540 is three. The three tool positioning reference parts 540 are distributed in a triangular shape and fixed at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500. By setting the tool positioning reference parts 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 is flush with the bottom of the tool positioning reference part 540. A lifting ring 550 is also fixed to the top of the second aircraft nose semi-enclosed bulkhead panel assembly tool 500, so as to facilitate the overall lifting and transportation of the side wall assembly and the second aircraft nose semi-enclosed bulkhead panel assembly tool 500 after assembly, so as to transport them to the subsequent assembly station.

[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, process decomposition of the semi-enclosed bulkhead panel of the aircraft nose is performed, and the semi-enclosed bulkhead panel of the aircraft nose is decomposed into a left wall component 100 and a right wall component 200, and then the two groups of side wall components are decomposed into a side wall 310, a cross bar 320 and a bushing 350; then according to the decomposition process, tolerance allocation is performed on the parts and side wall components and corresponding process control methods are adopted; the initial hole of the beam mounting hole 330 is processed on the side wall 310, and a 1mm margin is reserved when processing 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 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 other 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 three, process the remaining intersection holes 340 and install the bushing 350, and then perform additional processing on the bushing 350; the same equipment is used for CNC processing of the beam mounting hole 330 and the remaining intersection holes 340 to ensure that the beam 320 is coaxial with the beam mounting hole 330 and the position accuracy 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 component 100 and the right side wall component 200. The second aircraft nose semi-enclosed bulkhead panel assembly tool 500 is symmetrically provided with positioning components consisting of a first positioning member 510, a second positioning member 520 and a third positioning member 530 on both sides. 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 front landing gear assembly, and 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 front landing gear assembly, and the opening size tolerance between the two groups of positioning components is controlled to be 0-0.1mm.

[0036] Step six, 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 threaded bolts 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 in that: 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 composed 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 semi-enclosed bulkhead panel of the aircraft nose 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 uses the initial hole of the beam mounting hole (330) as a reference to position the beam (320); after the initial hole of the beam mounting hole (330) is processed into a final hole and a 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 wall assembly (100) and the right 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 components consisting of a first positioning member (510), a second positioning member (520) and a third positioning member (530) are symmetrically arranged 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) correspond to the remaining two intersection holes (340) respectively. 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 the cooperation of the positioning pins and 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 of an aircraft nose as claimed in claim 1, characterized in that: In the step 1, a 1 mm margin is reserved when processing 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 of an aircraft nose as claimed in claim 1, characterized in that: In the second step, a plurality of positioning columns (410) are arranged on the first aircraft nose semi-enclosed bulkhead panel assembly tool (400), the positioning columns (410) are vertically fixed on the first aircraft nose semi-enclosed bulkhead panel assembly tool (400), and the tops of the plurality of positioning columns (410) are horizontally aligned with the crossbeam mounting holes (330) and the remaining intersection holes (340), respectively.

4. The method for assembling a semi-enclosed bulkhead panel of an aircraft nose as claimed in claim 1, characterized in that: In the step 5, a plurality of tooling positioning reference pieces (540) are evenly distributed at 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 of an aircraft nose as claimed in claim 4, characterized in that: The number of tooling positioning reference parts (540) arranged at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool (500) is three, and the three tooling positioning reference parts (540) are distributed in a triangular shape and fixed at the bottom of the second aircraft nose semi-enclosed bulkhead panel assembly tool (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 of an aircraft nose as claimed in claim 1, characterized in that: 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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