Multi-stage progressive assembly method suitable for double-curvature weak-rigidity component of large aircraft

Abstract

The invention provides a multi-stage progressive assembly method suitable for double-curvature weak-rigidity components of a large aircraft, and belongs to the technical field of aircraft assembly.The multi-stage progressive assembly method comprises the steps that firstly, an upper left wall plate assembly, a lower left wall plate assembly, an upper right wall plate assembly, a lower right wall plate assembly, a top wall plate assembly and a bottom wall plate assembly are assembled respectively; the left half shell part and the right half shell part are assembled; thirdly, the right half shell part and the bottom wall plate assembly are assembled into a super wall plate part; and finally, the super wall plate component, the floor beam assembly, the left half shell component and the top wall plate assembly are assembled to complete final assembly. A traditional technology is broken through, a brand-new process separation surface division mode, a vertical posture assembly mode and a multi-stage progressive key element control mode are adopted, the product quality and the assembly efficiency can be effectively improved, the assembly coordination difficulty is greatly reduced, human engineering is met, the labor productivity is improved, and the production cost is reduced. And the requirement for rapidly improving the assembly capacity of the double-curvature part of the large civil aircraft can be met.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft assembly, and relates to a multi-stage progressive assembly method suitable for double-curvature weak-rigidity components of large aircraft. Background Art

[0002] At present, the assembly of the double-curvature barrel section of commercial large aircraft usually adopts the method of butt-jointing the upper and lower half shells, that is, in accordance with the X, Y, and Z postures of the aircraft (in the aircraft coordinate system), the three wall panel components of the upper half shell (including the upper left wall panel component, the upper right wall panel component and the top wall panel component), the three wall panel components of the lower half shell (including the lower left wall panel component, the lower right wall panel component and the bottom wall panel component) and the floor beam component are first formed respectively, and then the components are assembled to form the upper and lower half shell components respectively, and finally the upper and lower half shells are butt-jointed to form the barrel section component, such as Figure 1 As shown. This traditional assembly method of hyperbolic barrel sections has complex coordination relationships and often requires the simultaneous assembly of more than three components to form lower-level components, and the synchronous control of multiple key control points of the docking interface, which is difficult and has many technical problems. In addition, due to the influence of gravity and the lack of rigidity of the components themselves, the product will deform when the upper and lower shells are docked, resulting in aerodynamic dimension deviations and a large number of interference or gap problems; at the same time, there are ergonomic factors in the traditional assembly mode, and operators need to adopt a prone or upward posture to make holes or rivets. The above problems lead to low assembly efficiency of hyperbolic barrel section components, frequent technical problems, and high costs, which greatly affect the improvement of product assembly speed. Therefore, technical innovation is urgently needed to solve a series of problems. Summary of the invention

[0003] In order to solve the above problems, the present invention provides a multi-stage progressive assembly method suitable for large aircraft hyperbolic weak rigidity components. It breaks through traditional technology and adopts a new process separation surface division method, a vertical posture assembly method and a multi-stage progressive key element control method, etc. It is suitable for the assembly of large-size hyperbolic aircraft components, can effectively improve product quality and assembly efficiency, greatly reduce the difficulty of assembly coordination, conform to ergonomics, improve assembly efficiency and labor productivity, and can meet the demand for rapid improvement of assembly capacity of hyperbolic components of large civil aircraft.

[0004] The specific technical solutions of the present invention are as follows:

[0005] A multi-stage progressive assembly method applicable to large aircraft double-curvature weak rigidity components, the multi-stage progressive assembly method comprising the following steps:

[0006] Step 1, wall panel assembly stage:

[0007] The assembly of the upper left wall panel assembly, the lower left wall panel assembly, the upper right wall panel assembly, the lower right wall panel assembly, the top wall panel assembly and the bottom wall panel assembly are completed respectively; during the assembly process, the frames and long stringers in each assembly are used as the skeleton for positioning first, and then the outer shapes of the positioned frames and long stringers are used as the positioning reference for positioning the skin; after positioning is completed, the assembly of the upper left wall panel assembly, the lower left wall panel assembly, the upper right wall panel assembly, the lower right wall panel assembly, the top wall panel assembly and the bottom wall panel assembly are completed respectively through hole making, burr removal and riveting operations.

[0008] Step 2, left and right half shell assembly stage:

[0009] Adopting the principle of minimum coordination, the upper left wall panel assembly and the lower left wall panel assembly are assembled to form the left half-shell component, and the upper right wall panel assembly and the lower right wall panel assembly are assembled to form the right half-shell component; during the assembly of the left half-shell component, the upper left wall panel assembly and the lower left wall panel assembly respectively use their frames as the positioning reference to complete the positioning and docking of the two, and synchronously control the frame docking, skin docking and strip plate docking on the assembly interface of the two components; during the assembly of the right half-shell component, the upper right wall panel assembly and the lower right wall panel assembly also use their frames as the positioning reference to complete the positioning and docking of the two, and synchronously control the three key elements of frame docking, skin docking and strip plate docking on the assembly interface of the two components; after positioning, the left and right half-shell components are assembled respectively through hole making, deburring and riveting operations.

[0010] Step 3, super wall panel assembly stage:

[0011] Adopting the principle of minimum coordination and vertical assembly, the right half shell component and the bottom wall panel assembly are assembled to form a super wall panel component. Specifically:

[0012] The right half shell component and the bottom wall panel assembly are rotated to be perpendicular to the aircraft attitude respectively. Under the attitude perpendicular to the aircraft, the skin shapes of the two are used as the positioning reference to complete the positioning and docking of the right half shell component and the bottom wall panel assembly. The frame docking, skin docking and strip plate docking on the assembly interface of the two are controlled synchronously. After positioning, the super wall panel component assembly is finally completed through hole making, deburring and riveting operations.

[0013] Step 4, final assembly stage:

[0014] The super wall panel component, floor beam assembly, left half shell component and top wall panel assembly are rotated to be perpendicular to the aircraft posture respectively, and the super wall panel component, left half shell component, floor beam assembly and top wall panel assembly are positioned and docked in sequence under the perpendicular attitude to the aircraft, wherein the skin shape of the super wall panel component and the left half shell component is used as the positioning reference when positioning and docking, the floor beam assembly is positioned and docked based on the bottom plate beam reference, and the skin shape of the top wall panel assembly, the super wall panel component and the left half shell component is used as the positioning reference when positioning and docking the top wall panel assembly; finally, the assembly is completed through hole making, burr removal and riveting operations.

[0015] Furthermore, the multi-stage progressive assembly method adopts a left and right half-shell docking method to replace the traditional upper and lower half-shell docking method.

[0016] Furthermore, in the steps 2 and 3, the principle of minimum coordination refers to the form of docking assembly through only two components (different from the existing form of docking assembly through three or more components), and only the key elements on the assembly interface of the two components need to be synchronously controlled. The key elements include frame docking, skin docking and strip plate docking, which can reduce the number of assembly interfaces, and then reduce the number of key elements that need to be synchronously controlled on the assembly interface, thereby improving assembly accuracy and work efficiency.

[0017] Furthermore, in the step 3, the right half shell component and the bottom wall panel assembly are respectively rotated to be perpendicular to the aircraft posture as follows: in the aircraft coordinate system, the right half shell component and the bottom wall panel assembly are rotated 90° around the Y axis along the XZ plane to be perpendicular to the aircraft posture with their respective installation postures on the aircraft as initial postures, and the ends of the two facing the nose are on top.

[0018] Furthermore, in the step 3, a shape controller is installed at the skin edge of the right half shell component and the bottom wall panel assembly to control the deformation of the two in the circumferential direction.

[0019] Furthermore, in the step 4, the super wall panel component, the floor beam assembly, the left half shell component and the top wall panel assembly are respectively rotated to be perpendicular to the aircraft posture as follows: in the aircraft coordinate system, the super wall panel component, the floor beam assembly, the left half shell component and the top wall panel assembly are respectively rotated 90° around the Y axis along the XZ plane to be perpendicular to the aircraft posture with their respective installation postures on the aircraft as initial postures, and the super wall panel component, the floor beam assembly, the left half shell component and the top wall panel assembly are all with one end facing the nose of the aircraft on top.

[0020] Furthermore, in the step 4, a shape controller is installed at the outer edge of the skin of the super wall panel component, the left half shell component and the top wall panel assembly to control the deformation of the three in the circumferential direction.

[0021] The beneficial effects of the present invention are:

[0022] 1. The present invention adopts a new process separation surface division method to reduce the assembly interface control area, reduce the number of key elements that need to be synchronously controlled, and improve assembly accuracy and work efficiency.

[0023] 2. The vertical assembly method is adopted in some steps of the present invention, which eliminates the deformation of key assembly docking elements (such as skin, frame, etc.) along gravity and greatly reduces assembly coordination problems; at the same time, the vertical assembly method is in line with ergonomic principles and improves operator efficiency.

[0024] 3. The present invention adopts multi-stage progressive key element control, which improves the rigidity of each stage of assembly, specifically solves the deformation in the circumferential direction (aerodynamic shape) caused by vertical posture assembly, and improves product quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the assembly process of a typical hyperbolic aircraft barrel section component.

[0026] Figure 2 Schematic diagram of assembling the left half shell components using the principle of minimum coordination.

[0027] Figure 3 Schematic diagram of assembling the right half shell components using the principle of minimum coordination.

[0028] Figure 4 Schematic diagram of assembling super wall panel components using the principle of minimum coordination.

[0029] Figure 5 This is a schematic diagram of assembling super wall panel components in a vertical assembly manner.

[0030] Figure 6 This is a schematic diagram of the final assembly stage using a vertical assembly method.

[0031] Figure 7 Schematic diagrams of key element control in each stage, where (a) is a schematic diagram of key element control in the panel assembly stage, where the arrow indicates the box used as a positioning reference; (b) is a schematic diagram of key element control in the left and right half-shell assembly stage, where the arrow indicates the box used as a positioning reference; (c) is a schematic diagram of key element control in the super panel assembly stage, where the arrow indicates the shape controller. DETAILED DESCRIPTION

[0032] The technical solution of the present invention is described clearly and completely below. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments improved or adjusted by ordinary technicians in the field belong to the protection scope of the present invention.

[0033] A multi-stage progressive assembly method suitable for large aircraft double-curvature weak rigidity components. In order to effectively reduce the technical coordination problems caused by multi-component double-curvature assembly, the present invention adopts a new process separation surface division method, that is, the traditional upper and lower half shell docking method is no longer used, but replaced by the left and right half shell docking method. The multi-stage progressive assembly method includes the following steps:

[0034] Step 1, wall panel assembly stage;

[0035] Complete the assembly of the upper left wall panel assembly, lower left wall panel assembly, upper right wall panel assembly, lower right wall panel assembly, top wall panel assembly, bottom wall panel assembly and bottom beam assembly respectively. During the assembly process, the frame and long stringer in each assembly are used as the skeleton for positioning first, and the shape of the positioned frame and long stringer is used as the positioning reference to position the skin (such as Figure 7 As shown in (a), the arrow in the figure indicates the frame used as the positioning reference). After the positioning is completed, hole making, burr removal and riveting operations are performed to complete the assembly of each component. In the panel assembly stage, according to the stress conditions of each component during the assembly process, the method of positioning the skin with the positioned frame and long stringer as the reference can achieve the purpose of controlling the shape of the entire panel and improving the rigidity of the panel assembly.

[0036] Step 2, left and right half shell assembly stage;

[0037] The principle of minimum coordination is adopted, that is, only through the docking assembly of two components, the upper left wall panel component and the lower left wall panel component are assembled into the left half shell component, and the upper right wall panel component and the lower right wall panel component are assembled into the right half shell component. When the components are docked and assembled, the key elements on the assembly interface need to be controlled synchronously. The key elements include frame docking, skin docking and strip board docking. The more assembly interfaces there are, the more key requirements need to be controlled synchronously. The principle of minimum coordination is adopted, and the existing three or more component docking assembly forms are replaced by the docking assembly form of two components. This can reduce the number of assembly interfaces. Only the assembly interface between the two components needs to be controlled, thereby reducing the number of key elements that need to be controlled synchronously, thereby improving assembly accuracy and work efficiency.

[0038] Specific:

[0039] The frame in the upper left wall panel assembly and the lower left wall panel assembly is the positioning reference (such as Figure 7 As shown in (b), the arrow in the figure indicates the frame used as the positioning reference), the two are positioned and docked, and the frame docking, skin docking and strip board docking on the assembly interface of the two components are synchronously coordinated and controlled during the process, such as Figure 2 As shown in the figure, after positioning, hole making, burr removal and riveting operations are performed to complete the assembly of the left half shell component; similarly, the frame of the upper right wall panel assembly and the lower right wall panel assembly are used as the positioning reference, and the two are positioned using the tooling. During the process, the frame docking, skin docking and strip board docking on the assembly interface of the two components are synchronously coordinated and controlled, as shown in the figure. Figure 3 As shown, after positioning, hole making, burr removal and screwing operations are performed to complete the assembly of the right half shell component; in the left and right half shell assembly stage, according to the rigidity changes and stress conditions of each component during the assembly process, the frame is used as the positioning reference, which can control the appearance of the left and right half shell components and further improve the rigidity.

[0040] Step 3, super wall panel assembly stage;

[0041] Adopting the principle of minimum coordination and vertical assembly, the right half shell component and the bottom wall panel assembly are assembled to form a super wall panel component. Specifically:

[0042] Install the shape controller at the edge of the skin of the right half shell component and the bottom wall panel assembly, establish the aircraft coordinate system with the aircraft flight direction as the X-axis, the wing extension direction as the Y-axis, and the direction perpendicular to the XY plane as the Z-axis. Take the right half shell component and the bottom wall panel assembly as the initial posture, rotate 90° around the Y-axis along the XZ plane to the posture perpendicular to the aircraft, with the end of the two facing the nose direction on the top, as shown in the figure. Figure 5 As shown; taking the skin shapes of the two, that is, the installed shape controller as the positioning reference, the right half shell component and the bottom wall panel assembly are positioned perpendicular to the aircraft attitude, and the frame docking, skin docking and strip board docking on the assembly interface of the two are synchronously controlled, as shown Figure 4 As shown, after positioning, hole making, burring and riveting operations are performed to complete the assembly of the super wall panel components.

[0043] The reason why the vertical assembly method is adopted in the super wall panel assembly stage is that the right half shell component and the bottom wall panel assembly are large-sized weak rigid component products. When assembled in the existing position parallel to the aircraft attitude, they will be affected by gravity and will produce deformation along the Z direction, that is, the direction of gravity, which will cause the aerodynamic shape size to exceed the tolerance and cause gaps or interference when the frame and the skin are connected. The vertical assembly method can eliminate the deformation of key connection elements including the skin and the frame along the direction of gravity, but while maintaining a good shape in the Z direction, it is easy to produce deformation in the circumferential direction, such as contraction or extension along the radius. Therefore, a shape controller is set on the outer edge of the skin of the right half shell component and the bottom wall panel assembly to control the deformation in the circumferential direction, such as Figure 7 As shown in (c), the arrow in the figure indicates the shape controller. In addition, since the right half shell component and the bottom wall panel assembly have good process control in steps 1 and 2, the shapes of the two are well controlled and have sufficient rigidity. Considering the rigidity change and stress of the right half shell component and the bottom wall panel assembly during the assembly process, the super wall panel assembly stage uses the skin shape of the two as the positioning reference to meet the rigidity and shape control requirements.

[0044] Step 4, final assembly stage;

[0045] like Figure 6As shown, a shape controller is installed at the outer edge of the skin of the super wall panel component, the left half shell component and the top wall panel assembly, and the super wall panel component, the floor beam assembly, the left half shell component and the top wall panel assembly are respectively rotated 90° around the Y axis along the XZ plane to be perpendicular to the aircraft posture with their respective installation postures on the aircraft as the initial posture, and the super wall panel component, the floor beam assembly, the left half shell component and the top wall panel assembly are all positioned with one end facing the nose direction upward; first, the super wall panel component is positioned perpendicular to the aircraft posture with the skin, that is, the installed shape controller, as a positioning reference, and then the left half shell component is positioned and docked with the super wall panel component with the shape controller as a positioning reference in the posture perpendicular to the aircraft, and then the floor beam assembly is overlapped with the super wall panel component and the left half shell component based on the bottom plate beam reference, and finally the top wall panel assembly is positioned and docked with the three with its own skin, the super wall panel component and the left half shell component, that is, the shape controller, as the positioning reference, and then the assembly is completed through hole making, deburring and riveting operations.

[0046] The reasons for using the vertical assembly method and the skin as the positioning reference in the final assembly stage are the same as those in the super panel assembly stage. In addition, the vertical assembly method in the super panel assembly stage and the final assembly stage can make the operating parts face the operator directly, and the operator can operate in a composite ergonomic posture, which greatly improves the operating efficiency.

[0047] In order to cooperate with the new process separation surface division method and the vertical posture assembly method, the present invention adopts a multi-stage progressive key element control method, that is, in different assembly stages, different key elements are controlled step by step according to the changes in the rigidity and stress conditions of each component and part, including: in the wall panel assembly stage, the frames and long stringers in each component are used as the skeleton for positioning, and the skin is positioned with the shape of the positioned frame and long stringer as the positioning reference; in the left and right half-shell assembly stage, the frame is used as the positioning reference to connect the wall panel components; in the super wall panel assembly stage and the final assembly stage, due to the use of the vertical posture assembly method, the skin is selected as the positioning reference, and the circumferential deformation is controlled by setting a shape controller at the edge of the skin.

[0048] The above-described embodiments merely express the implementation methods of the present invention, but they should not be understood as limiting the scope of the present invention. It should be pointed out that for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, which all belong to the protection scope of the present invention.

Claims

1. A multi-stage progressive assembly method suitable for large aircraft double-curvature weak rigidity components, characterized in that: The multi-stage progressive assembly method comprises the following steps: Step 1, wall panel assembly stage: Complete the assembly of the upper left wall panel assembly, the lower left wall panel assembly, the upper right wall panel assembly, the lower right wall panel assembly, the top wall panel assembly and the bottom wall panel assembly respectively; Step 2, left and right half shell assembly stage: Adopting the principle of minimum coordination, the upper left wall panel assembly and the lower left wall panel assembly are assembled to form a left half shell component, and the upper right wall panel assembly and the lower right wall panel assembly are assembled to form a right half shell component; Step 3, super wall panel assembly stage: Adopting the principle of minimum coordination and vertical posture assembly, the right half shell component and the bottom wall panel assembly are assembled to form a super wall panel component; Step 4, final assembly stage: The super wall panel components, floor beam assemblies, left half shell components and top wall panel assemblies are assembled in a vertical posture to complete the final assembly.

2. A multi-stage progressive assembly method for large aircraft double-curvature weak rigidity components according to claim 1, characterized in that: The specific steps include: Step 1, wall panel assembly stage: The upper left wall panel assembly, the lower left wall panel assembly, the upper right wall panel assembly, the lower right wall panel assembly, the top wall panel assembly and the bottom wall panel assembly are assembled respectively; during the assembly process, the frames and long stringers in each assembly are used as the skeleton for first positioning, and then the outer shapes of the positioned frames and long stringers are used as the positioning reference for positioning the skin; after the positioning is completed, the upper left wall panel assembly, the lower left wall panel assembly, the upper right wall panel assembly, the lower right wall panel assembly, the top wall panel assembly and the bottom wall panel assembly are assembled respectively through hole making, burr removal and riveting operations; Step 2, left and right half shell assembly stage: Adopting the principle of minimum coordination, the upper left wall panel assembly and the lower left wall panel assembly are assembled to form the left half shell component, and the upper right wall panel assembly and the lower right wall panel assembly are assembled to form the right half shell component; during the assembly of the left half shell component, the upper left wall panel assembly and the lower left wall panel assembly respectively use their frames as the positioning reference to complete the positioning docking of the two, and synchronously control the frame docking, skin docking and strip plate docking on the assembly interface of the two components; during the assembly of the right half shell component, the upper right wall panel assembly and the lower right wall panel assembly also use their frames as the positioning reference to complete the positioning docking of the two, and synchronously control the frame docking, skin docking and strip plate docking on the assembly interface of the two components; after positioning, the left and right half shell components are assembled respectively through hole making, deburring and riveting operations; Step 3, super wall panel assembly stage: Adopting the principle of minimum coordination and vertical assembly, the right half shell component and the bottom wall panel assembly are assembled to form a super wall panel component. Specifically: The right half shell component and the bottom wall panel assembly are rotated to be perpendicular to the aircraft posture respectively. Under the perpendicular aircraft posture, the skin shape of the two is used as the positioning reference to complete the positioning docking of the right half shell component and the bottom wall panel assembly. The frame docking, skin docking and strip board docking on the assembly interface of the two are synchronously controlled. After positioning, the hole making, deburring and riveting operations are carried out to finally complete the assembly of the super wall panel component. Step 4, final assembly stage: The super wall panel components, floor beam components, left half shell components and top wall panel components are assembled in a vertical posture to complete the final assembly. Specifically: The super wall panel component, floor beam assembly, left half shell component and top wall panel assembly are rotated to be perpendicular to the aircraft posture respectively, and the super wall panel component, left half shell component, floor beam assembly and top wall panel assembly are positioned and docked in sequence under the perpendicular attitude to the aircraft, wherein the skin shape of the super wall panel component and the left half shell component is used as the positioning reference when positioning and docking, the floor beam assembly is positioned and docked based on the bottom plate beam reference, and the skin shape of the top wall panel assembly, the super wall panel component and the left half shell component is used as the positioning reference when positioning and docking the top wall panel assembly; finally, the assembly is completed through hole making, burr removal and riveting operations.

3. A multi-stage progressive assembly method for double-curvature weak rigidity components of large aircraft according to claim 1 or 2, characterized in that: The multi-stage progressive assembly method adopts the left and right half-shell docking mode to replace the upper and lower half-shell docking mode.

4. A multi-stage progressive assembly method for double-curvature weak rigidity components of large aircraft according to claim 1 or 2, characterized in that: In the steps 2 and 3, the principle of minimum coordination refers to the form of docking assembly through only two components, and only the key elements on the assembly interface of the two components need to be synchronously controlled, and the key elements include frame docking, skin docking and strip plate docking.

5. The multi-stage progressive assembly method for large aircraft double-curvature weak rigidity components according to claim 2, characterized in that: In the step 3, the right half shell component and the bottom wall panel assembly are rotated to be perpendicular to the aircraft posture respectively. Specifically, in the aircraft coordinate system, the right half shell component and the bottom wall panel assembly are rotated 90° around the Y axis along the XZ plane to be perpendicular to the aircraft posture with their respective installation postures on the aircraft as the initial posture, and the ends of the two facing the nose are on top.

6. A multi-stage progressive assembly method for double-curvature weak rigidity components of large aircraft according to claim 2 or 5, characterized in that: In the step 3, a shape controller is installed at the skin edge of the right half shell component and the bottom wall panel assembly to control the deformation of the two in the circumferential direction.

7. A multi-stage progressive assembly method for large aircraft double-curvature weak rigidity components according to claim 2, characterized in that: In the step 4, the super wall panel component, floor beam assembly, left half shell component and top wall panel assembly are respectively rotated to be perpendicular to the aircraft posture. Specifically, in the aircraft coordinate system, the super wall panel component, floor beam assembly, left half shell component and top wall panel assembly are respectively rotated 90° around the Y axis along the XZ plane to be perpendicular to the aircraft posture with their respective installation postures on the aircraft as the initial posture, and the super wall panel component, floor beam assembly, left half shell component and top wall panel assembly are all with the end facing the nose direction on top.

8. A multi-stage progressive assembly method for double-curvature weak rigidity components of large aircraft according to claim 2 or 7, characterized in that: In the step 4, a shape controller is installed at the outer edge of the skin of the super wall panel component, the left half shell component and the top wall panel assembly to control the deformation of the three in the circumferential direction.

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