Installation method of large-size half-enveloping structure composite fairing

Abstract

The invention provides an installation method for a large-size half-enveloping structure composite fairing, and belongs to the technical field of aircraft assembly.The method specifically comprises the steps that a front partition plate and a rear partition plate of a middle fairing and a connecting piece of a fuselage are positioned and installed on the fuselage, so that the positioning reference of the middle fairing on the fuselage is determined; the middle fairing and the connecting piece are connected in a positioning mode, and installation of the middle fairing is completed; the middle fairing is used as a main reference for positioning the front fairing and the rear fairing on the fuselage, and the front fairing and the rear fairing are installed; the positions of the front fairing and the rear fairing in the heading direction are adjusted by taking the appearances of the front partition plate and the rear partition plate of the middle fairing and the opposite seam gap as the positioning reference of the front fairing and the rear fairing; the opposite seam gap of the front fairing and the middle fairing at the front partition plate and the opposite seam gap of the middle fairing and the rear fairing at the rear partition plate reach preset gaps. And the mounting efficiency and reliability of the large-size half-enveloping structure composite fairing are improved.

Description

Technical Field

[0001] This application relates to the field of aircraft assembly, and in particular to a method for installing a large-size semi-enclosed composite fairing. Background Technology

[0002] In the assembly of aircraft fuselage structures, the fairing structure is generally located in areas with complex aerodynamic shapes and significant curvature changes. The precise installation of the fairing affects the accuracy of the aircraft's aerodynamic shape manufacturing and the reliability of its connection to the fuselage, thus impacting the aircraft's overall quality. To achieve aerodynamic rectification during flight and reduce aircraft weight, the external fairing structure often has a large geometric dimension. Given the advantages of composite materials, such as light weight and corrosion resistance, large-size segmented semi-enclosed composite fairings are becoming a major trend for future large aircraft applications. However, large-size segmented semi-enclosed composite fairings suffer from drawbacks such as weak rigidity and obstructed installation pathways, making it difficult to guarantee the accuracy of the fairing's installation on the aircraft. Summary of the Invention

[0003] In view of this, this application provides a method for installing a large-size semi-enclosed composite fairing, which solves the problems in the prior art and improves the installation efficiency and reliability of the large-size semi-enclosed composite fairing.

[0004] The technical solution for installing a large-size semi-enclosed composite fairing provided in this application is as follows: A method for installing a large-size semi-enclosed composite fairing includes the following steps: The front and rear bulkheads of the center fairing are connected to the fuselage and positioned on the fuselage to determine the positioning reference of the center fairing on the fuselage. Position and connect the front and rear bulkheads and connectors on the center fairing to complete the installation of the center fairing; The middle fairing is used as the main reference for positioning the front and rear fairings on the fuselage, and the installation of the front and rear fairings is carried out. Using the shape and seam gap of the front and rear bulkheads of the center fairing as the positioning reference for the front and rear fairings, the positions of the front and rear fairings in the heading direction are adjusted so that the seam gap between the front and center fairings at the front bulkhead and the seam gap between the center and rear fairings at the rear bulkhead reach the preset gap. With the fuselage, front fairing, and rear fairing on the same coordinate system, mark the positions where the fuselage meets the front fairing, the fuselage meets the rear fairing, the front fairing meets the fuselage, and the rear fairing meets the fuselage. The mark lines where the fuselage meets the front fairing and the front fairing meets the fuselage are on the first straight line, and the mark lines where the fuselage meets the rear fairing and the rear fairing meets the fuselage are on the second straight line. The first and second straight lines are parallel to the horizontal plane of the aircraft structure. Using the marking lines on the outer surface of the fuselage as an auxiliary positioning reference, the overlap of the marking lines on the front fairing and the rear fairing with the marking lines on the fuselage is adjusted to achieve accurate positioning of the front fairing and the rear fairing in the vertical direction of the fuselage.

[0005] Optionally, the marking line at the junction of the front fairing and the fuselage is located at the leading edge of the front fairing and at the intersection of the fairing and the fuselage, and the marking line at the junction of the front fairing and the fuselage is located at the maximum profile of the heading.

[0006] Optionally, the marking line at the junction of the aft fairing and the fuselage is located at the rear end of the aft fairing in the heading direction and at the intersection line between the fairing and the fuselage, and the marking line at the junction of the aft fairing and the fuselage is located at the maximum outline in the heading direction.

[0007] Optionally, during the installation of the center fairing, front fairing, and rear fairing, the center fairing, front fairing, and rear fairing are respectively installed on a fairing installation vehicle, and the position and attitude of the center fairing, front fairing, and rear fairing are adjusted by the fairing installation vehicle.

[0008] Optionally, during the installation of the fairing, conformal frames are installed on the exterior of the fairing, front fairing, and rear fairing respectively, and the fairing is installed on the fairing installation vehicle via the conformal frames.

[0009] Optionally, the installation method also includes checking the fit between the L-shaped side strips around the middle fairing, front fairing and rear fairing and the outer surface of the fuselage, and adjusting the overlap between the L-shaped side strips and the end face of the composite fairing to reduce the assembly stress during the connection process.

[0010] In summary, this application includes the following beneficial technical effects: This application, through the sequential selection of positioning benchmarks, particularly the design of the fairing conformal frame and installation vehicle, securely integrates the fairing and its conformal frame, achieving a reasonable distribution of the accumulated positioning errors of each fairing section and its design compensation. This enables the precise installation of large-size segmented semi-enclosed composite fairings. This method offers high installation accuracy, good coordination, low assembly stress, and high installation reliability, effectively improving installation efficiency. Attached Figure Description

[0011] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 This is a schematic diagram illustrating the installation principle of a large-size semi-enclosed composite fairing.

[0013] Explanation of reference numerals in the attached drawings: 1. Front fairing; 2. Middle fairing; 3. Rear fairing; 4. Front bulkhead; 5. Rear bulkhead; 6. Connecting piece; 7. L-shaped side strip; 8. Marking line at the junction of the front fairing and the fuselage; 9. Marking line at the junction of the rear fairing and the fuselage. Detailed Implementation

[0014] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0015] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0016] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0017] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The illustrations only show the components related to this application and are not drawn according to the number, shape and size of the components in actual implementation. In actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0018] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0019] This application provides a method for installing a large-size semi-enclosed composite fairing.

[0020] like Figure 1 As shown, a method for installing a large-size semi-enclosed composite fairing includes the following steps: The front bulkhead 4 and rear bulkhead 5 of the fairing 2 are positioned and installed on the fuselage as the connecting parts 6 to determine the positioning reference of the fairing 2 on the fuselage. During the installation of the connecting parts 6, 2-3 assembly holes are made on the connecting parts 6, and tooling positioners are set according to the above-mentioned assembly hole positions in the final assembly state of the fuselage components to achieve accurate positioning of the connecting parts 6 and the fuselage, which serves as the initial reference for fairing installation.

[0021] Position and connect the front bulkhead 4, rear bulkhead 5, and connector 6 of the center fairing 2 to complete the installation of the center fairing 2. During the installation of the center fairing 2, connect the front bulkhead 4, rear bulkhead 5, and peripheral L-shaped side strips 7 of the center fairing 2 to the fuselage, and then remove the fairing installation vehicle.

[0022] Using the middle fairing 2 as the main reference for positioning the front fairing 1 and the rear fairing 3 on the fuselage, the installation operations of the front fairing 1 and the rear fairing 3 are carried out. Using the shape and seam gap of the front bulkhead 4 and rear bulkhead 5 of the center fairing 2 as the positioning reference for the front fairing 1 and rear fairing 3, the positions of the front fairing 1 and rear fairing 3 in the heading direction are adjusted so that the seam gap between the front fairing 1 and the center fairing 2 at the front bulkhead 4, and the seam gap between the center fairing 2 and the rear fairing 3 at the rear bulkhead 5, reach the preset gaps. This reduces the positioning error in the heading direction of the coordinated points of the front fairing 1, rear fairing 3, and center fairing 2.

[0023] With the fuselage, front fairing 1, and rear fairing 3 positioned on the same coordinate system, marking lines are drawn at the locations where the fuselage meets the front fairing 1, the fuselage meets the rear fairing 3, the front fairing 1 meets the fuselage, and the rear fairing 3 meets the fuselage. The marking line 8 at the location where the fuselage meets the front fairing 1 and the front fairing meets the fuselage are on a first straight line, and the marking line 9 at the location where the fuselage meets the rear fairing 3 and the rear fairing meets the fuselage are on a second straight line. The first and second straight lines are parallel to the horizontal plane of the aircraft structure. Using the marking lines on the outer surface of the fuselage as auxiliary positioning references, the overlap between the marking lines on the front fairing 1 and the rear fairing 3 and the marking lines on the fuselage is adjusted to achieve accurate positioning of the front fairing 1 and the rear fairing 3 in the vertical direction of the fuselage.

[0024] In this embodiment, the marking line 8 at the junction of the front fairing and the fuselage is located at the forward leading edge of the front fairing 1 and at the intersection line between the fairing and the fuselage, and at the maximum directional profile. The marking line 9 at the junction of the rear fairing and the fuselage is located at the rear leading edge of the rear fairing 3 and at the intersection line between the fairing and the fuselage, and at the maximum directional profile.

[0025] During the installation of the middle fairing 2, the front fairing 1, and the rear fairing 3, the middle fairing 2, the front fairing 1, and the rear fairing 3 are respectively installed on the fairing installation vehicle, and the position and attitude of the middle fairing 2, the front fairing 1, and the rear fairing 3 are adjusted by the fairing installation vehicle.

[0026] During the installation of the center fairing 2, conformal frames are installed on the exterior of the center fairing 2, the front fairing 1, and the rear fairing 3. These conformal frames are then mounted on the fairing installation vehicle, improving the structural rigidity of the center fairing 2, the front fairing 1, and the rear fairing 3. Specifically, 2-3 assembly holes coordinated with the connector 6 are provided on the inner side partition of the center fairing 2, and 2-3 shape-adjustable plates are provided on the outer side, forming a unified external conformal frame for the center fairing 2. This ensures that the design compensation of the L-shaped edge strip 7 around the center fairing 2 meets the shape deviation requirements.

[0027] The installation method also includes checking the fit of the L-shaped side strips 7 around the middle fairing 2, front fairing 1 and rear fairing 3 with the outer surface of the fuselage, and adjusting the overlap between the L-shaped side strips 7 and the end face of the composite fairing to reduce the assembly stress during the connection process and improve the reliability of the connection.

[0028] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for installing a large-size semi-enclosed composite fairing, characterized in that, Includes the following steps: The front bulkhead (4) and rear bulkhead (5) of the center fairing (2) are connected to the fuselage and the connecting parts (6) are positioned and installed on the fuselage to determine the positioning reference of the center fairing (2) on the fuselage. Position and connect the front baffle (4), rear baffle (5) and connector (6) on the fairing (2) to complete the installation of the fairing (2); Using the middle fairing (2) as the main reference for positioning the front fairing (1) and the rear fairing (3) on the fuselage, the installation operation of the front fairing (1) and the rear fairing (3) is carried out. Using the shape and seam gap of the front bulkhead (4) and rear bulkhead (5) of the middle fairing (2) as the positioning reference of the front fairing (1) and rear fairing (3), adjust the position of the front fairing (1) and rear fairing (3) in the heading direction so that the seam gap of the front fairing (1) and the middle fairing (2) at the front bulkhead (4) and the seam gap of the middle fairing (2) and the rear fairing (3) at the rear bulkhead (5) reach the preset gap; Place the fuselage, front fairing (1), and rear fairing (3) on the same coordinate system. Mark the positions where the fuselage meets the front fairing (1), the fuselage meets the rear fairing (3), the front fairing (1) meets the fuselage, and the rear fairing (3) meets the fuselage. Mark the positions where the fuselage meets the front fairing (1) and the front fairing meets the fuselage (8) on the first straight line. Mark the positions where the fuselage meets the rear fairing (3) and the rear fairing meets the fuselage (9) on the second straight line. The first and second straight lines are parallel to the horizontal plane of the aircraft structure. Using the marking lines on the outer surface of the fuselage as an auxiliary positioning reference, the overlap of the marking lines on the front fairing (1) and the rear fairing (3) with the marking lines on the fuselage is adjusted to achieve accurate positioning of the front fairing (1) and the rear fairing (3) in the vertical direction of the fuselage.

2. The method for installing a large-size semi-enclosed composite fairing according to claim 1, characterized in that, The marking line (8) at the junction of the front fairing and the fuselage is located at the front of the heading of the front fairing (1) and at the intersection of the fairing and the fuselage. The marking line (8) at the junction of the front fairing and the fuselage is located at the maximum heading.

3. The method for installing a large-size semi-enclosed composite fairing according to claim 1, characterized in that, The marking line (9) at the junction of the rear fairing and the fuselage is located at the rear end of the rear fairing (3) in the heading direction and at the intersection of the fairing and the fuselage. The marking line (9) at the junction of the rear fairing and the fuselage is located at the maximum outline in the heading direction.

4. The method for installing a large-size semi-enclosed composite fairing according to claim 1, characterized in that, During the installation of the middle fairing (2), the front fairing (1), and the rear fairing (3), the middle fairing (2), the front fairing (1), and the rear fairing (3) are respectively installed on the fairing installation vehicle, and the positions of the middle fairing (2), the front fairing (1), and the rear fairing (3) are adjusted by the fairing installation vehicle.

5. The method for installing a large-size semi-enclosed composite fairing according to claim 1, characterized in that, During the installation of the middle fairing (2), conformal frames are set on the outside of the middle fairing (2), the front fairing (1), and the rear fairing (3), respectively. The middle fairing (2), the front fairing (1), and the rear fairing (3) are installed on the fairing installation vehicle through the conformal frames.

6. The method for installing a large-size semi-enclosed composite fairing according to claim 1, characterized in that, The installation method also includes checking the fit of the L-shaped side strips (7) around the middle fairing (2), front fairing (1) and rear fairing (3) with the outer surface of the fuselage, and adjusting the overlap between the L-shaped side strips (7) and the end face of the composite fairing to reduce the assembly stress during the connection process.

Images