A method of installing an outer elongate structural member of an aircraft skin

Abstract

The application discloses a method for installing an outer long and narrow structure of an aircraft skin, and relates to the technical field of mechanical assembly, which comprises the following steps: positioning two ends of the long and narrow structure outside the skin through a pilot hole to obtain an installation reference, and making a primary hole; pre-installing a first support and a second support for installing the long and narrow structure in the primary hole; installing a light long and narrow structure dummy on the first support and the second support, which has the same size characteristics as the long and narrow structure; obtaining three-dimensional coordinates of a front reference hole and a rear reference hole of the installed long and narrow structure dummy; judging whether the installation angle of the long and narrow structure dummy meets the requirements based on the three-dimensional coordinates of the front reference hole and the rear reference hole; if not, re-drilling the pilot hole and completing the aforementioned steps; if yes, making a final hole from the primary hole, completing the final installation of the first support and the second support, removing the long and narrow structure dummy, and installing the long and narrow structure. The application is beneficial to reducing manufacturing cost, time cost and labor cost.

Description

Technical Field

[0001] This application relates to the field of mechanical assembly technology, specifically to a method for installing a long and narrow structural component on the outer skin of an aircraft. Background Technology

[0002] The skin is a load-bearing component that covers the outside of the aircraft's skeleton structure. The skin surface is connected to some long and narrow structural components (such as stringers) to provide support and reinforcement.

[0003] However, in the aircraft manufacturing industry, installing long and narrow structural components on the outside of aircraft skin is quite difficult because these types of structural components have high assembly requirements, such as large weight, high rigidity, small angular tolerance, and high front-to-back coaxiality. Summary of the Invention

[0004] The main objective of this application is to provide a method for installing elongated structural components on the outer surface of aircraft skin, aiming to solve the technical problem of high installation difficulty in installing elongated structural components on the outer surface of aircraft skin.

[0005] The technical solution adopted in this application is as follows:

[0006] A method for installing a narrow, elongated structural component on the outer surface of an aircraft skin, comprising the following steps:

[0007] The mounting references for both ends of the elongated structural component outside the skin are located by using pilot holes, and initial holes are made.

[0008] The first and second supports for installing the elongated structural components are pre-installed in the initial hole;

[0009] A lightweight, elongated structural dummy with the same dimensional characteristics as the elongated structural member is mounted on the first support and the second support;

[0010] Obtain the three-dimensional coordinates of the front and rear reference holes of the elongated structural dummy after installation;

[0011] Based on the three-dimensional coordinates of the front reference hole and the rear reference hole, determine whether the installation angle of the elongated structural component dummy meets the requirements;

[0012] If not, then drill a new hole and complete the aforementioned steps;

[0013] If so, the initial hole is made into a final hole to complete the final installation of the first support and the second support, and the dummy elongated structural component is removed and installed on the first support and the second support.

[0014] Optionally, the step of positioning the mounting references of both ends of the elongated structural member outside the skin through the pilot holes and making the initial holes includes the following steps:

[0015] Install the first drilling tool on the inner machining frame of the aircraft skin, and install the second drilling tool on the inner machining frame of the aircraft.

[0016] The first and second positioning guide holes are drawn onto the aircraft skin using the first and second drilling tools.

[0017] A first fitting tool is installed on the outside of the aircraft skin through the first positioning guide hole, and a second fitting tool is installed on the outside of the aircraft skin through the second positioning guide hole.

[0018] Initial holes are made on the aircraft skin from the outside to the inside using the first and second hole-making tools.

[0019] Optionally, the first drilling tool is connected to the process hole on the inner side of the aircraft skin machining frame via a connector, and the second drilling tool is positioned and installed based on the shape of the inner side of the aircraft machining frame. Both the first drilling tool and the second drilling tool are provided with guide holes for drilling into the skin.

[0020] Optionally, the connector may include a pin or a bolt.

[0021] Optionally, the first and second hole-making tools each have matching drill holes for positioning the mounting holes of the first and second supports on the skin.

[0022] Optionally, the first and second hole-fitting tools are connected to the corresponding positioning guide holes by means of pins or bolts.

[0023] Optionally, obtaining the three-dimensional coordinates of the front and rear reference holes of the elongated structural dummy after installation includes the following steps:

[0024] Transform the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structural component;

[0025] A rake ball mounting hole is provided at the center of the front and rear sides of the dummy part of the narrow structure, and the rake ball is placed in the rake ball mounting hole;

[0026] The three-dimensional coordinates of the rake ball at the front and rear center of the dummy part of the narrow structure were obtained using a laser tracker.

[0027] Optionally, the step of transforming the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structural component includes the following steps:

[0028] The coordinates of at least three reference points on the outer surface of the aircraft that are not in the same plane are measured using a target ball, or the coordinates of at least three reference points of the aircraft coordinate system on the assembly platform on which the aircraft is located are measured using a target ball. The coordinate system is then established by software using a sphere determined by three points in space.

[0029] Optionally, based on the three-dimensional coordinates of the front and rear reference holes, it is determined whether the installation angle of the elongated structural dummy meets the requirements, including the following steps:

[0030] Based on the three-dimensional coordinates of the front and rear reference holes, the slopes of the elongated structural dummy component in the vertical and horizontal directions are obtained. and ;

[0031] Determine the slope Does it meet the requirements? , Does it meet the requirements? ,in, The downward deviation of the elongated structural component relative to the vertical direction of the aircraft; This refers to the upward deviation of the elongated structural component relative to the vertical direction of the aircraft. The downward deviation of the elongated structural component relative to the left and right directions of the aircraft; This refers to the upper deviation of the elongated structural component relative to the left and right angles of the aircraft.

[0032] Optionally, let the three-dimensional coordinates of the front reference hole be ( The three-dimensional coordinates of the rear reference hole are ( The slope = The slope = .

[0033] Compared with the prior art, the beneficial effects of this application are:

[0034] This application proposes a method for installing a long, narrow structural component on the outer surface of an aircraft skin, comprising the following steps: positioning the mounting references of both ends of the long, narrow structural component outside the skin using pilot holes, and creating initial holes; pre-installing a first and second support for mounting the long, narrow structural component into the initial holes; installing a lightweight, long, narrow structural component dummy with the same dimensional characteristics as the long, narrow structural component onto the first and second supports; obtaining the three-dimensional coordinates of the front and rear reference holes of the installed long, narrow structural component dummy; determining whether the installation angle of the long, narrow structural component dummy meets the requirements based on the three-dimensional coordinates of the front and rear reference holes; if not, re-piloting and completing the aforementioned steps; if yes, making the initial holes into final holes, completing the final installation of the first and second supports, removing the long, narrow structural component dummy, and installing the long, narrow structural component onto the first and second supports. In this technical solution, the installation reference of the elongated structural component is determined by using a pre-drilling method. The installation of the elongated structural component is confirmed by pre-installing a lightweight dummy component to ensure that the installation meets the requirements. This improves the angular accuracy and coaxiality of the elongated structural component after installation, effectively ensuring the assembly quality of the product. The lightweight dummy component is easy and convenient to hoist, which facilitates the installation work when repeated reinstallation is required due to non-compliance with the installation reference. This helps to reduce manufacturing costs, time costs, and labor costs. The entire installation method provides technical support for the standardized installation of elongated structural components on the outside of aircraft. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the installation of the long and narrow structural component outside the skin;

[0036] Figure 2 A schematic diagram of the installation of a dummy component for the elongated outer frame structure of the skin;

[0037] Figure 3 A schematic diagram showing the state of the first pre-hole tool on the machining frame inside the aircraft skin;

[0038] Figure 4 A schematic diagram showing the initial hole preparation state of the first hole-making tool on the outer side of the skin;

[0039] Figure 5 A schematic diagram showing the state of the first support pre-installed in the initial hole;

[0040] Figure 6 A schematic diagram showing the state of the second drilling tool on the machining frame inside the aircraft.

[0041] Figure 7 This is a schematic diagram showing the initial hole preparation state of the second hole-making tool on the outside of the skin;

[0042] Figure 8 A schematic diagram showing the state of the second support pre-installed in the initial hole;

[0043] Figure 9 This is a schematic flowchart illustrating an installation method for an elongated external structural component of an aircraft skin, as provided in an embodiment of this application.

[0044] Explanation of the labels in the attached drawings:

[0045] 1-Elongated structural dummy, 2-Aircraft skin, 3-First support, 4-Second support, 5-Elongated structural component, 6-First pre-drilling tool, 7-Inner machined frame of aircraft skin, 8-First pin, 9-Second pin, 10-First hole fitting component A, 11-First hole fitting component B, 12-Inner machined frame of aircraft, 13-Second pre-drilling tool, 14-Third pin, 15-Second hole fitting tool, 16-Front reference hole, 17-Rear reference hole. Detailed Implementation

[0046] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. Based on the embodiments of this application, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of this application.

[0047] It should be noted that all directional indicators (such as up, down, left, right, front, back, etc.) in the embodiments of this application are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indicator will also change accordingly.

[0048] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0049] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0050] See attached document Figure 9 As shown in the figure, this application embodiment provides a method for installing a long and narrow structural member on the outer surface of an aircraft skin, including the following steps:

[0051] S1: Locate the mounting references for both ends of the elongated structural component outside the skin using the pilot holes, and create the initial holes;

[0052] S2: The first and second supports for installing the elongated structural components are pre-installed in the initial hole;

[0053] S3: Install a lightweight, elongated structural dummy with the same dimensional characteristics as the elongated structural member onto the first support and the second support;

[0054] S4: Obtain the three-dimensional coordinates of the front and rear reference holes of the elongated structural dummy after installation;

[0055] S5: Based on the three-dimensional coordinates of the front reference hole and the rear reference hole, determine whether the installation angle of the dummy elongated structural component meets the requirements;

[0056] If not, then drill a new hole and complete the aforementioned steps;

[0057] If so, the initial hole is made into a final hole to complete the final installation of the first support and the second support, and the dummy elongated structural component is removed and installed on the first support and the second support.

[0058] like Figure 1 As shown, some long and narrow structural components are usually installed on the outside of the aircraft skin. Currently, the installation method of long and narrow structural components on the outside of the aircraft skin is mainly carried out by drawing lines by hand. When positioning, the connector on the aircraft skin is used as a reference point for drawing lines. Then, positioning guide holes are made according to the position of the drawn lines, and the long and narrow structural components are installed.

[0059] Therefore, the problems that urgently need to be solved include the following:

[0060] First: The position requirements for the connectors that need to be referenced on the aircraft skin are very high. It is usually necessary to find multiple reference points and repeatedly check the dimensions after drawing the lines, which is time-consuming.

[0061] Second: The accuracy of manually drawn lines has a certain margin of error, resulting in poor final positioning accuracy;

[0062] Third: It is difficult to guarantee the angle and coaxiality requirements of the long and narrow outer structural parts after the skin is installed by manually drawing lines for positioning and installation. This can easily lead to rework or even scrapped parts, increasing time and manufacturing costs.

[0063] Based on the above implementation method, the installation reference of the elongated structural component is determined by using a pre-drilling method. Compared with manual drawing, this method can more accurately locate the installation positions of the first and second supports, improving the angular accuracy and front-to-back coaxiality of the elongated structural component after installation, effectively ensuring the assembly quality of the product. At the same time, the installation of the elongated structural component is confirmed by pre-installing a lightweight dummy component to determine whether the installation meets the requirements. Since the lightweight dummy component is easy and convenient to hoist, it facilitates the installation work when repeated reinstallation is required if the installation reference is not met. This helps to reduce manufacturing costs, time costs, and labor costs. The entire installation method provides technical support for the standardized installation of elongated structural components on the outside of aircraft.

[0064] To further illustrate the installation method of an elongated outer structure component for aircraft skin provided in this application embodiment, the above steps are described in detail.

[0065] The specific implementation process for steps S1-S3 is as follows:

[0066] like Figures 3 to 5As shown, the first drilling tool 6, which has a drilling function, is passed through the process hole on the inner machining frame 7 of the aircraft skin via the first pin 8. The first drilling tool 6 is temporarily fixed to the inner machining frame 7 of the aircraft skin. The drilling guide hole on the first drilling tool 6 is used to drill a hole into the aircraft skin 2 to create the first positioning guide hole. Then, the first drilling tool 6 is removed, and the second pin 9 is passed through the first positioning guide hole created by the first drilling tool 6 to fix the first drilling tool with the drilling function to the outer side of the aircraft skin 2. On the side, the first hole-fitting tool has a matching drill hole for positioning the first support 3 in the aircraft skin 2. The first hole-fitting tool includes two parts, namely the first hole-fitting component A10 and the first hole-fitting component B11. After the first hole-fitting tool is fixed to the outside of the aircraft skin 2 by the second pin 9, the matching drill hole is used to make the initial hole required to fix the first support 3 from the outside of the aircraft skin 2 to the inside. Then the first hole-fitting tool is removed, and the first support 3 is temporarily fixed to the outside of the aircraft skin by the second pin 9.

[0067] like Figures 6 to 8 As shown, the second drilling tool 13 with drilling function is positioned and installed according to the shape of the inner machining frame 12 of the aircraft skin. The second drilling tool 13 is temporarily fixed to the inner machining frame 12 of the aircraft skin, and the drilling guide hole on the second drilling tool 13 is used to drill a hole in the aircraft skin 2 to make a second positioning guide hole. Then the second drilling tool 13 is removed, and the third pin 14 is used to pass through the second positioning guide hole made by the second drilling tool 13 to fix the second drilling tool 15 with drilling function on the outer side of the aircraft skin 2. The second drilling tool 15 has a drilling hole for positioning the second support 4 in the aircraft skin 2. After the second drilling tool 15 is fixed to the outer side of the aircraft skin 2 by the third pin 14, the drilling hole is used to make the initial hole required to fix the second support 4 from the outer side of the aircraft skin 2 to the inner side. Then the second drilling tool 15 is removed, and the second support 4 is temporarily fixed to the outer side of the aircraft skin 2 by the pin 9.

[0068] like Figure 2 As shown, after the first support 3 and the second support 4 are temporarily fixed to the outside of the aircraft skin by the pins, the long and narrow structural dummy 1 is installed on the first support 3 and the second support 4 using a hoist.

[0069] In the above-described embodiment of pre-drilling and installing the first and second supports, it is understood that positioning holes for fixing the first and second supports need to be made on the aircraft skin. However, the current method of determining the position of the positioning holes is by drawing lines, which has a large error. Therefore, in this embodiment, the existing process holes on the machining frame are used as a reference to locate the position of the pre-drilling tool and drill holes on the skin surface to form positioning guide holes. The positioning guide holes are used to fix the matching tool with the same process mounting holes as the supports. The process mounting holes of the matching tool are used to drill holes on the aircraft skin surface. The pre-drilled holes are consistent with the mounting holes on the supports, which can complete the positioning and installation of the supports. This method is more accurate than drawing lines to make holes.

[0070] For clarification, "machined frame" refers to a frame structure manufactured through mechanical processing methods.

[0071] The specific implementation process for step S4 is as follows:

[0072] S41: Transform the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structural component;

[0073] S42: Provide rake ball mounting holes at the center of the front and rear sides of the dummy part of the elongated structure, and place the rake ball in the rake ball mounting holes, wherein the diameter of the rake ball mounting holes is required to be smaller than the diameter of the rake ball;

[0074] S43: Obtain the three-dimensional coordinates of the rake ball at the front and rear center of the dummy part of the narrow structure using a laser tracker.

[0075] In this embodiment, the front reference hole of the elongated structural component dummy refers to the center hole of the elongated structural component dummy located on one side end face of the first support, and the rear reference hole of the elongated structural component dummy refers to the center hole of the elongated structural component dummy located on one side end face of the second support.

[0076] In this embodiment, obtaining the three-dimensional coordinates of a reference point on a part using a laser tracker is common practice in the industry, offering fast and accurate coordinate value acquisition. Of course, transforming the measurement coordinate system of the laser tracker to the reference coordinate system of the measured part typically employs the well-known 3-2-1 method. After obtaining the relevant reference, the coordinate system transformation is performed using the laser tracker's built-in software, which includes the following steps:

[0077] Transforming the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structural component includes the following steps:

[0078] The coordinates of at least three reference points on the outer surface of the aircraft that are not in the same plane are measured using a target ball, or the coordinates of at least three reference points of the aircraft coordinate system on the assembly platform on which the aircraft is located are measured using a target ball. The coordinates are then established by software using a sphere determined by three points in space.

[0079] Finally, the specific implementation process of step S5 is as follows:

[0080] S51: The three-dimensional coordinates of the front reference hole 16 obtained by the laser tracker are ( The three-dimensional coordinates of the rear reference hole 17 are ( After that, based on the three-dimensional coordinates of the front reference hole 16 and the rear reference hole 17, the slopes of the elongated structural component dummy 1 in the vertical and horizontal directions are obtained. and The slope = slope = ;

[0081] S52: Determining the slope Does it meet the requirements? , Does it meet the requirements? ,in, The downward deviation of the elongated structural component relative to the vertical direction of the aircraft; This refers to the upward deviation of the elongated structural component relative to the vertical direction of the aircraft. The downward deviation of the elongated structural component relative to the left and right directions of the aircraft; This refers to the upper deviation of the elongated structural component relative to the left and right angles of the aircraft.

[0082] Mechanical drilling typically achieves high precision, so this method can usually meet installation requirements in one go, effectively improving installation efficiency and reducing labor costs.

[0083] In summary, the method for installing a narrow, elongated structural component on the outer surface of an aircraft skin provided in this application includes the following steps:

[0084] S1: Locate the mounting references for both ends of the elongated structural component outside the skin using the pilot holes, and create the initial holes;

[0085] S2: The first and second supports for installing the elongated structural components are pre-installed in the initial hole;

[0086] S3: Install a lightweight, elongated structural dummy with the same dimensional characteristics as the elongated structural member onto the first support and the second support;

[0087] S4: Obtain the three-dimensional coordinates of the front and rear reference holes of the elongated structural dummy after installation;

[0088] S5: Based on the three-dimensional coordinates of the front reference hole and the rear reference hole, determine whether the installation angle of the dummy elongated structural component meets the requirements;

[0089] If not, then drill a new hole and complete the aforementioned steps;

[0090] If so, the initial hole is made into a final hole to complete the final installation of the first support and the second support, and the dummy elongated structural component is removed and installed on the first support and the second support.

[0091] In this technical solution, the installation reference for the elongated structural component is determined by using a pre-drilling method. Compared with manual drawing, this method can more accurately locate the installation positions of the first and second supports, improving the angular accuracy and coaxiality of the elongated structural component after installation and effectively ensuring the assembly quality of the product. At the same time, the installation of the elongated structural component is confirmed by pre-installing a lightweight dummy component to determine whether the installation meets the requirements. Since the lightweight dummy component is easy and convenient to hoist, it facilitates the installation work when repeated reinstallation is required if the installation reference is not met. This helps to reduce manufacturing costs, time costs, and labor costs. The entire installation method provides technical support for the standardized installation of elongated structural components on the outside of aircraft.

[0092] The above description is only a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A method for installing a long and narrow structural component on the outer surface of an aircraft skin, characterized in that, Including the following steps: The mounting references for both ends of the elongated structural component outside the skin are located by using pilot holes, and initial holes are made. The first and second supports for installing the elongated structural components are pre-installed in the initial hole; A lightweight, elongated structural dummy with the same dimensional characteristics as the elongated structural member is mounted on the first support and the second support; Obtain the three-dimensional coordinates of the front reference hole and the rear reference hole of the elongated structural dummy after installation; wherein the front reference hole is at the exact center of the front side of the dummy, and the rear reference hole is at the exact center of the rear side of the dummy; Based on the three-dimensional coordinates of the front reference hole and the rear reference hole, determine whether the installation angle of the elongated structural component dummy meets the requirements; If not, then drill a new hole and complete the aforementioned steps; If so, the initial hole is made into a final hole to complete the final installation of the first support and the second support, and the dummy elongated structural component is removed and installed on the first support and the second support.

2. The method for installing the elongated outer structural component of the aircraft skin according to claim 1, characterized in that, The process of positioning the mounting references for both ends of the elongated structural member outside the skin through pilot holes and creating initial holes includes the following steps: Install the first drilling tool on the inner machining frame of the aircraft skin, and install the second drilling tool on the inner machining frame of the aircraft. The first and second positioning guide holes are drawn onto the aircraft skin using the first and second drilling tools. A first fitting tool is installed on the outside of the aircraft skin through the first positioning guide hole, and a second fitting tool is installed on the outside of the aircraft skin through the second positioning guide hole. Initial holes are made on the aircraft skin from the outside to the inside using the first and second hole-making tools.

3. The method for installing the elongated outer structural component of the aircraft skin according to claim 2, characterized in that, The first drilling tool is connected to the process hole on the inner side of the aircraft skin machining frame via a connector. The second drilling tool is positioned and installed based on the shape of the inner side of the aircraft machining frame. Both the first drilling tool and the second drilling tool are provided with guide holes for drilling into the skin.

4. The method for installing the elongated outer structural component of the aircraft skin according to claim 3, characterized in that, The connector includes a pin or a bolt.

5. The method for installing the elongated outer structural component of the aircraft skin according to claim 2, characterized in that, The first and second hole-making tools each have matching drill holes for positioning the mounting positions of the first and second supports on the skin.

6. The method for installing the elongated outer structural component of the aircraft skin according to claim 2, characterized in that, The first and second hole-fitting tools are connected to the corresponding positioning guide holes by pins or bolts.

7. The method for installing the elongated outer structural component of the aircraft skin according to claim 1, characterized in that, The process of obtaining the three-dimensional coordinates of the front and rear reference holes of the elongated structural dummy after installation includes the following steps: Transform the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structural component; A rake ball mounting hole is provided at the center of the front and rear sides of the dummy part of the narrow structure, and the rake ball is placed in the rake ball mounting hole; The three-dimensional coordinates of the rake ball at the front and rear center of the dummy part of the narrow structure were obtained using a laser tracker.

8. The method for installing the elongated outer structural component of the aircraft skin according to claim 7, characterized in that, The step of transforming the measurement coordinate system of the laser tracker to the reference coordinate system of the dummy elongated structure includes the following steps: The coordinates of at least three reference points on the outer surface of the aircraft that are not in the same plane are measured using a target ball, or the coordinates of at least three reference points of the aircraft coordinate system on the assembly platform on which the aircraft is located are measured using a target ball. The coordinate system is then established by software using a sphere determined by three points in space.

9. The method for installing the elongated outer structural component of the aircraft skin according to claim 1, characterized in that, Based on the three-dimensional coordinates of the front and rear reference holes, determine whether the installation angle of the elongated structural dummy meets the requirements, including the following steps: Based on the three-dimensional coordinates of the front and rear reference holes, the slopes of the elongated structural dummy component in the vertical and horizontal directions are obtained. and ; Determine the slope Does it meet the requirements? , Does it meet the requirements? ,in, The downward deviation of the elongated structural component relative to the vertical direction of the aircraft; This refers to the upward deviation of the elongated structural component relative to the vertical direction of the aircraft. The downward deviation of the elongated structural component relative to the left and right directions of the aircraft; This refers to the upper deviation of the elongated structural component relative to the left and right angles of the aircraft.

10. The method for installing the elongated outer structural component of the aircraft skin according to claim 8, characterized in that, Let the three-dimensional coordinates of the front reference hole be ( The three-dimensional coordinates of the rear reference hole are ( The slope = The slope = .

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