A method of assembling an aircraft fuselage

Abstract

The application belongs to the technical field of aircraft assembly design, and particularly relates to an aircraft fuselage assembly method, which realizes the arrangement of corresponding measurement stations, measurement reference points and object measurement points of each small wallboard, and the pre-positioning, pre-coordination, posture adjustment and secondary coordination of each small wallboard through the space outward deviation of the theoretical assembly positions of the upper, lower, left and right long strip wallboards, and can well eliminate the problem of large deformation in the assembly process of the four long strip wallboards with weak rigidity, has high assembly precision and efficiency, and can well guarantee the aerodynamic performance of the aircraft fuselage assembly.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft assembly design, and particularly relates to an aircraft fuselage assembly method. BACKGROUND

[0002] At present, when an aircraft is assembled, the fuselage is usually divided into three segments, i.e., a front segment, a middle segment and a rear segment, for component assembly, and then the three segments are connected to obtain a complete fuselage large component. This fuselage assembly method is beneficial to balanced allocation of production resources and uniform production capacity, but has poor integration of the front, middle and rear segments, and has extremely high requirements for precision control, and accumulates two levels of assembly errors of component level and large component level for positioning of the whole fuselage horizontal measurement point, so it is difficult to guarantee the precision of fuselage assembly based on the current technical level, resulting in poor fuselage shape coordination and difficulty in guaranteeing the aerodynamic performance of the aircraft fuselage. This problem is particularly prominent for the assembly of large-size aircraft fuselages of more than 50 m.

[0003] In order to guarantee the aerodynamic performance of the aircraft fuselage assembly, some technical solutions change the three-segment assembly of the front, middle and rear of the fuselage into the assembly of four long strip-shaped panels, i.e., an upper long strip-shaped panel, a lower long strip-shaped panel, a left long strip-shaped panel and a right long strip-shaped panel. This fuselage assembly method has the following technical difficulties:

[0004] The long strip-shaped panel structure has a long size, and has weak rigidity, which is prone to deformation during assembly;

[0005] Each long strip-shaped panel is assembled by a plurality of small panels, and the measurement and positioning during assembly are complex and have high technical difficulty.

[0006] The present application is proposed in view of the above technical defects. SUMMARY

[0007] The purpose of the present application is to provide an aircraft fuselage assembly method to overcome or alleviate at least one aspect of the known technical defects.

[0008] The technical solution of the present application is:

[0009] An aircraft fuselage assembly method, comprising:

[0010] Step one, dividing the fuselage into an upper long strip-shaped panel, a lower long strip-shaped panel, a left long strip-shaped panel and a right long strip-shaped panel, the upper long strip-shaped panel, the lower long strip-shaped panel, the left long strip-shaped panel and the right long strip-shaped panel comprising a plurality of small panels;

[0011] Step two, offsetting each small panel by a set distance from a theoretical assembly position as a whole, and pre-positioning and pre-coordinating each small panel;

[0012] Step three, a plurality of local measurement station positions of laser trackers are arranged in the gaps between the upper long strip wallboard, the lower long strip wallboard and the left long strip wallboard and the right long strip wallboard along the machine body axis direction, and each small wallboard can be matched to a local measurement station position;

[0013] Step four, the laser beams of the laser trackers arranged at the left local measurement station positions are projected to the machine body assembly tool surface outside the right long strip wallboard through the gaps between the upper long strip wallboard, the lower long strip wallboard and the right long strip wallboard, assembly tool measurement reference points are arranged at the projection point positions, and foundation measurement reference points are arranged on the surface of the visible foundation at each left local measurement station position;

[0014] The laser beams of the laser trackers arranged at the right local measurement station positions are projected to the machine body assembly tool surface outside the left long strip wallboard through the gaps between the upper long strip wallboard, the lower long strip wallboard and the left long strip wallboard, assembly tool measurement reference points are arranged at the projection point positions, and foundation measurement reference points are arranged on the surface of the visible foundation at each right local measurement station position;

[0015] Step five, wallboard object measurement points are arranged inside each small wallboard;

[0016] Step six, the assembly tool measurement reference points and the foundation measurement reference points are calibrated based on the machine body assembly tool measurement field, and a global coordinate system is constructed;

[0017] Step seven, in the global coordinate system, each small wallboard is calibrated with the assembly tool measurement reference points and the foundation measurement reference points arranged at the corresponding local measurement station positions by the laser tracker, the local coordinate system is reconstructed, and a local coordinate system is constructed;

[0018] Step eight, in the local coordinate system, the wallboard object measurement points are measured by the laser tracker arranged at the corresponding local measurement station position, and the posture adjustment and secondary coordination are performed;

[0019] Step nine, each small wallboard of the upper long strip wallboard, the lower long strip wallboard, the left long strip wallboard and the right long strip wallboard is assembled;

[0020] Step ten, the local measurement station positions are removed, the upper long strip wallboard, the lower long strip wallboard, the left long strip wallboard and the right long strip wallboard are moved to the theoretical assembly position, and the whole machine body assembly is performed.

[0021] Optionally, in the above aircraft machine body assembly method, the set distance of the integral coordination of each small wallboard of the upper long strip wallboard and the lower long strip wallboard to the outside from the theoretical assembly position in step two is a fixed small distance;

[0022] The fixed large distance is set as a fixed distance of the whole small wallboards of the left long wallboard and the right long wallboard from the theoretical assembly position.

[0023] Optionally, in the aircraft fuselage assembly method, the fixed small distance is not less than 200 mm for the fuselage assembly exceeding 50 m in length, and the fixed small distance is not less than 50 mm for the fuselage assembly below 50 m in length.

[0024] The fixed large distance is not less than 800 mm.

[0025] Optionally, in the aircraft fuselage assembly method, the local measurement station is supported on the ground by a measurement support in the step three.

[0026] Optionally, in the aircraft fuselage assembly method, the ground measurement reference point corresponding to the left local measurement station is in the range of the projection of the gap between the lower long wallboard and the left long wallboard on the ground surface, and a laser beam from the laser tracker on the left local measurement station to the assembly tool measurement reference point is visible.

[0027] The ground measurement reference point corresponding to the right local measurement station is in the range of the projection of the gap between the lower long wallboard and the right long wallboard on the ground surface, and a laser beam from the laser tracker on the right local measurement station to the assembly tool measurement reference point is visible.

[0028] The number of small wallboards that can match the assembly tool measurement reference point is not less than two, and the number of ground measurement reference points is not less than four.

[0029] Optionally, in the aircraft fuselage assembly method, the wallboard object measurement point on each small wallboard is arranged in the assembly positioning hole, and the number of wallboard object measurement points is not less than four, and the corresponding local measurement station is visible.

[0030] Optionally, in the aircraft fuselage assembly method, the network measurement method is used to calibrate the assembly tool measurement reference point and the ground measurement reference point based on the fuselage assembly tool measurement field, and a global coordinate system is constructed.

[0031] Optionally, in the aircraft fuselage assembly method, the connection holes in the two side extension distances are not connected when the small wallboards of the upper long wallboard, the lower long wallboard, the left long wallboard and the right long wallboard are assembled in the step nine.

[0032] The extension distance is not less than 200 mm or not less than the distance between two fuselage long spars.

[0033] Optionally, in the aircraft fuselage assembly method described above, after the assembly of each small wall panel of the upper long strip wall panel, the lower long strip wall panel, the left long strip wall panel and the right long strip wall panel is completed in step nine, attitude measurement and evaluation are performed, and if the requirements cannot be met, corresponding assembly adjustment is performed.

[0034] Optionally, in the aircraft fuselage assembly method described above, after the assembly of each small wall panel of the upper long strip wall panel, the lower long strip wall panel, the left long strip wall panel and the right long strip wall panel is completed in step nine, attitude measurement and evaluation are performed, and if the requirements cannot be met, corresponding assembly adjustment is performed.

[0035] A full-aircraft measurement station position is provided at the positions of the nose window and the tail cabin door, and a laser beam of a laser tracker provided at the full-aircraft measurement station position can extend into the interior of the fuselage, and a plurality of fuselage horizontal measurement points are provided at the fuselage assembly positioning structure.

[0036] In the global coordinate system, the laser tracker provided at the full-aircraft measurement station position is used to calibrate each fuselage horizontal measurement point in a segmented regional local coordinate system of the front, middle and rear fuselage to evaluate and adjust the bending and twisting of the full-aircraft fuselage.

[0037] The present application has at least the following beneficial technical effects:

[0038] The present application provides an aircraft fuselage assembly method, which realizes the arrangement of each small wall panel, measurement reference point and object measurement point by outwardly offsetting the theoretical assembly positions of the upper, lower, left and right long strip wall panels, and realizes the pre-positioning, pre-coordination, attitude adjustment and secondary coordination of each small wall panel, thereby effectively eliminating the problem of large deformation in the assembly process of the weak rigid upper, lower, left and right long strip wall panels, and achieving high assembly precision and efficiency and good guarantee of the aerodynamic performance of the aircraft fuselage assembly. BRIEF DESCRIPTION OF DRAWINGS

[0039] Figure 1 is a schematic diagram of the aircraft fuselage assembly method provided by the embodiment of the present application;

[0040] Figure 2 is a schematic diagram of the outward offset of each small wall panel of the upper long strip wall panel, the lower long strip wall panel, the left long strip wall panel and the right long strip wall panel from the theoretical assembly position by a set distance;

[0041] Among them:

[0042] 1-upper long strip wall panel; 2-lower long strip wall panel; 3-left long strip wall panel; 4-right long strip wall panel; 5-local measurement station position; 6-measurement support; 7-ground; 8-assembly tool measurement reference point; 9-ground measurement reference point; 10-wall panel object measurement point; 11-full-aircraft measurement station position; 12-assembly tool.

[0043] For better illustrating the embodiments, some contents in the drawings are omitted, enlarged or reduced, which are only used for illustrative description and can not be understood as limitation to the present application. DETAILED DESCRIPTION

[0044] In order to make the technical solutions of the present application and the advantages thereof clearer, the technical solutions of the present application will be further clearly and completely described in the following with reference to the drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application, which are used to explain the present application but not to limit the present application. It should be noted that, in order to facilitate the description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the general design.

[0045] In addition, unless otherwise defined, the technical terms or scientific terms used in the present application description should be the general meanings understood by the general technical personnel in the field of the present application. In the present application description, "comprising" indicates that the concept appearing before the word covers the concepts listed after the word and its equivalents, and does not exclude other associated concepts.

[0046] In addition, the words expressing the position used in the present application description are only used to express the relative direction or position relationship, and when the absolute position of the described object changes, the relative position relationship may also change accordingly. It should be noted that, unless otherwise specified and limited, "mounting", "connecting" and similar words used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection or detachable connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and the person skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0047] An aircraft fuselage assembly method, as shown in Figure 1 .

[0048] Step one, divide the fuselage into upper long strip wallboard 1, lower long strip wallboard 2, left long strip wallboard 3, right long strip wallboard 4, the upper long strip wallboard 1, the lower long strip wallboard 2, the left long strip wallboard 3, the right long strip wallboard 4 include a plurality of small wallboards.

[0049] Step two, offset each small wallboard from the theoretical assembly position by a set distance, as shown in Figure 2 , pre-position and pre-coordinate each small wallboard.

[0050] Design an independent attitude positioning mechanism for each small wallboard of the upper long strip wallboard 1, the lower long strip wallboard 2, the left long strip wallboard 3 and the right long strip wallboard 4, which can specifically adopt an independent mechanical arm to perform offset operation on each small wallboard.

[0051] The fixed small distance of the set distance of the whole small wallboard of the upper long wallboard 1 and the lower long wallboard 2 from the theoretical assembly position is not less than 200 mm for the fuselage assembly of more than 50 m in length, and not less than 50 mm for the fuselage assembly of less than 50 m in length.

[0052] The fixed large distance of the set distance of the whole small wallboard of the left long wallboard 3 and the right long wallboard 4 from the theoretical assembly position is not less than 800 mm.

[0053] Step three, a plurality of local measurement station positions 5 of laser trackers are arranged in the gaps of the upper long wallboard 1, the lower long wallboard 2, the left long wallboard 3 and the right long wallboard 4 along the fuselage axis, and each small wallboard can be matched to a local measurement station position 5.

[0054] Each local measurement station position 5 is supported on the foundation 7 by a measuring support 6.

[0055] Step four, the laser beam of the laser tracker arranged on each left local measurement station position 5 passes through the gap between the upper long wallboard 1, the lower long wallboard 2 and the right long wallboard 4, and is projected onto the surface of the fuselage assembly tool 12 outside the right long wallboard 4, an assembly tool measurement reference point 8 is arranged at the projection position, and a foundation measurement reference point 9 is arranged on the surface of the foundation 7 visible to each left local measurement station position 5.

[0056] The corresponding foundation measurement reference point 9 of each left local measurement station position 5 is within the projection range of the gap between the lower long wallboard 2 and the left long wallboard 3 on the surface of the foundation 7, and the laser beam of the laser tracker arranged on the left local measurement station position 5 is visible to the assembly tool measurement reference point 8.

[0057] The laser beam of the laser tracker arranged on each right local measurement station position 5 passes through the gap between the upper long wallboard 1, the lower long wallboard 2 and the left long wallboard 3, and is projected onto the surface of the fuselage assembly tool 12 outside the left long wallboard 3, an assembly tool measurement reference point 8 is arranged at the projection position, and a foundation measurement reference point 9 is arranged on the surface of the foundation 7 visible to each right local measurement station position 5.

[0058] The corresponding foundation measurement reference point 9 of each right local measurement station position 5 is within the projection range of the gap between the lower long wallboard 2 and the right long wallboard 4 on the surface of the foundation 7, and the laser beam of the laser tracker arranged on the right local measurement station position 5 is visible to the assembly tool measurement reference point 8.

[0059] The number of each small wallboard matched to the assembly tool measurement reference point 8 is not less than two, and the number of the foundation measurement reference point 9 is not less than four.

[0060] Step five, set the wallboard object measuring point 10 on the inner side of each small wallboard.

[0061] The wallboard object measuring point 10 on each small wallboard is set in the assembly positioning hole, and the number is not less than four, and the corresponding local measuring station 5 can be seen.

[0062] Step six, based on the fuselage assembly tool measurement field, calibrate the assembly tool measurement reference point 8 and the foundation measurement reference point 9, and construct the global coordinate system.

[0063] Based on the fuselage assembly tool measurement field, the assembly tool measurement reference point 8 and the foundation measurement reference point 9 are calibrated by using the network measurement method, and then the global coordinate system is constructed.

[0064] Step seven, in the global coordinate system, the corresponding assembly tool measurement reference point 8 and the foundation measurement reference point 9 are calibrated by using the laser tracker set on the corresponding local measuring station 5, the local coordinate system is reconstructed, and the local coordinate system is constructed.

[0065] Step eight, in the local coordinate system, the wallboard object measuring point 10 is measured by using the laser tracker set on the corresponding local measuring station 5, and the posture is adjusted and the secondary coordination is performed.

[0066] Step nine, assemble each small wallboard of the upper long strip-shaped wallboard 1, the lower long strip-shaped wallboard 2, the left long strip-shaped wallboard 3 and the right long strip-shaped wallboard 4.

[0067] When assembling each small wallboard of the upper long strip-shaped wallboard 1, the lower long strip-shaped wallboard 2, the left long strip-shaped wallboard 3 and the right long strip-shaped wallboard 4, the connecting parts in the two-side expansion distance are not connected first, that is, the connecting holes in the two-side expansion distance are reserved.

[0068] The expansion distance is not less than 200mm, or not less than the distance between two fuselage long stringers. In this way, when connecting the upper long strip-shaped wallboard 1, the lower long strip-shaped wallboard 2, the left long strip-shaped wallboard 3 and the right long strip-shaped wallboard 4, the micro-adjustment can be performed through the pad filing, the smoothness of the connection between the upper long strip-shaped wallboard 1, the lower long strip-shaped wallboard 2, the left long strip-shaped wallboard 3 and the right long strip-shaped wallboard 4 is ensured, and the aerodynamic performance of the fuselage assembly is ensured.

[0069] After assembling each small wallboard of the upper long strip-shaped wallboard 1, the lower long strip-shaped wallboard 2, the left long strip-shaped wallboard 3 and the right long strip-shaped wallboard 4, the posture is measured and evaluated. If it cannot meet the requirements, the corresponding assembly adjustment is performed.

[0070] Step ten, evacuate the local measurement station 5, move the upper long strip wallboard 1, the lower long strip wallboard 2, the left long strip wallboard 3 and the right long strip wallboard 4 to the theoretical assembly position, and carry out full fuselage assembly.

[0071] The single synchronous collaborative motion function of the attitude adjustment positioning mechanism is used to move the upper long strip wallboard 1, the lower long strip wallboard 2, the left long strip wallboard 3 and the right long strip wallboard 4 to the theoretical assembly position.

[0072] After the full fuselage assembly is completed, the full fuselage bending and torsion are evaluated and adjusted, and the specific reference is as follows:

[0073] A full machine measurement station 11 of a laser tracker is arranged at the position of the nose door window and the tail cabin door, the laser beam of the laser tracker arranged at the full machine measurement station 11 can extend into the interior of the fuselage, and a plurality of fuselage horizontal measurement points are arranged at the fuselage assembly positioning structure.

[0074] The attitude adjustment positioning mechanism is evacuated, and the laser tracker arranged at the full machine measurement station 11 is used to evaluate and adjust the full fuselage bending and torsion of each fuselage horizontal measurement point in the full coordinate system, and the full machine measurement station 11 is evacuated.

[0075] The aircraft fuselage assembly method disclosed in the above embodiment can well eliminate the problem of large deformation in the assembly process of the four long strip wallboards with weak rigidity, has high assembly precision and efficiency, and can well guarantee the aerodynamic performance of the aircraft fuselage assembly.

[0076] The technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without deviating from the principles of the present application, and the technical solutions after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A method for assembling an aircraft fuselage, characterized in that, include: Step 1: Divide the fuselage into an upper long strip panel (1), a lower long strip panel (2), a left long strip panel (3), and a right long strip panel (4). The upper long strip panel (1), lower long strip panel (2), left long strip panel (3), and right long strip panel (4) include multiple small panels. Step 2: Offset each small wall panel outward by a set distance from its theoretical assembly position as a whole, and pre-position and pre-coordinate each small wall panel. Step 3: In the gap between the upper long strip wall panel (1), the lower long strip wall panel (2), the left long strip wall panel (3), and the right long strip wall panel (4), set up multiple local measurement stations (5) of laser trackers along the fuselage axis. Each small wall panel can be matched with a local measurement station (5). Step 4: The laser beams of the laser trackers set on each local measurement station (5) on the left pass through the gap between the upper long strip wall panel (1), the lower long strip wall panel (2) and the right long strip wall panel (4), and are projected onto the surface of the fuselage assembly fixture (12) outside the right long strip wall panel (4). The assembly fixture measurement reference point (8) is set at the projection point, and the foundation measurement reference point (9) is set on the surface of the visible foundation (7) of each local measurement station (5) on the left. The laser beams of the laser trackers installed on each local measurement station (5) on the right side pass through the gap between the upper long strip wall panel (1), the lower long strip wall panel (2) and the left long strip wall panel (3), and are projected onto the surface of the fuselage assembly fixture (12) outside the left long strip wall panel (3). The assembly fixture measurement reference point (8) is set at the projection point, and the foundation measurement reference point (9) is set on the surface of the visible foundation (7) of each local measurement station (5) on the right side. Step 5: Set measurement points (10) for the wall panel object on the inside of each small wall panel. Step 6: Based on the fuselage assembly tooling measurement field, calibrate the assembly tooling measurement reference point (8) and the foundation measurement reference point (9) to construct a global coordinate system; Step 7: Under the global coordinate system, for each small wall panel, use the laser tracker set on the corresponding local measurement station (5) to calibrate the corresponding assembly tooling measurement reference point (8) and foundation measurement reference point (9), perform local coordinate system reconstruction, and construct the local coordinate system; Step 8: In the local coordinate system, for each small wall panel, use the laser tracker set on the corresponding local measurement station (5) to measure the measurement point (10) of the wall panel object, and perform posture adjustment and secondary coordination. Step 9: Assemble the small panels of the upper long strip wall panel (1), lower long strip wall panel (2), left long strip wall panel (3), and right long strip wall panel (4); Step 10: Remove the local measurement station (5), move the upper long strip wall panel (1), lower long strip wall panel (2), left long strip wall panel (3), and right long strip wall panel (4) to the theoretical assembly position, and perform full fuselage assembly.

2. The aircraft fuselage assembly method according to claim 1, characterized in that, In step two, the small wall panels of the upper long strip wall panel (1) and the lower long strip wall panel (2) are offset outward from their theoretical assembly positions by a set distance, which is a fixed small distance. The set distance by which each small panel of the left long strip panel (3) and the right long strip panel (4) is offset outward from the theoretical assembly position as a whole is a fixed large distance.

3. The aircraft fuselage assembly method according to claim 2, characterized in that, In step two, for fuselage assembly exceeding 50m in length, the fixed small distance shall not be less than 200mm; for fuselage assembly less than 50m in length, the fixed small distance shall not be less than 50mm. The fixed distance should not be less than 800mm.

4. The aircraft fuselage assembly method according to claim 3, characterized in that, In step three, each local measurement station (5) is supported on the foundation (7) by measurement pillars (6).

5. The aircraft fuselage assembly method according to claim 4, characterized in that, In step four, the foundation measurement reference point (9) corresponding to each local measurement station (5) on the left is located within the range of the projection of the gap between the lower long strip wall panel (2) and the left long strip wall panel (3) on the surface of the foundation (7), and the laser beam of the laser tracker set on the local measurement station (5) on the left to the assembly tooling measurement reference point (8) can be seen. The foundation measurement reference point (9) corresponding to each local measurement station (5) on the right is located within the range of the projection of the gap between the lower long strip wall panel (2) and the right long strip wall panel (4) on the surface of the foundation (7), and the laser beam of the laser tracker set on the local measurement station (5) on the right to the assembly tool measurement reference point (8) can be seen. Each small wall panel can be matched with no less than two assembly tooling measurement reference points (8), and the number of foundation measurement reference points (9) is no less than four.

6. The aircraft fuselage assembly method according to claim 5, characterized in that, In step five, the wall panel object measurement points (10) on each small wall panel are set in the assembly positioning holes, with no less than four points, and the corresponding local measurement stations (5) are visible.

7. The aircraft fuselage assembly method according to claim 6, characterized in that, In step six, based on the fuselage assembly tooling measurement field, a network measurement method is used to calibrate the assembly tooling measurement reference point (8) and the foundation measurement reference point (9), thereby constructing a global coordinate system.

8. The aircraft fuselage assembly method according to claim 7, characterized in that, In step nine, when assembling the small wall panels of the upper long strip wall panel (1), lower long strip wall panel (2), left long strip wall panel (3), and right long strip wall panel (4), the connecting seams between the upper long strip wall panel (1), lower long strip wall panel (2), left long strip wall panel (3), and right long strip wall panel (4) should not be connected at the beginning, and connection holes should be reserved within the expansion distance on both sides. The extension distance shall be no less than 200mm, or no less than the distance between two fuselage spans.

9. The aircraft fuselage assembly method according to claim 8, characterized in that, In step nine, after assembling each of the small wall panels of the upper long strip wall panel (1), lower long strip wall panel (2), left long strip wall panel (3), and right long strip wall panel (4), the posture is measured and evaluated. If it does not meet the requirements, the assembly is adjusted accordingly.

10. The aircraft fuselage assembly method according to claim 9, characterized in that, In step ten, after the entire fuselage is assembled, the bending and twisting of the entire fuselage are evaluated and adjusted, specifically as follows: At the nose door and rear door, a full-aircraft measurement station (11) for laser tracking is set up. The laser beam of the laser tracking device at the full-aircraft measurement station (11) can extend into the fuselage. Multiple fuselage horizontal measurement points are set at the fuselage assembly and positioning structure. Under the global coordinate system, the laser tracker set on the full-aircraft measurement station (11) is used to calibrate the local coordinate system of the front, middle and rear fuselage segments for each horizontal measurement point of the fuselage, and to evaluate and adjust the bending and twisting of the entire fuselage.

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