Aircraft fuselage assembling device and aircraft fuselage assembling method

Abstract

The aircraft fuselage assembling device and the aircraft fuselage assembling method are used for assembling an aircraft, and the aircraft comprises a front-section fuselage framework, a tail-section fuselage framework, a first skin and a second skin; the aircraft fuselage assembling device comprises a workbench; the at least two pairs of movable shape clamping plate mechanisms are provided with working positions and retreating positions, when the movable shape clamping plate mechanisms are located at the working positions, the movable shape clamping plate mechanisms are used for positioning all fuselage frames of the front-section fuselage framework or used for positioning and pressing the installed first skin and / or second skin, and when the movable shape clamping plate mechanisms are located at the retreating positions, the movable shape clamping plate mechanisms are used for positioning and pressing the installed first skin and / or second skin. The assembly platform is used for avoiding assembly of the first skin or the second skin; the detachable eccentric fuselage frame fixing frame is used for fixing the tail-section fuselage skeleton and avoiding one of the first skin and the second skin, and after the eccentric fuselage frame fixing frame is detached, the eccentric fuselage frame fixing frame is used for avoiding the other one of the first skin and the second skin; the suspension device is used for suspending the front-section fuselage framework; and the skin mounting precision can be ensured.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft fuselage assembly, and more particularly to an aircraft fuselage assembly device and an aircraft fuselage assembly method. Background Art

[0002] With the development of the low-altitude economy, various types of electric aircraft have been widely developed.

[0003] An aircraft includes a fuselage frame and a skin covering the fuselage frame. However, in the related art, it is not easy to ensure the installation accuracy of the skin due to its relatively large size.

[0004] Therefore, how to ensure the installation accuracy of aircraft skin is an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0005] In view of this, an object of the present invention is to provide an aircraft fuselage assembly device that can ensure the installation accuracy of the aircraft skin.

[0006] Another object of the present invention is to provide an aircraft fuselage assembly method applied to the above-mentioned aircraft fuselage assembly device, which can ensure the installation accuracy of the aircraft skin.

[0007] In order to achieve the above object, the present invention provides the following technical solutions:

[0008] An aircraft fuselage assembly device is used to assemble an aircraft, the aircraft comprising a forward fuselage frame, a tail fuselage frame, a first skin, and a second skin, the forward fuselage frame and the tail fuselage frame being arranged sequentially along a first direction, the first skin and the second skin being symmetrically arranged along a centerline of a second direction, the second direction being perpendicular to the first direction;

[0009] The aircraft fuselage assembly device comprises:

[0010] Workbench;

[0011] At least two pairs of movable outer shape clamping mechanisms are spaced apart along the first direction and are movably disposed on the workbench along the second direction. The paired movable outer shape clamping mechanisms are disposed opposite to each other. The movable outer shape clamping mechanisms have a working position and a withdrawn position. When the movable outer shape clamping mechanisms are in the working position, they are used to position the respective fuselage frames of the front fuselage skeleton, or to position and press the first skin and / or the second skin after installation. When the movable outer shape clamping mechanisms are in the withdrawn position, they are used to make way for assembly of the first skin or the second skin.

[0012] an eccentric fuselage frame fixing frame, used to fix the tail fuselage frame and make way for one of the first skin and the second skin; the eccentric fuselage frame fixing frame is removable relative to the workbench; after the eccentric fuselage frame fixing frame is removed, it is used to make way for the other of the first skin and the second skin;

[0013] A suspension device has a preset relative position with the workbench and is used for suspending the front fuselage frame.

[0014] Optionally, the movable outer shape clamping mechanism corresponding to the front fuselage frame includes:

[0015] a support frame, movably provided on the workbench along the second direction;

[0016] A card plate and a positioning block detachably connected to the card plate, the card plate is arranged on the support frame, and when the positioning block is connected to the card plate, the positioning block is used to position each of the fuselage frames of the front fuselage skeleton; when the positioning block is removed, the card plate is used to position and press the first skin or the second skin.

[0017] Optionally, the eccentric fuselage frame fixing frame includes:

[0018] Two oppositely arranged positioning members are used to correspondingly fix a single fuselage frame of the tail fuselage frame;

[0019] a first supporting member, wherein both of the positioning members are connected to the first supporting member;

[0020] An eccentric column is connected to the first support member and is close to one of the positioning members. The eccentric column is detachably arranged on the workbench.

[0021] Optionally, it also includes:

[0022] The wing mounting interface template is provided on the suspension device. The wing mounting interface template is provided with first mounting parts on both sides along the first direction. The two first mounting parts are used to position and connect the two preset fuselage frames of the front fuselage skeleton.

[0023] Optionally, it also includes:

[0024] The front landing gear mounting interface master mold is arranged on the workbench. The front landing gear mounting interface master mold is respectively provided with second mounting parts on both sides along the second direction. The two second mounting parts are used for correspondingly positioning the preset longitudinal beams connecting the front fuselage frame.

[0025] Optionally, it also includes:

[0026] The front fuselage frame clamping device includes a first bottom contoured card that can be raised and lowered along a third direction. When the first bottom contoured card is raised, it is used to press the first skin and the second skin to cover the bottom of the front fuselage skeleton part. The third direction is perpendicular to the first direction and the second direction respectively.

[0027] Optionally, it also includes:

[0028] The auxiliary support device for the bottom of the skin includes a second bottom contoured card that can be raised and lowered along a third direction. When the second bottom contoured card is raised, it is used to press the first skin and the second skin to cover the bottom of the tail fuselage frame part.

[0029] Optionally, the workbench includes a first workbench and a second workbench that are spaced apart, and the front fuselage frame clamping device and the skin bottom auxiliary support device are respectively arranged in the gap between the first workbench and the second workbench.

[0030] Optionally, the workbench is provided with:

[0031] a positioning portion for positioning the movable outer shape clamping mechanism at the working position; and / or,

[0032] An auxiliary tightening device is used to tighten the movable outer shape clamping plate mechanism when the movable outer shape clamping plate mechanism is located in the working position.

[0033] An aircraft fuselage assembly method, applied to the above-mentioned aircraft fuselage assembly device, the aircraft fuselage assembly method comprising:

[0034] placing the movable outer shape clamping plate mechanism of the aircraft fuselage assembly device in a working position, and using the movable outer shape clamping plate mechanism to position each fuselage frame of the front fuselage skeleton of the aircraft;

[0035] Using the eccentric fuselage frame fixing frame of the aircraft fuselage assembly device to position and fix each fuselage frame of the tail fuselage skeleton;

[0036] Connecting the fuselage longitudinal beams of the front fuselage frame to the corresponding fuselage frames to form the entire front fuselage frame;

[0037] suspending the front fuselage frame using the suspension device of the aircraft fuselage assembly device;

[0038] Place the movable outer shape clamping plate mechanism in the withdrawal position;

[0039] pre-installing a first skin of the aircraft;

[0040] placing the movable outer shape clamping plate mechanism in the working position and connecting the movable outer shape clamping plate mechanism to the first skin;

[0041] Moving the movable outer shape clamping plate mechanism to the exit position, driving the first skin to separate from the front fuselage frame and the rear fuselage frame;

[0042] applying glue to the first skin;

[0043] The movable outer shape clamping plate mechanism drives the glued first skin to move to the working position, so that the first skin is bonded to the front fuselage frame and the tail fuselage frame;

[0044] removing the eccentric fuselage frame fixing bracket;

[0045] pre-installing a second skin of the aircraft;

[0046] placing the movable outer shape clamping plate mechanism in the working position and connecting the movable outer shape clamping plate mechanism to the second skin;

[0047] Moving the movable outer shape clamping plate mechanism to the exit position, driving the second skin to separate from the front fuselage frame and the tail fuselage frame;

[0048] applying glue to the second skin;

[0049] The movable outer shape clamping plate mechanism drives the glue-coated second skin to move to the working position, so that the second skin is bonded to the front fuselage frame and the tail fuselage frame.

[0050] The aircraft fuselage assembly device provided by the present invention has at least the following beneficial effects:

[0051] When the aircraft fuselage assembly device is used to assemble an aircraft, the movable outer shape clamping plate mechanism is placed in the working position, and the movable outer shape clamping plate mechanism is used to position the various fuselage frames of the front fuselage frame and the tail fuselage frame of the aircraft; after the various fuselage frames of the front fuselage frame are positioned by the movable outer shape clamping plate mechanism, the fuselage longitudinal beams of the front fuselage frame are connected to the corresponding fuselage frames to form an integral front fuselage frame; then, the assembled front fuselage frame is suspended by the suspension device; and the tail fuselage frame is fixed by the eccentric fuselage frame fixing frame; at this time, under the action of the suspension device and the eccentric fuselage frame fixing frame, the front fuselage frame and the tail fuselage frame remain in position unchanged, so the movable outer shape clamping plate mechanism can be used to fix the front fuselage frame. The plate mechanism moves from the working position to the exit position, so that the movable outer shape clamping plate mechanism makes way for the installation of the first skin; then, the first skin of the aircraft is pre-installed, that is, the first skin is leaned against the front fuselage frame and the tail fuselage frame from the side, and the first skin is fitted to the front fuselage frame and the tail fuselage frame; then, the movable outer shape clamping plate mechanism is moved from the exit position to the working position, so that the movable outer shape clamping plate mechanism presses the first skin, and the movable outer shape clamping plate mechanism is connected to the first skin; then, the movable outer shape clamping plate mechanism is moved from the working position to the exit position, so that the movable outer shape clamping plate mechanism drives the first skin to move away from the front fuselage frame and the tail fuselage frame, thereby The first skin is separated from the front fuselage frame and the tail fuselage frame; then, glue is applied to the first skin, that is, glue is applied to the position where the first skin is used to combine with the front fuselage frame and the tail fuselage frame; then, the movable outer shape clamping plate mechanism drives the glued first skin to move to the working position, so that the first skin is bonded to the front fuselage frame and the tail fuselage frame, thereby realizing the installation of the first skin; during the installation of the first skin, since the eccentric fuselage frame fixing frame gives way to the first skin, the eccentric fuselage frame fixing frame does not interfere with the installation of the first skin, thereby ensuring the smooth installation of the first skin; after the installation of the first skin is completed, the eccentric fuselage frame fixing frame is removed, at this time, the tail fuselage frame and the first skin are connected. The skin has been fixed, and the tail fuselage frame, the first skin and the front fuselage frame form an integral structure, and the front fuselage frame is suspended by the suspension device to keep its position unchanged. Therefore, after removing the eccentric fuselage frame fixing frame, the position of the tail fuselage frame can still be ensured. At this time, the eccentric fuselage frame fixing frame can make way for the installation of the second skin, so that the second skin can be pre-installed; that is, the second skin is leaned against the front fuselage frame and the tail fuselage frame from the side, and the second skin is attached to the front fuselage frame and the tail fuselage frame; then, the movable outer shape clamping plate mechanism is moved from the withdrawal position to the working position, so that the movable outer shape clamping plate mechanism presses the second skin and connects the movable outer shape clamping plate mechanism to the second skin;Then, the movable outer shape clamping plate mechanism is moved from the working position to the withdrawn position, so that the movable outer shape clamping plate mechanism drives the second skin to move away from the front fuselage frame and the tail fuselage frame, thereby separating the second skin from the front fuselage frame and the tail fuselage frame; then, the second skin is coated with glue, that is, the second skin is coated with glue at the position where it is used to connect with the front fuselage frame and the tail fuselage frame; then, the movable outer shape clamping plate mechanism drives the glued second skin to move to the working position, so that the second skin is bonded to the front fuselage frame and the tail fuselage frame, thereby completing the installation of the second skin. At this point, the first skin and the second skin have been installed and the first skin and the second skin are assembled into a complete skin of the aircraft. The movable outer shape clamping plate mechanism presses the first skin and the second skin until the structural glue is cured, and then the movable outer shape clamping plate mechanism is removed, and the fuselage assembly is completed.

[0052] From this, it can be seen that the aircraft fuselage assembly device uses a movable external shape clamping plate mechanism to position each fuselage frame of the front fuselage frame and the tail fuselage frame when in the working position, which is beneficial to ensure the positioning accuracy of the aircraft frame; after the assembly of the front fuselage frame is completed, the assembled front fuselage frame is suspended by a suspension device, and the tail fuselage frame is fixed by an eccentric fuselage frame fixing frame, so that the movable external shape clamping plate mechanism can be switched between the working position and the exit position, thereby realizing the process of "first skin and aircraft frame grinding and assembly → first skin and aircraft frame separation → first skin gluing → first skin re-installation and positioning → first skin and aircraft frame bonding and pressing", thereby realizing the installation of the first skin and fully ensuring the various dimensional requirements of the first skin such as installation accuracy, bonding quality, external contour, etc.; similarly, when the first skin is installed, under the condition that the first skin is bonded to the front fuselage frame and the tail fuselage frame as a whole, the assembled front fuselage frame and the tail fuselage frame are suspended by the suspension device. The eccentric fuselage frame fixing frame can be removed to make way for the installation of the second skin. At this time, the movable shape clamping plate mechanism is switched between the working position and the exit position to realize the process flow of "second skin and aircraft frame grinding and assembly → second skin and aircraft frame separation → second skin coating → second skin re-installation and positioning → second skin and aircraft frame bonding and pressing". The installation of the second skin is realized and the various dimensional requirements such as installation accuracy, bonding quality and shape profile of the second skin are fully guaranteed. Since the structural adhesive has the characteristic of short operation time, it is necessary to quickly complete the positioning of the skin after coating. Therefore, the embodiment of the present invention adopts the operation of the movable shape clamping plate mechanism to realize rapid and repeated positioning of the skin and ensure positioning accuracy. Moreover, the movable shape clamping plate mechanism is used to compress and constrain the first skin and the second skin, and the movable shape clamping plate mechanism and the eccentric fuselage frame fixing frame do not interfere with the installation of the first skin and the second skin, which is the key to ensuring the aerodynamic shape profile accuracy of the aircraft skin after assembly.

[0053] The aircraft fuselage assembly method provided by the present invention is applied to any one of the above-mentioned aircraft fuselage assembly devices, and at least includes the beneficial effects of the above-mentioned aircraft fuselage assembly device. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or related technologies, the following briefly introduces the drawings required for use in the embodiments or related technical descriptions. Obviously, the drawings described below are merely embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0055] Figure 1 A schematic diagram of the structure of the aircraft before the first and second skins are assembled with the fuselage frame;

[0056] Figure 2 A schematic structural diagram of an aircraft fuselage assembly device provided in a specific embodiment of the present invention;

[0057] Figure 3 A schematic diagram of the structure after the mobile outer shape clamping mechanism positions the fuselage frame of the fuselage skeleton and the longitudinal beams of the front fuselage skeleton are connected to the corresponding fuselage frames;

[0058] Figure 4 This is a structural diagram of the front fuselage frame after the suspension device suspends the assembly, the eccentric fuselage frame fixing frame fixes the tail fuselage frame, and the movable outer shape clamping plate mechanism is in the withdrawal position;

[0059] Figure 5 This is a schematic diagram of the structure after the first skin is installed;

[0060] Figure 6 This is a structural diagram of the second skin being installed and the movable outer shape clamping mechanism pressing the first skin and the second skin;

[0061] Figure 7 This is a structural diagram of the aircraft when it is assembled and the movable outer shape clamping plate mechanism is in the withdrawal position;

[0062] Figure 8 It is a structural diagram of the movable outer shape pallet mechanism on the workbench;

[0063] Figure 9 It is a partial enlarged schematic diagram of the movable outer shape card mechanism when it is in the withdrawal position;

[0064] Figure 10 It is a partial enlarged schematic diagram of the fuselage frame in which the movable outer shape clamping plate mechanism is located in the working position and positions and fixes the front fuselage frame;

[0065] Figure 11 It is a structural schematic diagram of an eccentric fuselage frame fixing frame;

[0066] Figure 12 A schematic diagram of the structure of the fuselage frame for positioning and fixing the tail fuselage frame with an eccentric fuselage frame fixing frame;

[0067] Figure 13 This is a schematic diagram of the structure of the wing installation interface template;

[0068] Figure 14 A schematic diagram showing the structure of the wing mounting interface, which is positioned to connect two preset fuselage frames;

[0069] Figure 15 This is a schematic diagram of the structure of the wing installation interface template connected to the suspension device;

[0070] Figure 16 This is a schematic diagram of the structure of the front fuselage frame after the suspension device is assembled by suspensory modeling through the wing mounting interface;

[0071] Figure 17 This is a schematic diagram of the structure of the front landing gear installation interface template;

[0072] Figure 18 A schematic diagram of the structure for connecting two preset longitudinal beams for the front landing gear installation interface;

[0073] Figure 19 This is a partial enlarged schematic diagram of the installation position of the front landing gear installation interface template;

[0074] Figure 20 It is a structural schematic diagram of the front fuselage frame pressing device;

[0075] Figure 21 It is a schematic diagram of the structure of the front fuselage frame pressing device and the skin bottom auxiliary support device 8 pressing the first skin and the second skin bottom;

[0076] Figure 22 This is a flow chart of an aircraft fuselage assembly method provided in a specific embodiment of the present invention.

[0077] Reference numerals:

[0078] 1-Workbench; 11-First workbench; 12-Second workbench; 13-Auxiliary tensioner; 14-First positioning pin hole; 15-Slide rail; 2-Mobile outer shape clamping plate mechanism; 21-Support frame; 211-Second positioning pin hole; 22-Clamping plate; 23-Location block; 3-Eccentric fuselage frame fixing frame; 31-Location member; 32-First support member; 33-Eccentric column; 4-Suspension device; 41-Hanging seat; 5-Wing mounting bracket Mounting interface template; 51-first mounting part; 6-front landing gear mounting interface template; 7-front fuselage frame clamping device; 71-first bottom profiling card plate; 72-frame; 8-skin bottom auxiliary support device; 81-second bottom profiling card plate; 82-second bracket; 91-front fuselage frame; 911-preset fuselage frame; 912-preset longitudinal beam; 92-tail fuselage frame; 93-first skin; 94-second skin. DETAILED DESCRIPTION

[0079] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0080] The core of the present invention is to provide an aircraft fuselage assembly device that can ensure the installation accuracy of the aircraft skin. Another core of the present invention is to provide an aircraft fuselage assembly method applied to the above-mentioned aircraft fuselage assembly device that can ensure the installation accuracy of the aircraft skin.

[0081] The aircraft fuselage assembly device provided by the embodiment of the present invention is used to assemble an aircraft, such as Figure 1 As shown, the aircraft includes an aircraft frame, a first skin 93 and a second skin 94. The aircraft frame includes a front fuselage frame 91 and a tail fuselage frame 92. The front fuselage frame 91 and the tail fuselage frame 92 are arranged in sequence along a first direction. The first skin 93 and the second skin 94 are symmetrically arranged along the center line of a second direction, and the second direction is perpendicular to the first direction.

[0082] It should be noted that in the embodiments of the present invention, the first direction refers to the longitudinal direction of the aircraft, and the second direction refers to the width direction of the aircraft. That is, in the embodiments of the present invention, the first skin 93 and the second skin 94 are symmetrically distributed about the centerline of the width direction of the aircraft. In other words, the aircraft skin is divided into two left and right skins along the width direction. Furthermore, the third direction in the embodiments of the present invention refers to the vertical direction of the aircraft.

[0083] In addition, in some embodiments, the forward fuselage frame 91 includes at least two fuselage frames of different specifications and longitudinal beams connecting the fuselage frames. The fuselage frames and longitudinal beams of the forward fuselage frame 91 are connected to form an integral forward fuselage frame 91. The tail fuselage frame 92 can be composed of fuselage frames of different specifications. That is, the fuselage frames of the tail fuselage frame 92 can be independent of each other, providing spacers at predetermined positions along a first direction, without being connected together by longitudinal beams. For example, the fuselage frames of the forward fuselage frame 91 and the tail fuselage frame 92 are each an integral circular frame structure. In addition, the first skin 93 and the second skin 94 are bonded to the forward fuselage frame 91 and the tail fuselage frame 92 using structural adhesive.

[0084] Furthermore, it should be noted that the embodiments of the present invention do not limit the specific material of the aircraft. For example, the main body of the aircraft is made of carbon fiber. Furthermore, the embodiments of the present invention do not limit the specific dimensions of the aircraft. For example, the length of the aircraft along the first direction may be 10 meters.

[0085] Please refer to Figure 2 An embodiment of the present invention provides an aircraft fuselage assembly device, which includes a workbench 1, a movable shape card mechanism 2, an eccentric fuselage frame fixing frame 3, and a suspension device 4. The number of the movable shape card mechanism 2 is at least two pairs, and the movable shape card mechanisms 2 of different pairs are arranged at intervals along a first direction, and the movable shape card mechanism 2 can be movably arranged on the workbench 1 along a second direction. The paired movable shape card mechanisms 2 are arranged relative to each other, and the movable shape card mechanism 2 has a working position and an exit position. When the movable shape card mechanism 2 is in the working position, it is used to position the front fuselage frame 91 Each fuselage frame, or used to position and press the installed first skin 93 or second skin 94. When the movable outer shape clamping plate mechanism 2 is in the exit position, it is used to make way for the assembly of the first skin 93 or the second skin 94; the eccentric fuselage frame fixing frame 3 is used to fix the tail fuselage skeleton 92 and make way for one of the first skin 93 and the second skin 94. The eccentric fuselage frame fixing frame 3 can be disassembled relative to the workbench 1. After the eccentric fuselage frame fixing frame 3 is disassembled, it is used to make way for the other of the first skin 93 and the second skin 94; the suspension device 4 has a preset relative position with the workbench 1, and is used to suspend the front fuselage skeleton 91.

[0086] Please refer to Figure 3-Figure 7When the aircraft fuselage assembly device is used to assemble an aircraft, the movable outer shape clamping plate mechanism 2 is placed in the working position, and the movable outer shape clamping plate mechanism 2 is used to position the various fuselage frames of the front fuselage frame 91 and the tail fuselage frame 92 of the aircraft; after the various fuselage frames of the front fuselage frame 91 are positioned by the movable outer shape clamping plate mechanism 2, the fuselage longitudinal beams of the front fuselage frame 91 are connected to the corresponding fuselage frames to form an integral front fuselage frame 91; then, the assembled front fuselage frame 91 is suspended by the suspension device 4; and the tail fuselage frame 92 is fixed by the eccentric fuselage frame fixing frame 3; at this time, under the action of the suspension device 4 and the eccentric fuselage frame fixing frame 3, the front fuselage frame 91 and the tail fuselage frame 92 remain in position, so , the movable outer shape clamping mechanism 2 can be moved from the working position to the withdrawal position, so that the movable outer shape clamping mechanism 2 makes way for the installation of the first skin 93; then, the first skin 93 of the aircraft is pre-installed, that is, the first skin 93 is leaned against the front fuselage frame 91 and the tail fuselage frame 92 from the side, and the first skin 93 is fitted to the front fuselage frame 91 and the tail fuselage frame 92; then, the movable outer shape clamping mechanism 2 is moved from the withdrawal position to the working position, so that the movable outer shape clamping mechanism 2 presses the first skin 93, and connects the movable outer shape clamping mechanism 2 to the first skin 93; then, the movable outer shape clamping mechanism 2 is moved from the working position to the withdrawal position, so that the movable outer shape clamping mechanism 2 drives the first skin 93 away from the front fuselage frame The first skin 93 is moved in the direction of the front fuselage frame 91 and the tail fuselage frame 92, thereby separating the first skin 93 from the front fuselage frame 91 and the tail fuselage frame 92; then, the first skin 93 is coated with glue, that is, the position where the first skin 93 is used to be combined with the front fuselage frame 91 and the tail fuselage frame 92 is coated with glue; then, the movable outer shape clamping plate mechanism 2 drives the first skin 93 coated with glue to the working position, so that the first skin 93 is bonded to the front fuselage frame 91 and the tail fuselage frame 92, thereby realizing the installation of the first skin 93; during the installation process of the first skin 93, since the eccentric fuselage frame fixing frame 3 gives way to the first skin 93, the eccentric fuselage frame fixing frame 3 does not interfere with the installation of the first skin 93, which can ensure that the first skin 93 3 is smoothly installed; after the installation of the first skin 93 is completed, the eccentric fuselage frame fixing frame 3 is removed. At this time, the tail fuselage frame 92 and the first skin 93 are fixed, and the tail fuselage frame 92, the first skin 93 and the front fuselage frame 91 form an integral structure, and the front fuselage frame 91 is suspended by the suspension device 4 to keep its position unchanged. Therefore, after removing the eccentric fuselage frame fixing frame 3, the position of the tail fuselage frame 92 can still be ensured. At this time, the eccentric fuselage frame fixing frame 3 can make way for the installation of the second skin 94, so that the second skin 94 can be pre-installed; that is, the second skin 94 is made to lean against the front fuselage frame 91 and the tail fuselage frame 92 from the side, and the second skin 94 is attached to the front fuselage frame 91 and the tail fuselage frame 92;Then, the movable outer shape card mechanism 2 is moved from the exit position to the working position, so that the movable outer shape card mechanism 2 presses the second skin 94 and connects the movable outer shape card mechanism 2 to the second skin 94; then, the movable outer shape card mechanism 2 is moved from the working position to the exit position, so that the movable outer shape card mechanism 2 drives the second skin 94 to move away from the front fuselage frame 91 and the tail fuselage frame 92, thereby separating the second skin 94 from the front fuselage frame 91 and the tail fuselage frame 92; then, the second skin 94 is coated with glue, that is, the second skin 94 is used to be connected to the front fuselage frame 91 and the tail fuselage frame Glue is applied to the fuselage frame 92 where it meets the surface. Then, the movable outer shape clamping mechanism 2 drives the glued second skin 94 to the working position, where it is bonded to the front fuselage frame 91 and the rear fuselage frame 92. This completes the installation of the second skin 94. At this point, the first skin 93 and the second skin 94 are both installed, forming the complete aircraft skin. The movable outer shape clamping mechanism 2 compresses the first skin 93 and the second skin 94 until the structural adhesive solidifies. The movable outer shape clamping mechanism 2 is then removed, and the fuselage assembly is complete.

[0087] It can be seen from this that the aircraft fuselage assembly device uses the movable shape clamping plate mechanism 2 to position each fuselage frame of the front fuselage frame 91 and the tail fuselage frame 92 when in the working position, which is beneficial to ensure the positioning accuracy of the aircraft frame; after the front fuselage frame 91 is assembled, the assembled front fuselage frame 91 is suspended by the suspension device 4, and the tail fuselage frame 92 is fixed by the eccentric fuselage frame fixing frame 3, so that the movable shape clamping plate mechanism 2 can be switched between the working position and the exit position, thereby realizing the first skin 93 and the aircraft frame grinding. The process flow is as follows: first skin 93 is installed → first skin 93 is separated from aircraft frame → first skin 93 is glued → first skin 93 is reinstalled and positioned → first skin 93 is bonded and pressed against aircraft frame, thereby achieving the installation of first skin 93 and fully ensuring the various dimensional requirements of the first skin 93 such as installation accuracy, bonding quality, and external profile; similarly, when the installation of the first skin 93 is completed, under the condition that the first skin 93 is bonded to the front fuselage frame 91 and the tail fuselage frame 92 as a whole, the assembled front fuselage frame 91 and the tail fuselage frame 92 are suspended by the suspension device 4. The skeleton 92 and the first skin 93 are integrally formed, and the eccentric fuselage frame fixing frame 3 can be removed to make way for the installation of the second skin 94. At this time, the movable shape clamping plate mechanism 2 is switched between the working position and the exit position to realize the process of "assembly of the second skin 94 and the aircraft skeleton → separation of the second skin 94 and the aircraft skeleton → gluing the second skin 94 → re-installation and positioning of the second skin 94 → bonding and pressing the second skin 94 and the aircraft skeleton". In this way, the installation of the second skin 94 is realized and the installation accuracy, bonding quality and shape of the second skin 94 are fully guaranteed. Various dimensional requirements such as contour; since structural adhesive has the characteristic of short operation time, it is necessary to quickly complete the positioning of the skin after gluing. Therefore, the embodiment of the present invention adopts the operation of the movable contour clamping mechanism 2 to realize rapid and repeated positioning of the skin and ensure positioning accuracy; moreover, the movable contour clamping mechanism 2 is used to compress and constrain the first skin 93 and the second skin 94, and the movable contour clamping mechanism 2 and the eccentric fuselage frame fixing frame 3 do not interfere with the installation of the first skin 93 and the second skin 94, which is the key to ensuring the accuracy of the aerodynamic contour of the aircraft skin after assembly.

[0088] It should be noted that this embodiment does not limit the specific structure of the mobile shape clamp mechanism 2, as long as the mobile shape clamp mechanism 2 can be switched between the working position and the exit position, and when the mobile shape clamp mechanism 2 is in the working position, it can position the front fuselage frame 91 or the tail fuselage frame 92, or be used to press the first skin 93 or the second skin 94 after installation.

[0089] Please refer to Figure 8 、 Figure 9 and Figure 10In some embodiments, the movable outer shape cardboard mechanism 2 corresponding to the front fuselage frame 91 includes a support frame 21, a cardboard 22 and a positioning block 23. The support frame 21 can be movably arranged on the workbench 1 along the second direction; the cardboard 22 is arranged on the support frame 21, and the positioning block 23 is detachably connected to the cardboard 22. When the positioning block 23 is connected to the cardboard 22, the positioning block 23 is used to position each fuselage frame of the front fuselage frame 91; when the positioning block 23 is removed, the cardboard 22 is used to position and press the first skin 93 or the second skin 94.

[0090] That is to say, this embodiment utilizes the support frame 21 to set and support the card plate 22 and the positioning block 23, and the support frame 21 moves relative to the workbench 1 in the second direction, thereby driving the card plate 22 and the positioning block 23 to move in the second direction. At the same time, the positioning block 23 is detachably connected to the card plate 22 to achieve positioning of each fuselage frame of the front fuselage skeleton 91 by the positioning block 23, so as to ensure that each fuselage frame has an accurate position, and to achieve positioning of the first skin 93 and the second skin 94 by the card plate 22 and to press them after installation. It should be noted that the embodiment of the present invention does not limit the specific detachable connection method between the positioning block 23 and the card plate 22, as long as the detachable connection between the positioning block 23 and the card plate 22 can be achieved. For example, the positioning block 23 is connected to the card plate 22 using bolts.

[0091] For example, the positioning block 23 is provided with a positioning pin hole, so that the positioning pins can be used to connect and position the fuselage frame to the positioning block 23. When the fuselage frame is positioned on the positioning block 23 by the positioning pins, the longitudinal beams of the front fuselage frame 91 can be connected to each fuselage frame to assemble and form the entire front fuselage frame 91. It will be understood that after the front fuselage frame 91 forms the mid-body, the positioning block 23 can be removed from the clamping plate 22. At this time, the front fuselage frame 91 is maintained in position by the suspension device 4, and the suspension device 4 can avoid interfering with the installation of the first skin 93 and the second skin 94.

[0092] In addition, it can be understood that after the first skin 93 or the second skin 94 is pre-installed with the aircraft frame and before the first skin 93 or the second skin 94 is separated from the aircraft frame, the first skin 93 or the second skin 94 needs to be connected to the clamping plate 22. For example, an L-shaped connector and hot melt adhesive are used to temporarily fix the first skin 93 or the second skin 94 to the clamping plate 22. In this way, the movable outer shape clamping plate mechanism 2 can be moved from the working position to the exit position to drive the first skin 93 or the second skin 94 to separate from the aircraft frame. The purpose of doing this is to ensure that the first skin 93 or the second skin 94 is in a precisely positioned state after grinding and installation, and the first skin 93 or the second skin 94 is "accommodated" by the clamping plate 22, and the first skin 93 or the second skin 94 is fixed on the clamping plate 22, so that the first skin 93 or the second skin 94 can be separated from the aircraft frame and glued, and repeatedly returned to the installation position while still in the precisely positioned state during grinding and installation, thereby ensuring the accuracy of repeated positioning, for example, the deviation of the first skin 93 or the second skin 94 along the first direction after installation is no more than 0.5 mm, and the deviation along the second direction is no more than 0.3 mm.

[0093] In addition, it can be understood that the main structure of the mobile shape clamping mechanism 2 corresponding to the tail section fuselage frame 92 can be the same as the main structure of the mobile shape clamping mechanism 2 corresponding to the front section fuselage frame 91. For example, the mobile shape clamping mechanism 2 corresponding to the tail section fuselage frame 92 can also include a support frame 21 and a clamping plate 22. At the same time, the positioning block 23 can be cancelled, so that the various fuselage frames of the tail section fuselage frame 92 are directly fixed on the eccentric fuselage frame fixing frame 3, that is, the eccentric fuselage frame fixing frame 3 is used to position the various fuselage frames of the tail section fuselage frame 92. The main function of the mobile shape clamping mechanism 2 corresponding to the tail section fuselage frame 92 is to use the clamping plate 22 to position and press the first skin 93 and the second skin 94.

[0094] It should be noted that the above embodiment does not limit the specific structure of the eccentric fuselage frame fixing frame 3, as long as it can position each fuselage frame of the tail fuselage skeleton 92, and can make way for one of the first skin 93 and the second skin 94 to be installed and make way for the other of the first skin 93 and the second skin 94 to be installed when disassembled.

[0095] Please refer to Figure 11 and Figure 12 In some embodiments, the eccentric fuselage frame fixing frame 3 includes two relatively arranged positioning members 31, a first support member 32 and an eccentric column 33. The positioning member 31 is used to correspond to a single fuselage frame of the fixed tail fuselage skeleton 92; both positioning members 31 are connected to the first support member 32, and the eccentric column 33 is connected to the first support member 32 and is close to one of the positioning members 31. The eccentric column 33 is detachably provided on the workbench 1.

[0096] It should be noted that in this embodiment, there are two positioning members 31 corresponding to a single fuselage frame of the tail fuselage frame 92, and the two positioning members 31 are arranged opposite each other to position and secure a single fuselage frame. For example, the positioning members 31 are provided with positioning pin holes, so that positioning pins inserted through the positioning pin holes can be used to secure the fuselage frame of the tail fuselage frame 92 to the corresponding positioning members 31. Furthermore, it is understood that the eccentric columns 33 provide overall support for the first support member 32 and the corresponding two positioning members 31. The eccentric columns 33 are positioned near one of the positioning members 31 to provide clearance for the other positioning member 31, thereby avoiding interference with the installation of one of the skins (e.g., the first skin 93). It is understood that when the number of fuselage frames of the tail fuselage frame 92 is at least two, the number of eccentric fuselage frame fixing brackets 3 is at least two, so as to separately position and secure multiple fuselage frames.

[0097] Also, please refer to Figure 13-16 In order to constrain the important dimensions of the installation interface of the fuselage frame of the front fuselage skeleton 91 and ensure the dimensional accuracy of the front fuselage skeleton 91, in some embodiments, the aircraft fuselage assembly device also includes a wing installation interface template 5, and the wing installation interface template 5 is arranged on the suspension device 4. The wing installation interface template 5 is respectively provided with a first installation portion 51 on both sides along the first direction. The two first installation portions 51 are used to correspond to the positioning of the two preset fuselage frames 911 connected to the front fuselage skeleton 91.

[0098] In other words, this embodiment utilizes the wing mounting interface master form 5 to constrain the positioning and installation of the two preset fuselage frames 911 of the front fuselage skeleton 91, thereby ensuring the installation accuracy of the two preset fuselage frames 911. It should be noted that this embodiment does not limit the specific structure of the first mounting portion 51, as long as it can achieve the positioning and installation of the preset fuselage frames 911. For example, the first mounting portion 51 is a threaded hole. For example, the wing mounting interface master form 5 is provided with two threaded holes on either side along the first direction. Four threaded holes can be formed using CNC machining and used with threaded locating pins to constrain the two preset fuselage frames 911. In other words, using the master form to ensure the key interface dimensions of the preset fuselage frames 911 is beneficial for improving the positioning accuracy of the fuselage frames. The wing mounting interface template 5 is provided on the suspension device 4. After the front fuselage frame 91 is assembled into a whole, the suspension device 4 is used to hang two preset fuselage frames 911 through the wing mounting interface template 5, so that the front fuselage frame 91 as a whole is in a suspended state, which can avoid interference with the installation of the first skin 93 and the second skin 94.

[0099] For further information, please refer to Figure 17 、 Figure 18 and Figure 19In some embodiments, the aircraft fuselage assembly device further includes a front landing gear mounting interface mold 6, which is disposed on the workbench 1, and the front landing gear mounting interface mold 6 is provided with second mounting portions on both sides along the second direction, respectively, and the two second mounting portions are used to correspond to and position the preset longitudinal beams 912 connecting the front fuselage frame 91.

[0100] In other words, this embodiment utilizes the front landing gear mounting interface master form 6 to constrain the positioning and installation of the two preset longitudinal beams 912 of the front fuselage frame 91, thereby ensuring the installation accuracy of the two preset longitudinal beams 912. It should be noted that this embodiment does not limit the specific structure of the second mounting portion, as long as it can achieve the positioning and installation of the preset longitudinal beams 912. For example, the second mounting portion is a threaded hole. For example, the front landing gear mounting interface master form 6 is provided with two threaded holes on either side along the second direction. Four threaded holes can be formed using CNC machining and used with threaded locating pins to constrain the two preset longitudinal beams 912. In other words, the use of a master form to ensure the key interface dimensions of the preset longitudinal beams 912 is conducive to improving the positioning accuracy of the longitudinal beams.

[0101] Also, please refer to Figure 20 In some embodiments, the aircraft fuselage assembly device further includes a front fuselage frame clamping device 7, which includes a first bottom contoured cardboard 71 that can be raised and lowered along a third direction. When the first bottom contoured cardboard 71 is raised, it is used to clamp the first skin 93 and the second skin 94 to cover the bottom of the front fuselage frame 91. The third direction is perpendicular to the first direction and the second direction, respectively.

[0102] Specifically, this embodiment utilizes the forward fuselage frame clamping device 7. Once both the first and second skins 93, 94 are installed, the first bottom contouring plate 71 is raised to compress the first and second skins 93, 94 to cover the bottom of the forward fuselage frame 91. This ensures a tight fit between the bottoms of the first and second skins 93, 94 and the fuselage frame, ensuring a high-quality bond. It will be appreciated that the lowering of the first bottom contouring plate 71 in the third direction prevents interference with the installation of the first and second skins 93, 94.

[0103] It should be noted that this embodiment does not limit the specific implementation method of lifting and lowering the first bottom profiling card plate 71 along the third direction, as long as the first bottom profiling card plate 71 can be lifted and lowered along the third direction. In some embodiments, the front fuselage frame clamping device 7 also includes a frame 72, a first bracket and a motor. The frame 72 is used to set the first bottom contoured card plate 71. It can be understood that the number of the first bottom contoured card plates 71 can be multiple, and multiple first bottom contoured card plates 71 are arranged at intervals along the first direction. Multiple first bottom contoured card plates 71 are all arranged on the frame 72. The frame 72 is used to connect all the first bottom contoured card plates 71 together and support all the first bottom contoured card plates 71 as a whole; in addition, the first bracket is supported on the ground, and the frame 72 is slidably arranged on the first bracket; the motor is used to provide a driving force for the overall lifting and lowering of the frame 72, that is, this embodiment uses a motor to drive the frame 72 to lift and lower along the third direction, so that the frame 72 drives all the first bottom contoured card plates 71 to lift and lower along the third direction as a whole, thereby ensuring the uniformity and consistency of the pressing force of all the first bottom contoured card plates 71 on the first skin 93 and the second skin 94.

[0104] Also, please refer to Figure 21 In some embodiments, the aircraft fuselage assembly device further includes a skin bottom auxiliary support device 8, which includes a second bottom contoured card plate 81 that can be raised and lowered along a third direction. When the second bottom contoured card plate 81 is raised, it is used to press the first skin 93 and the second skin 94 to cover the bottom of the tail fuselage frame 92.

[0105] Specifically, this embodiment utilizes the auxiliary skin bottom support device 8. Once both the first skin 93 and the second skin 94 are installed, the second bottom contouring plate 81 is raised, pressing the first skin 93 and the second skin 94 together to cover the bottom of the tail fuselage frame 92. This ensures a tight fit between the bottoms of the first and second skins 93 and 94, ensuring a high-quality bond. It will be appreciated that the lowering of the second bottom contouring plate 81 in the third direction prevents interference with the installation of the first and second skins 93 and 94.

[0106] It should be noted that this embodiment does not limit the specific implementation method for raising and lowering the second bottom profiling card 81 along the third direction, as long as the second bottom profiling card 81 can be raised and lowered along the third direction. In some embodiments, the skin bottom auxiliary support device 8 further includes a second bracket 82, a second support member, and a manual screw. The second bottom profiling card 81 is disposed on the second support member, the second support member is slidably connected to the second bracket 82, the second bracket 82 is supported on the ground, and the manual screw is threadedly connected to the second support member. By manually turning the manual screw, the height of the second support member can be adjusted, thereby causing the second support member to drive the second bottom profiling card 81 to rise and fall along the third direction, thereby achieving the second bottom profiling card 81 pressing and giving way to the first skin 93 and the second skin 94.

[0107] Furthermore, considering the simplicity of the structure and the convenience of installation, in some embodiments, the eccentric column 33 of the eccentric fuselage frame fixing frame 3 is detachably connected to the second bracket 82. That is, in this embodiment, the eccentric fuselage frame fixing frame 3 and the second bottom contoured card plate 81 are integrated into the second bracket 82, so that the eccentric fuselage frame fixing frame 3 and the second bottom contoured card plate 81 form an integrated structure, which facilitates the structural layout and installation of the aircraft fuselage assembly device.

[0108] In addition, the above embodiments do not limit the specific structure of the workbench 1. It can be understood that the workbench 1 mainly plays a supporting role, is used to connect the mobile outer shape clamping mechanism 2, etc., and provides a standing space for operators.

[0109] In some embodiments, the workbench 1 includes a first workbench 11 and a second workbench 12 that are spaced apart, and the front fuselage frame clamping device 7 and the skin bottom auxiliary support device 8 are respectively arranged in the gap between the first workbench 11 and the second workbench 12.

[0110] That is to say, in this embodiment, the front fuselage frame clamping device 7 and the skin bottom auxiliary support device 8 are respectively arranged in the gap between the first workbench 11 and the second workbench 12, which is conducive to positioning the front fuselage frame clamping device 7 and the skin bottom auxiliary support device 8 at the center position of the aircraft fuselage assembly device along the second direction, and is conducive to allowing the first bottom profiling card plate 71 and the second bottom profiling card plate 81 to press the bottom of the first skin 93 and the second skin 94, so that the first bottom profiling card plate 71, the second bottom profiling card plate 81 and the movable outer shape card plate mechanism 2 work together to make the first skin 93 and the second skin 94 fit tightly with the fuselage frame.

[0111] In addition, in some embodiments, the workbench 1 is provided with a positioning portion, an auxiliary tightening device 13 and / or a slide rail 15. The positioning portion is used to position the movable shape clamping mechanism 2 at the working position. The auxiliary tightening device 13 is used to tighten the movable shape clamping mechanism 2 when the movable shape clamping mechanism 2 is located at the working position. The slide rail 15 is slidingly connected to the movable shape clamping mechanism 2 to ensure the smooth movement of the movable shape clamping mechanism 2 between the working position and the exit position.

[0112] Exemplarily, the positioning portion is a first positioning pin hole 14 provided at a preset position of the workbench 1, and the movable shape clamping mechanism 2 is provided with a second positioning pin hole 211 for aligning and connecting with the first positioning pin hole 14. When the movable shape clamping mechanism 2 moves to the working position, the first positioning pin hole 14 and the second positioning pin hole 211 are aligned. At this time, the positioning pin is inserted into the first positioning pin hole 14 and the second positioning pin hole 211 to fix the movable shape clamping mechanism 2 in the working position.

[0113] Exemplarily, the auxiliary tightening device 13 is a screw structure, that is, by screwing the screw of the screw structure, the end of the auxiliary tightening device 13 is pressed against the movable outer shape clamping mechanism 2, so that the movable outer shape clamping mechanism 2 can be pressed against the first skin 93 and the second skin 94, ensuring the bonding accuracy of the first skin 93 and the second skin 94 to the fuselage frame respectively.

[0114] It should be noted that the above embodiment does not limit the specific number of the mobile shape card mechanism 2. For example, the number of the mobile shape card mechanism 2 is six pairs, and the paired mobile shape card mechanism 2 is respectively arranged on the first workbench 11 and the second workbench 12. The mobile shape card mechanism 2 corresponding to the front fuselage frame 91 can be four pairs, and the mobile shape card mechanism 2 corresponding to the rear fuselage frame 92 can be two pairs.

[0115] In addition, the above embodiments do not limit the specific structure of the suspension device 4, as long as the suspension device 4 can fix the front fuselage frame 91.

[0116] In some embodiments, the suspension device 4 is a gantry structure. Exemplarily, the gantry structure is arranged on both sides of the workbench 1 along the second direction.

[0117] Exemplarily, the gantry structure is a frame 72 structure formed by welding square steel, and the gantry structure includes two parallel column frames 72 and a beam connected between the tops of the two column frames 72; the column frames 72 are connected to the ground by expansion bolts, and the beam is provided with a hanger 41, and the wing mounting interface mold 5 is connected to the hanger 41 by bolts, that is, the suspension device 4 suspends the assembled front fuselage frame 91 through the wing mounting interface mold 5, so as to avoid interference with the installation of the first skin 93 and the second skin 94.

[0118] Please refer to Figure 22 In addition to the above-mentioned aircraft fuselage assembly device, an embodiment of the present invention further provides an aircraft fuselage assembly method applied to the aircraft fuselage assembly device disclosed in the above-mentioned embodiment. The aircraft fuselage assembly method includes steps S1 to S16:

[0119] S1: The movable outer shape clamping plate mechanism 2 of the aircraft fuselage assembly device is placed in the working position, and the movable outer shape clamping plate mechanism 2 is used to position each fuselage frame of the front fuselage skeleton 91 of the aircraft;

[0120] S2: Using the eccentric fuselage frame fixing frame 3 of the aircraft fuselage assembly device to position and fix each fuselage frame of the tail fuselage skeleton 92;

[0121] S3: Connecting the fuselage longitudinal beams of the front fuselage frame 91 to the corresponding fuselage frames to form the entire front fuselage frame 91;

[0122] S4: suspending the front fuselage frame 91 using the suspension device 4 of the aircraft fuselage assembly device;

[0123] S5: The movable outer shape clamping plate mechanism 2 is in the withdrawal position;

[0124] S6: Pre-installing the first skin 93 of the aircraft;

[0125] S7: placing the movable outer shape clamping plate mechanism 2 in the working position and connecting the movable outer shape clamping plate mechanism 2 to the first skin 93;

[0126] S8: Move the movable outer shape clamping plate mechanism 2 to the withdrawal position, driving the first skin 93 to separate from the front fuselage frame 91 and the tail fuselage frame 92;

[0127] S9: Apply glue to the first skin 93;

[0128] S10: The movable outer shape clamping plate mechanism 2 drives the glued first skin 93 to move to the working position, so that the first skin 93 is bonded to the front fuselage frame 91 and the rear fuselage frame 92;

[0129] S11: Remove the eccentric fuselage frame fixing bracket 3;

[0130] S12: Pre-installing the second skin 94 of the aircraft;

[0131] S13: placing the movable outer shape clamping plate mechanism 2 in the working position and connecting the movable outer shape clamping plate mechanism 2 to the second skin 94;

[0132] S14: Move the movable outer shape clamping plate mechanism 2 to the withdrawal position, driving the second skin 94 to separate from the front fuselage frame 91 and the rear fuselage frame 92;

[0133] S15: Apply glue to the second skin 94;

[0134] S16: The movable outer shape clamping plate mechanism 2 drives the glued second skin 94 to move to the working position, so that the second skin 94 is bonded to the front fuselage frame 91 and the rear fuselage frame 92.

[0135] It can be seen that through the above aircraft fuselage assembly method and using the above aircraft fuselage assembly device, the assembly of the aircraft can be achieved. The aircraft fuselage assembly method at least includes the beneficial effects of the above aircraft fuselage assembly device, which will not be repeated here.

[0136] It should also be noted that, in this specification, relational terms such as first and second, etc. are merely used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations.

[0137] The various embodiments in this specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other.

[0138] The above describes in detail the aircraft fuselage assembly device and aircraft fuselage assembly method provided by the present invention. Specific examples are used herein to illustrate the principles and implementation methods of the present invention. The description of the above embodiments is intended only to facilitate understanding of the method and core concept of the present invention. It should be noted that, for those skilled in the art, various improvements and modifications may be made to the present invention without departing from the principles of the present invention, and such improvements and modifications also fall within the scope of protection of the present invention.

Claims

1. An aircraft fuselage assembly device, characterized in that: Used for assembling an aircraft, the aircraft comprising a front fuselage frame (91), a tail fuselage frame (92), a first skin (93) and a second skin (94), the front fuselage frame (91) and the tail fuselage frame (92) being arranged in sequence along a first direction, the first skin (93) and the second skin (94) being symmetrically arranged along a center line of a second direction, the second direction being perpendicular to the first direction; The aircraft fuselage assembly device comprises: Workbench (1); At least two pairs of movable shape card mechanism (2) are arranged at intervals along the first direction and can be movably arranged on the workbench (1) along the second direction. The paired movable shape card mechanism (2) are arranged relative to each other. The movable shape card mechanism (2) has a working position and a withdrawal position. When the movable shape card mechanism (2) is located at the working position, it is used to position each fuselage frame of the front fuselage skeleton (91), or to position and press the first skin (93) and / or the second skin (94) after installation. When the movable shape card mechanism (2) is located at the withdrawal position, it is used to make way for the assembly of the first skin (93) or the second skin (94); an eccentric fuselage frame fixing frame (3) for fixing the tail fuselage frame (92) and making way for one of the first skin (93) and the second skin (94); the eccentric fuselage frame fixing frame (3) is detachable relative to the workbench (1); after the eccentric fuselage frame fixing frame (3) is disassembled, it is used to make way for the other of the first skin (93) and the second skin (94); The suspension device (4) has a preset relative position with the workbench (1) and is used to suspend the front fuselage frame (91).

2. The aircraft fuselage assembly device according to claim 1, characterized in that: The movable outer shape clamping plate mechanism (2) corresponding to the front fuselage frame (91) comprises: A support frame (21) is movably provided on the workbench (1) along the second direction; A card plate (22) and a positioning block (23) detachably connected to the card plate (22), wherein the card plate (22) is provided on the support frame (21); when the positioning block (23) is connected to the card plate (22), the positioning block (23) is used to position each of the fuselage frames of the front fuselage skeleton (91); when the positioning block (23) is disassembled, the card plate (22) is used to position and press the first skin (93) or the second skin (94).

3. The aircraft fuselage assembly device according to claim 1, characterized in that: The eccentric fuselage frame fixing frame (3) comprises: Two positioning members (31) arranged opposite to each other are used to fix a single fuselage frame of the tail fuselage frame (92); a first support member (32), wherein both of the positioning members (31) are connected to the first support member (32); An eccentric column (33) is connected to the first support member (32) and is close to one of the positioning members (31). The eccentric column (33) is detachably provided on the workbench (1).

4. The aircraft fuselage assembly device according to any one of claims 1 to 3, characterized in that: Also includes: A wing mounting interface former (5) is provided on the suspension device (4), and the wing mounting interface former (5) is provided with first mounting portions (51) on both sides along the first direction, respectively. The two first mounting portions (51) are used for correspondingly positioning and connecting two preset fuselage frames (911) of the front fuselage skeleton (91).

5. The aircraft fuselage assembly device according to any one of claims 1 to 3, characterized in that: Also includes: A front landing gear mounting interface former (6) is provided on the workbench (1), and the front landing gear mounting interface former (6) is provided with second mounting portions on both sides along the second direction, respectively, and the two second mounting portions are used for correspondingly positioning and connecting the preset longitudinal beams (912) of the front fuselage frame (91).

6. The aircraft fuselage assembly device according to any one of claims 1 to 3, characterized in that: Also includes: A front fuselage frame pressing device (7) comprises a first bottom profiled card plate (71) that can be raised and lowered along a third direction, wherein the first bottom profiled card plate (71) is used to press the first skin (93) and the second skin (94) to cover the bottom of the front fuselage frame (91) when the first bottom profiled card plate (71) is raised, and the third direction is perpendicular to the first direction and the second direction respectively.

7. The aircraft fuselage assembly device according to claim 6, characterized in that: Also includes: The skin bottom auxiliary support device (8) includes a second bottom profiling card plate (81) that can be raised and lowered along a third direction. When the second bottom profiling card plate (81) is raised, it is used to press the first skin (93) and the second skin (94) to cover the bottom of the tail fuselage frame (92).

8. The aircraft fuselage assembly device according to claim 7, characterized in that: The workbench (1) comprises a first workbench (11) and a second workbench (12) which are arranged at intervals, and the front fuselage frame pressing device (7) and the skin bottom auxiliary support device (8) are respectively arranged in the gap between the first workbench (11) and the second workbench (12).

9. The aircraft fuselage assembly device according to any one of claims 1 to 3, characterized in that: The workbench (1) is provided with: a positioning portion, used to position the movable outer shape clamping mechanism (2) at the working position; and / or, An auxiliary tightening device (13) is used to tighten the movable outer shape clamping plate mechanism (2) when the movable outer shape clamping plate mechanism (2) is located at the working position.

10. A method for assembling an aircraft fuselage, characterized in that: Applicable to the aircraft fuselage assembly device according to any one of claims 1 to 9, the aircraft fuselage assembly method comprising: The movable outer shape clamping plate mechanism (2) of the aircraft fuselage assembly device is placed in a working position, and each fuselage frame of the front fuselage skeleton (91) of the aircraft is positioned using the movable outer shape clamping plate mechanism (2); Using the eccentric fuselage frame fixing frame (3) of the aircraft fuselage assembly device to position and fix each fuselage frame of the tail fuselage skeleton (92); Connecting the fuselage longitudinal beams of the front fuselage frame (91) to corresponding fuselage frames to form the entire front fuselage frame (91); Utilizing the suspension device (4) of the aircraft fuselage assembly device to suspend the front fuselage frame (91); placing the movable outer shape clamping plate mechanism (2) in the withdrawal position; Pre-installing a first skin (93) of the aircraft; placing the movable outer shape clamping plate mechanism (2) in the working position, and connecting the movable outer shape clamping plate mechanism (2) to the first covering skin (93); Moving the movable outer shape clamping plate mechanism (2) to the exit position, driving the first skin (93) to separate from the front fuselage frame (91) and the rear fuselage frame (92); Applying glue to the first skin (93); The movable outer shape clamping plate mechanism (2) drives the first skin (93) coated with glue to move to the working position, so that the first skin (93) is bonded to the front fuselage frame (91) and the tail fuselage frame (92); Removing the eccentric fuselage frame fixing frame (3); Pre-installing a second skin (94) of the aircraft; placing the movable outer shape clamping plate mechanism (2) in the working position, and connecting the movable outer shape clamping plate mechanism (2) to the second skin (94); Moving the movable outer shape clamping plate mechanism (2) to the exit position, driving the second skin (94) to separate from the front fuselage frame (91) and the tail fuselage frame (92); Applying glue to the second skin (94); The movable outer shape clamping plate mechanism (2) drives the second skin (94) coated with glue to move to the working position, so that the second skin (94) is bonded to the front fuselage frame (91) and the tail fuselage frame (92).

Images