Aircraft tail structure assembling device

Abstract

The utility model provides an aircraft tail structure assembling device. The embodiment of the utility model provides an aircraft tail structure assembling device which is used for carrying and assembling a tail structure of an aircraft and comprises a first platform, a clamping assembly and a moving assembly. The clamping assembly is arranged on the first platform, the clamping assembly comprises two clamping pieces arranged in the first direction in a spaced mode, and the two clamping pieces can clamp the tail structure; the clamping piece can move in the second direction relative to the first platform so as to adjust the height of the clamped tail structure, the clamping piece can rotate relative to the first platform so as to adjust the posture of the clamped tail structure, and the second direction intersects with the first direction. The moving assembly can drive the first platform to move in the space.

Description

Technical Field

[0001] This application relates to the field of aircraft assembly technology, and in particular to an assembly device for the tail structure of an aircraft. Background Technology

[0002] Assembly is an important and complex task in the manufacturing process of aircraft, especially the installation of the V-tail. The V-tail consists of two wing surfaces, and it functions as both a vertical stabilizer and a horizontal stabilizer. It is relatively large and not easy to place, so a lot of manpower is required for adjustment, positioning and fixing.

[0003] Currently, the installation of V-tail fins typically involves lifting the aircraft's tail section with a crane or other lifting equipment, then manually adjusting the position of the V-tail fin to align it with the fuselage's mounting interface. However, this process heavily relies on the operator's experience and physical strength, requires a high level of coordination, and suffers from limitations in accuracy, high labor intensity, low efficiency, and safety hazards. Utility Model Content

[0004] To address the difficulty in installing the V-shaped tail fin of an aircraft, this application provides an assembly device for the tail structure of an aircraft that offers high installation efficiency and precision.

[0005] This application provides an assembly device for a tail structure of an aircraft, used for carrying and assembling the tail structure of an aircraft. The assembly device includes a first platform, a clamping assembly, and a moving assembly. The clamping assembly is disposed on the first platform and includes two clamping members spaced apart along a first direction, which can clamp the tail structure. The clamping members can move relative to the first platform along a second direction to adjust their height, and can rotate relative to the first platform to adjust their attitude. The second direction intersects the first direction. The moving assembly can drive the first platform to move in space.

[0006] Understandably, the clamping assembly is designed for the tail structure of the aircraft, providing a secure grip. Furthermore, the clamping assembly can be adjusted to accommodate different tail structures for optimal clamping. The clamping assembly can also adjust the height of the clamped tail structure, allowing it to be positioned at the required height during subsequent installation. The movable assembly, which drives the first platform to move within space, enables the clamping assembly to move as well, allowing the aircraft tail structure assembly device to move the tail structure to the desired installation location or to a location where it can be supported, facilitating subsequent operations.

[0007] In one embodiment, the clamping member includes a clamping portion and an adjusting portion, the clamping portion being rotatably connected to the adjusting portion, and the adjusting portion being movably connected to the first platform along the second direction.

[0008] In one embodiment, the clamping portion is provided with a clamping surface, the clamping surface is configured to abut against the tail structure, and the clamping surface is provided with a friction-enhancing member, the friction-enhancing member being configured to increase the friction between the tail structure and the clamping surface.

[0009] In one embodiment, along the first direction, the clamping surfaces of the two clamping members respectively abut against both sides of the tail structure, and the clamping surfaces of the two clamping members are inclined to each other.

[0010] In one embodiment, the friction enhancer is made of a soft material.

[0011] In one embodiment, a pressure detection device is provided on the clamping surface.

[0012] In one embodiment, the clamping member is provided with a quick-release mechanism.

[0013] In one embodiment, the aircraft tail structure assembly device further includes a host computer configured to control the moving component to move the first platform.

[0014] In one embodiment, the clamping assembly further includes a support member. Along a third direction, the support member is spaced apart on one side of the clamping member. The support member is capable of supporting the tail structure. The third direction intersects the first direction and the second direction.

[0015] In one embodiment, the support member is a telescopic structure, and its height can be adjusted in the second direction. Attached Figure Description

[0016] Figure 1 This is a perspective view of an aircraft tail structure assembly device provided in an embodiment of this application.

[0017] Figure 2 This is a rear view schematic diagram of an aircraft tail structure assembly device provided in an embodiment of this application.

[0018] Figure 3 A plan view of a friction-enhancing component of an aircraft tail structure assembly device provided in an embodiment of this application.

[0019] Figure 4 A perspective view of the second adjustment component of the aircraft tail structure assembly device provided in an embodiment of this application.

[0020] Figure 5This is a side view of an assembly device for the tail structure of an aircraft provided in an embodiment of this application.

[0021] Figure 6 This is a front view schematic diagram of a moving component in one embodiment of the aircraft tail structure assembly device provided in this application.

[0022] Explanation of key component symbols:

[0023] 100. Aircraft tail structure assembly device; 1. First platform; 2. Clamping assembly; 21. Clamping component; 211. Clamping part; 2110. Clamping surface; 2111. Friction enhancer; 212. Adjustment part; 22. Support component; 3. Moving assembly; 31. First adjustment assembly; 32. Second platform; 33. Second adjustment assembly; 331. First slide rail; 332. Second slide rail; 333. First slider; 334. Second slider; 335. Fifth platform; 34. Third platform; 35. Third adjustment assembly; 36. Fourth platform; 37. Fourth adjustment assembly; 38. Rolling component; X, first direction; Z, second direction; Y, third direction.

[0024] The following detailed description, in conjunction with the accompanying drawings, will further illustrate this application. Detailed Implementation

[0025] The following description will be given with reference to the accompanying drawings for a more complete description of the present application. The drawings illustrate exemplary embodiments of the present application. However, the present application may be implemented in many different forms and should not be construed as limited to the exemplary embodiments set forth herein. These exemplary embodiments are provided to make the present application thorough and complete, and to fully convey the scope of the present application to those skilled in the art. Similar reference numerals denote the same or similar components. The terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to limit the present application. As used herein, the singular forms “a,” “an,” and “the” are intended to also include the plural forms unless the context clearly indicates otherwise. Furthermore, when used herein, “comprising” and / or “including” and / or “having,” integers, steps, operations, components, and / or components, but without excluding the presence or addition of one or more other features, regions, integers, steps, operations, components, and / or groups thereof. Unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains. Furthermore, unless explicitly defined herein, terms such as those defined in a general dictionary should be interpreted as having the same meaning as they have in the relevant technology and in the content of this application, and should not be interpreted as having an idealized or overly formal meaning.

[0026] like Figure 1 and Figure 2As shown in the figure, this application provides an aircraft tail structure assembly device 100 for carrying and assembling the tail structure of an aircraft. The aircraft tail structure assembly device 100 includes a first platform 1, a clamping component 2, and a moving component 3.

[0027] For ease of reading, this application introduces a first direction X, a second direction Z, and a third direction Y to describe the embodiments of this application. The first direction X, the second direction Z, and the third direction Y can be three non-parallel straight lines in space; further, the first direction X, the second direction Z, and the third direction Y can be three mutually perpendicular directions in a three-dimensional coordinate system (a three-dimensional Cartesian coordinate system). In subsequent embodiments, the first direction X is described as the X-axis direction of the three-dimensional coordinate system, the second direction Z is the Z-axis direction of the three-dimensional coordinate system, and the third direction Y is the Y-axis direction of the three-dimensional coordinate system.

[0028] The clamping assembly 2 is mounted on the first platform 1. The clamping assembly 2 includes two clamping members 21 spaced apart along a first direction X. The two clamping members 21 can clamp the tail structure. The clamping members 21 can move relative to the first platform 1 along a second direction Z to adjust their height. The clamping members 21 can also rotate relative to the first platform 1 to adjust their posture. The moving assembly 3 can drive the first platform 1 to move within space.

[0029] In this embodiment, the tail structure of the aircraft can be a V-shaped tail fin of a large aircraft or drone, consisting of two inclined wing surfaces, which are difficult to clamp and move. In this application, two clamping members 21 are spaced apart along the first direction X to provide good support for both inclined wing surfaces of the V-shaped tail fin, while simultaneously positioning the tail structure between the two clamping members 21 for clamping. Each clamping member 21 may have at least two clamping points on its surface to ensure the V-tail is securely fixed. During clamping, the surface of the tail structure can be in contact with the surface of the clamping member 21 to ensure good clamping. The clamping member 21 may have a telescopic device, specifically a telescopic arm design, with an adjustment range of 500mm to 2000mm, allowing the clamping member 21 to move along the second direction Z. Adjusting the height of the clamping member 21 adjusts the position of the clamping member 21 on the tail structure, adapting to different tail structures of varying heights. After clamping, it can also move the tail structure to the required height.

[0030] The clamping member 21 can rotate relative to the first platform 1 around a rotation axis, the direction of which is parallel to the third direction Y. This allows the clamping member 21 to rotate within a range of ±15° on the original basis, so that it can be adjusted to a suitable angle before clamping, so as to fit the surface of the tail structure as closely as possible, thereby ensuring good clamping. After clamping, the angle of the tail structure can also be adjusted as needed to adjust the installation position of the tail structure.

[0031] The moving component 3 can be an AGV (Automated Guided Vehicle) or other device capable of moving the first platform 1, enabling the first platform 1 to move within space. The moving component 3 can also move the first platform 1 along a first direction X, a second direction Z, or a third direction Y to adjust the position of the first platform 1, thereby adjusting the position of the clamping component 2.

[0032] The moving component 3 may include a second platform 32 and a roller 38. The second platform 32 may be connected to the first platform 1. The roller 38 may be a wheel and is rotatably connected to the second platform 32. The second platform 32 can move by means of the roller 38, thereby enabling the first platform 1 connected to the second platform 32 to also move, thus realizing the movement of the first platform 1 in space.

[0033] Understandably, the clamping assembly 2 is designed for the tail structure of the aircraft, enabling it to grip the tail structure effectively. Furthermore, the clamping assembly 2 can be adjusted to better grip different tail structures. The clamping component 21 can also adjust the height of the clamped tail structure, allowing it to be adjusted to the required installation height during subsequent tail structure installation. The moving assembly 3, which drives the first platform 1 to move within space, allows the clamping assembly 2 to move within space, enabling the aircraft tail structure assembly device 100 to move the tail structure to the required installation position or to the position where the tail structure needs to be supported, facilitating subsequent operations.

[0034] In one embodiment, the clamping member 21 includes a clamping part 211 and an adjusting part 212. The clamping part 211 is rotatably connected to the adjusting part 212, and the adjusting part 212 is movably connected to the first platform 1 along the second direction Z.

[0035] In this embodiment, the clamping part 211 is used to contact and clamp the tail structure. It is connected to the adjusting part 212 via a rotating shaft so that the clamping part 211 is rotatably connected to the adjusting part 212, and the clamping part 211 can rotate within a range of ±15° from its original position. The adjusting part 212 can be a multi-segment telescopic arm structure, which can move along the second direction Z to adjust the height of the clamping member 21.

[0036] Understandably, the rotatable clamping part 211 and adjusting part 212 allow the angle of the clamping member 21 to be adjustable, enabling the finding of a better angle to fit the surface of the tail structure before clamping, and allowing the adjustment of the tail structure's posture after clamping. Similarly, the adjusting part 212, which can move along the second direction Z, can also adjust the appropriate height to properly clamp the tail structure, and can appropriately move the height of the tail structure after clamping to facilitate subsequent tail structure installation.

[0037] In other embodiments, the clamping member 21 may also be provided with a quick release mechanism, specifically a pneumatic quick release device, which can quickly release the tail structure in an emergency to improve clamping safety.

[0038] Further integration Figure 3 As shown, in one embodiment, the clamping part 211 is provided with a clamping surface 2110, the clamping surface 2110 is configured to abut against the tail structure, and the clamping surface 2110 is provided with a friction-enhancing member 2111, the friction-enhancing member 2111 is configured to increase the friction between the tail structure and the clamping surface 2110.

[0039] It is understandable that "resistance" means that the clamping surface 2110 is in contact with the tail structure at this time, and there is an interaction force between the two so that the clamping part 211 can clamp the tail structure.

[0040] In this embodiment, the friction enhancer 2111 can be an anti-slip pad. Other structures can also be used for the friction enhancer 2111, as long as they increase the friction between the tail structure and the clamping surface 2110 during clamping; no further restrictions are imposed here. The friction enhancer 2111 can be integrally formed with the clamping member 21 or formed separately. The friction enhancer 2111 can be formed by directly providing a concave-convex structure on the clamping surface 2110, thereby increasing the friction.

[0041] In other embodiments, the friction enhancer 2111 is made of a soft material, such as a soft pad, specifically high-density polyurethane foam with a thickness of 10 mm, to protect the surface of the tail structure.

[0042] Understandably, the friction enhancer 2111 makes the clamping member 21 more stable when clamping, while the flexible contact does not damage the surface of the tail structure, increasing clamping stability and making it safer to use.

[0043] In other embodiments, a pressure detection device may be provided on the clamping surface 2110 to detect the pressure on the clamping surface 2110 during clamping, facilitating operator monitoring of the clamping process and making the clamping process more reliable. The pressure detection device may be a pressure sensor, allowing the clamping force of the clamping member 21 to be precisely adjusted within the range of 0~1000N.

[0044] In one embodiment, along the first direction X, the clamping surfaces 2110 of the two clamping members 21 respectively abut against the two sides of the tail structure, and the two clamping surfaces 2110 are inclined to each other.

[0045] In this embodiment, the two clamping members 21 are arranged at an angle to each other, and the two clamping members 21 are roughly distributed in a "V" shape. Along the first direction X, the surfaces of the adjacent sides of the two clamping members 21 are set as clamping surfaces 2110.

[0046] Understandably, the inclined clamping surface 2110 can not only fit better with the two sides of the equally inclined tail structure, but also provide some support for the tail structure, thus achieving better clamping.

[0047] In one embodiment, the clamping assembly 2 further includes a support member 22. Along the third direction Y, the support member 22 is spaced apart on one side of the clamping member 21, and the support member 22 can support the tail structure.

[0048] In this embodiment, the support surface of the support member 22 that contacts the tail structure can be set to an arc shape according to the shape of the tail structure, so as to better fit the tail structure and provide good support. Similarly, the support member 22 can also be set as a telescopic structure, which can move in the second direction Z to adjust its height. The surface of the support member 23 can use high-density foam or soft rubber material to accommodate the slight unevenness of the tail structure surface. The support member 22 can rotate relative to the first platform 1 to better fit the tail structure, or adjust the position of the tail structure in subsequent processes to enable better installation.

[0049] Understandably, due to the large size of the tail structure, in order to avoid instability when the two clamping parts 21 are clamped, the support part 22 can provide further support for the tail structure to ensure that the clamping assembly 2 is stable and reliable when clamping.

[0050] In one embodiment, the moving component 3 further includes a first adjusting component 31, which is disposed on the second platform 32 and is connected to the first platform 1 for driving the first platform 1 to move along the second direction Z.

[0051] In this embodiment, the first adjustment component 31 may be composed of four hydraulic cylinders, which can move the first platform 1 in the second direction Z, thereby allowing the first platform 1 to be raised and lowered. Other devices may also be used for the first adjustment component 31, as long as they can enable the first platform 1 to be raised and lowered; no further restrictions are imposed here. The first adjustment component 31 can be precisely controlled by an electronic control unit.

[0052] Understandably, through the setting of the first adjustment component 31, the clamping component 2 can move in the second direction Z, and its position can be adjusted before clamping the tail structure to the clamping position. At the same time, the position of the first platform 1 can be adjusted after clamping to move the clamped tail structure to a suitable installation position.

[0053] like Figure 4 and Figure 5 As shown, in one embodiment, the moving component 3 further includes a second adjusting component 33, which is disposed on the first platform 1. The second adjusting component 33 is connected to the clamping component 2 and is used to drive the clamping component 2 to move along the first direction X and the third direction Y.

[0054] In this embodiment, the second adjustment component 33 may include a first slide rail 331, a second slide rail 332, a first slider 333, a second slider 334, and a fifth platform 335. The clamping component 2 is connected to the fifth platform 335. The first slide rail 331 is connected to the fifth platform 335 and can extend along a first direction X. The second slide rail 332 is connected to the first platform 1 and can extend along a third direction Y. The first slider 333 is movably connected to the first slide rail 331 and can move along the first slide rail 331, i.e., the first slider 333 can move along the first direction X. The second slider 334 is movably connected to the second slide rail 332 and can move along the second slide rail 332, i.e., the second slider 334 can move along a third direction Y. The first slider 333 and the second slider 334 are connected. When the second slider 334 moves along the third direction Y, it drives the first slider 333 and the first slide rail 331 to move, thereby driving the fifth platform 335 to move, and further driving the clamping assembly 2 to move along the third direction Y. When the first slider 333 moves relative to the first slide rail 331, the first slide rail 331 drives the fifth platform 335 to move along the first direction X, thereby driving the clamping assembly 2 to move, realizing the movement of the clamping assembly 2 in the first direction X and the third direction Y. The second adjustment assembly 33 can also be selected from other structures, as long as it can realize the movement of the clamping assembly 2 in the first direction X and the third direction Y, without too many restrictions. The second adjustment assembly 33 can be driven by a motor to achieve high-precision adjustment in the first direction X and the third direction Y.

[0055] Understandably, the second adjustment component 33 enables the clamping component 2 to move in the first direction X and the third direction Y. Before clamping the tail structure, the position of the clamping component 2 can be adjusted to align with the tail structure for clamping. After clamping, it can be moved to the installation position and then fine-tuned by the second adjustment component 33 so that the tail structure can be aligned with the body for installation.

[0056] In other embodiments, the clamping assembly 2 may also include a position detection device, which can detect the position on the body for installation with the tail structure. After clamping the tail structure, the position of the clamping assembly 2 can be adjusted according to the detection result of the detection device to obtain a better installation effect.

[0057] like Figure 6 As shown, in one embodiment, the moving component 3 further includes a third platform 34 and a third adjustment component 35. The third adjustment component 35 is disposed on the third platform 34 and is connected to the second platform 32 for driving the second platform 32 to move along the first direction X.

[0058] In this embodiment, the moving component 3 does not have a second adjustment component 33, but has a third adjustment component 35, so that the moving component 3 can be configured in one form as needed. The third adjustment component 35 can be a motor, which can drive the second platform 32 to move with high precision along the first direction X, and no further restrictions are imposed here.

[0059] Understandably, the third adjustment component 35 and the first adjustment component 31 enable the moving component 3 to drive the clamping component 2 to move in the first direction X and the second direction Z, so that the moving component 3 can be used as a four-degree-of-freedom platform and can be set according to different scenarios.

[0060] In one embodiment, the moving component 3 further includes a fourth platform 36 and a fourth adjustment component 37. The fourth adjustment component 37 is disposed on the fourth platform 36 and is drively connected to the third platform 34 for driving the third platform 34 to move along the third direction Y.

[0061] In this embodiment, if the moving component 3 is not provided with the second adjustment component 33, a fourth adjustment component 37 is further provided so that the clamping component 2 can move along the third direction Y. The fourth adjustment component 37 can be a motor, which can drive the third platform 34 to move with high precision along the third direction Y. No further restrictions are imposed here.

[0062] In other embodiments, the moving component 3 does not have a third adjustment component 35, and a fourth adjustment component 37 is provided on the fourth platform 36. The fourth adjustment component 37 is connected to the second platform 32 and is used to drive the second platform 32 to move along the third direction Y.

[0063] It is understandable that the third adjustment component 35 and the third platform 34, as well as the fourth adjustment component 37 and the fourth platform 36, can be set up separately according to the usage scenario, so that the moving component 3 can be used as a four-degree-of-freedom platform, or all of them can be set up at the same time to obtain six-degree-of-freedom adjustment.

[0064] In one embodiment, a rotary component is connected to the fourth platform 36, which can drive the third platform 34 to rotate.

[0065] In this embodiment, the rotary assembly can be a motor or a crank-slider mechanism to drive the third platform 34 to rotate. Other mechanisms capable of driving the third platform 34 to rotate can also be used for the rotary assembly; no further restrictions are imposed here.

[0066] Understandably, the rotating component allows the clamping component 2 to be further rotated while being moved horizontally, increasing the adjustment range of the moving component 3 and enabling the clamping component 2 to be better adjusted, thus ensuring the accurate installation of the subsequent tail structure.

[0067] In other embodiments, the moving component 3 is provided with a rolling element 38, which is connected to the fourth platform 36 so that the rolling element 38 can drive the fourth platform 36 to move under the action of external force, thereby driving the other platforms and the clamping component 2 to move.

[0068] In one embodiment, the aircraft tail structure assembly device 100 further includes a host computer configured to control the moving component 3 to move the first platform 1.

[0069] In this embodiment, the host computer can employ an electronic control unit (ECU) and a human-machine interface, enabling the operator to control the moving component 3 to move the first platform 1 via the host computer. Similarly, the host computer can also be electrically connected to the clamping member 21 to control the movement of the clamping member 21 along the first direction X and the second direction Z, and can also control the rotation angle of the clamping part 211 relative to the adjusting part 212. The host computer can integrate preset position memory, and can also pre-set the path planning of the aircraft tail structure assembly device 100 in the host computer to further simplify the installation process.

[0070] Understandably, the host computer's settings enable automated operation, reduce manual intervention, lower labor intensity, and improve installation efficiency and safety.

[0071] When using, such as Figure 5 and Figure 6As shown, under external force, the moving component 3 can drive the clamping component 2 to move roughly to a position close to the tail structure via the rolling element 38. Then, the first adjusting component 31, the second adjusting component 33, or the third adjusting component 35 and the fourth adjusting component 37 in the moving component 3 are used for high-precision fine-tuning to clamp the tail structure. After clamping, the moving component 3 drives the clamping component 2 to move roughly to a position close to where the tail structure needs to be installed. Then, the first adjusting component 31 lifts the tail structure, and the second adjusting component 33, or the third adjusting component 35 and the fourth adjusting component 37 are used for high-precision fine-tuning to align the tail structure with the installation position on the machine body, achieving precise installation.

[0072] The specific embodiments of this application have been described above with reference to the accompanying drawings. However, those skilled in the art will understand that various changes and substitutions can be made to the specific embodiments of this application without departing from the spirit and scope of this application. All such changes and substitutions fall within the scope defined by this application.

Claims

1. An aircraft tail structure assembly apparatus for carrying and assembling a tail structure of an aircraft, characterized by, The aircraft tail structure assembling device comprises: a first platform; a clamping assembly arranged on the first platform, the clamping assembly comprising two clamping members arranged in a first direction and capable of clamping the tail structure, the clamping members being movable relative to the first platform in a second direction to adjust the height of the clamping members, the clamping members being rotatable relative to the first platform to adjust the posture of the clamping members, the second direction intersecting the first direction; a moving assembly capable of driving the first platform to move in space.

2. The aircraft aft structure assembly apparatus of Claim 1, wherein, The clamping members comprise clamping portions and adjusting portions, the clamping portions being rotatably connected to the adjusting portions, the adjusting portions being movably connected to the first platform in the second direction.

3. The aircraft aft structure assembly apparatus of Claim 2, wherein, The clamping portions are provided with clamping surfaces configured to abut against the tail structure, the clamping surfaces being provided with friction-increasing members configured to increase the friction between the tail structure and the clamping surfaces.

4. The aircraft aft structure assembly apparatus of Claim 3, wherein, In the first direction, the clamping surfaces of the two clamping members abut against two sides of the tail structure respectively, and the clamping surfaces of the two clamping members are arranged obliquely to each other.

5. The aircraft aft structure assembly apparatus of Claim 3, wherein, The friction-increasing members are made of soft material.

6. The aircraft aft structure assembly apparatus of Claim 3, wherein, The clamping surfaces are provided with pressure detection devices.

7. The aircraft aft structure assembly apparatus of Claim 1, wherein, The clamping members are provided with quick release mechanisms.

8. The aircraft aft structure assembly apparatus of Claim 1, wherein, The aircraft tail structure assembling device further comprises a host computer configured to control the moving assembly to drive the first platform to move.

9. The aircraft aft structure assembly apparatus of any of claims 1-8, wherein, The clamping assembly further comprises support members arranged in a third direction on one side of the clamping members, the support members being capable of supporting the tail structure, the third direction intersecting the first direction and the second direction.

10. The aircraft aft structure assembly apparatus of Claim 9, wherein, The support members are telescopic structures, and the height of the support members can be adjusted in the second direction.

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