Lifting appliance

Abstract

The utility model provides a lifting appliance for disassembling and assembling a horizontal stabilizer trim actuator (HSTA) of an airplane, the lifting appliance is arranged on a skin of an airplane body, the lifting appliance comprises an outer cross beam assembly, an upper frame beam assembly, an L-shaped turning beam assembly and a lifting assembly for lifting the HSTA, the outer cross beam assembly is detachably fixed on the skin and is positioned right above a maintenance cabin door, and the upper frame beam assembly is detachably fixed on the upper frame beam assembly. The upper frame beam assembly is arranged on the skin located at the maintenance opening, the turning beam assembly is constructed to be capable of connecting the outer cross beam assembly and the upper frame beam assembly, and the hoisting assembly is constructed to be capable of moving on the turning beam assembly so as to be capable of moving between the outer cross beam assembly and the upper frame beam assembly.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft assembly, in particular to a sling. Background Art

[0002] The aircraft horizontal stabilizer trim actuator (HSTA) is not only an important part of the flight control system, but also an important device to ensure the safe flight of the aircraft. At present, when performing HSTA installation or disassembly maintenance tasks, the HSTA needs to be moved from the outside of the fuselage through the aircraft maintenance door to the installation position inside the cabin, or it needs to be moved away from the installation position and moved outside the aircraft cabin. Since the HSTA itself has a certain weight and the environment inside the fuselage cabin where it is installed is relatively complex, it is difficult for maintenance personnel to directly operate the HSTA to complete the disassembly and assembly tasks, and they often need to use certain lifting equipment to assist maintenance personnel in completing the disassembly and assembly of the HSTA.

[0003] like Figure 1 As shown, the existing sling 2000 for disassembling and assembling the aircraft HSTA is an integral frame beam structure. Due to the limitations of the cabin structure and the installation position, it is not convenient to install on the fuselage, and the lifting point after installation is in the aircraft cabin and deviates from the maintenance door. Therefore, when using the sling, maintenance personnel still need to first support the HSTA to fully enter the cabin, and then move the HSTA to the lifting point position, and then use the sling normally to lift the HSTA through the hand winch 2230, which is cumbersome and inefficient. Moreover, since the lifting point is not only not at the center of the maintenance door, but also close to the frame of the maintenance door, the HSTA is easily bumped against the maintenance door and its frame during the lifting process, causing damage to the HSTA or the maintenance door and its frame.

[0004] At the same time, if Figure 1 As shown, in order to make the lifting point close to the center of the maintenance door, the movable slide rail 2200 on the existing lifting device adopts the form of connecting the cantilever 2220 with the slide rails 2210 and 2240, and the movement reliability of the HSTA during the lifting process is poor. Moreover, the entire lifting device only relies on the friction between the bottom surface of the lifting device and the aircraft structure to support the movement of the HSTA in two directions and a long path, which makes the entire HSTA lifting process poorly stable and has potential safety hazards. Utility Model Content

[0005] Therefore, the technical problem to be solved by the utility model is to overcome the problem that the lifting point of the existing lifting device deviates from the maintenance door and the lifting movement process is unstable, and a new lifting device is proposed.

[0006] The utility model solves the above technical problems through the following technical solutions:

[0007] Specifically, the utility model provides a lifting device for disassembling and assembling an aircraft horizontal stabilizer trim actuator (HSTA), the lifting device being installed on the skin of the aircraft fuselage, and the characteristic of the lifting device is that the lifting device comprises:

[0008] an outer crossbeam assembly, the outer crossbeam assembly being detachably fixed to the skin and being located directly above the maintenance hatch;

[0009] an upper frame beam assembly mounted on the skin located at the maintenance opening;

[0010] An L-shaped turning beam assembly configured to connect the outer cross beam assembly and the upper frame beam assembly; and

[0011] A lifting assembly for lifting the HSTA is configured to be movable on the turning beam assembly, thereby being movable between the outer cross beam assembly and the upper frame beam assembly.

[0012] The utility model provides a lifting device for disassembling and assembling an aircraft HSTA. The lifting device is installed by using an outer crossbeam assembly structure and the outer crossbeam assembly is arranged above the maintenance cabin door. The installation of the lifting device can be simplified, and the HSTA does not need to be carried into the aircraft cabin for lifting, which can reduce the need for manual handling and effectively avoid the collision between the HSTA and the maintenance cabin door and the cabin structure. In addition, by arranging the outer crossbeam assembly just above the maintenance cabin door, the lifting can be carried out at the maintenance cabin door, thereby avoiding the collision between the HSTA and the maintenance cabin door during the lifting process.

[0013] In addition, the sling connects the outer cross beam assembly at the lifting point and the upper frame beam assembly near the HSTA installation position through the turning beam assembly, which can form a stable sling structure. Moreover, by making the lifting assembly move on the turning beam assembly between the outer cross beam assembly and the upper frame beam assembly, the suspension structure of a single support point is avoided, so that the stability of the HSTA lifting movement can be ensured, so that the HSTA is always in a safe and stable state during the lifting process, and the HSTA will not tip over during the lifting movement, thereby avoiding the occurrence of potential dangerous situations.

[0014] According to an embodiment of the utility model, the turning beam assembly is formed with an inner cavity extending along its extension direction and having a closed cross-section, and the inner cavity is configured to receive a pulley of the lifting assembly and enable the pulley to move on the bottom wall of the inner cavity.

[0015] According to an embodiment of the utility model, an L-shaped slot extending along the extension direction of the turning beam assembly is formed on the bottom wall, and the pulley connector connected to the pulley intermediate shaft is configured to pass through the L-shaped slot and extend out of the inner cavity and move along the L-shaped slot, so that the pulley can move along the L-shaped slot. Through the inner cavity and the L-shaped slot of the turning beam assembly, the pulley and the pulley connector can complete the installation of the hoisting assembly on the turning beam assembly, and the movement of the hoisting assembly between the outer cross beam assembly and the upper frame beam assembly.

[0016] According to one embodiment of the utility model, an open opening portion is formed at the end of the turning beam assembly connected to the upper frame beam assembly, and an L-shaped narrow groove is connected to the opening portion, so that the pulley and the pulley connecting member can be installed into or removed from the inner cavity of the turning beam assembly through the opening portion.

[0017] According to an embodiment of the present invention, the sling further comprises a square block, which is configured to be fixed to the end of the turning beam assembly connected to the upper frame beam assembly by a fastener to close the opening.

[0018] By designing the opening at the end of the turning beam assembly to be open and the L-shaped slot to be connected to the opening, the end of the turning beam assembly where the opening and the L-shaped slot are connected to each other can also be connected to the external environment, so that the pulley and the pulley connector used for lifting can be moved from the external environment to the inner cavity of the turning beam assembly through the opening and the L-shaped slot, respectively, so as to install the lifting assembly on the turning beam assembly and allow the pulley to move in the inner cavity. After the installation is completed, the opening can be closed by a square block to prevent the pulley from accidentally sliding out of the inner cavity of the turning beam assembly.

[0019] When necessary, the square block can also be removed from the end of the turning beam assembly so that the pulley and the pulley connector can be removed from the inner cavity of the turning beam assembly for subsequent repair and maintenance.

[0020] According to an embodiment of the utility model, a stopper is provided at a predetermined position on the inner cavity side wall of the turning beam assembly for blocking the movement of the pulley. By blocking the movement of the pulley in the inner cavity by the stopper, on the one hand, it can ensure that the pulley moves in the inner cavity according to the desired trajectory, and on the other hand, it can ensure that the pulley is positioned at the stopper position when it is idle, in the vertical lifting position or when it reaches the installation position in the cabin instead of moving randomly.

[0021] According to one embodiment of the utility model, the lifting assembly further comprises a hand chain hoist connected to the HSTA, and a free end of the pulley connector extending from the L-shaped slot is formed with a connecting hole allowing a hook of the hand chain hoist to pass through.

[0022] According to one embodiment of the utility model, the outer cross beam assembly is provided with two L-shaped connectors at the middle position on the outer wall surface close to the turning beam assembly, and the two L-shaped connectors are constructed to be able to clamp the end of the turning beam assembly connected to the outer cross beam assembly through legs that are parallel to each other and extend in a direction away from the outer cross beam assembly, so as to realize the connection between the outer cross beam assembly and the turning beam assembly.

[0023] According to an embodiment of the utility model, a gap is formed between the end of the turning beam assembly connected to the outer cross beam assembly and the outer wall surface of the outer cross beam assembly.

[0024] According to an embodiment of the present invention, the left and right ends of the outer crossbeam assembly are respectively mounted on two beams above the maintenance hatch and on both sides of the maintenance hatch along the transverse direction of the fuselage skin.

[0025] According to one embodiment of the utility model, both ends of the outer cross beam assembly are respectively provided with end blocks whose shapes match the cavity shapes of the beam, so that the outer cross beam assembly can be installed on the beam through the close fit between the end blocks and the corresponding cavity of the beam.

[0026] According to an embodiment of the present invention, the outer beam assembly includes an outer beam extending along an extension direction of the outer beam assembly and an inner beam arranged in a cavity of the outer beam and capable of extending out of the cavity or retracting along the extension direction.

[0027] According to one embodiment of the utility model, the upper frame beam assembly includes a rectangular frame beam and a cross beam connecting the two long sides of the frame beam, and the cross beam is provided with a single-ear mounting seat at the middle position on the surface of the cross beam away from the skin for connecting to the connecting seat on the turning beam assembly and connected to the upper frame beam assembly.

[0028] According to one embodiment of the utility model, a through hole with a joint bearing is arranged at the center of a single ear of a single ear mounting seat, the connecting seat has two first ear portions extending parallel to each other in a direction toward the crossbeam, a through hole is arranged at the center of each first ear portion, and the single ear mounting seat is configured to be clamped between the two first ear portions and fixed to the connecting seat by fasteners passing through the through hole on the single ear mounting seat and the through holes on the two first ear portions.

[0029] According to an embodiment of the utility model, the center of the upper frame beam assembly is aligned with the center of the maintenance opening.

[0030] On the basis of conforming to the common sense in the art, the above-mentioned preferred implementation modes can be arbitrarily combined to obtain the preferred implementation modes of the present utility model.

[0031] The positive and progressive effects of the above-mentioned embodiments of the present invention are:

[0032] 1. The components of the lifting device have a simple structure, and the components can form a stable structure, which is easy to install and use. In addition, the lifting device can realize the lifting point at the center of the maintenance hatch, so that the HSTA can be lifted vertically from the maintenance hatch without collision with the maintenance hatch;

[0033] 2. The hoist is installed by using an outer crossbeam assembly structure and arranging the outer crossbeam assembly above the maintenance hatch, which simplifies the installation of the hoist and eliminates the need to carry the HSTA into the aircraft cabin for lifting, thereby reducing the need for manual handling and effectively avoiding collision between the HSTA and the maintenance hatch and the cabin structure.

[0034] 3. The lifting device connects the outer cross beam assembly at the lifting point and the upper frame beam assembly near the HSTA installation position through the turning beam assembly, thereby forming a stable lifting device structure. In addition, by making the lifting assembly move on the turning beam assembly between the outer cross beam assembly and the upper frame beam assembly, the suspension structure with a single support point is avoided, thereby ensuring the stability of the HSTA lifting movement;

[0035] 4. During the process of lifting and moving to the final position, HSTA is always in a safe and stable state, and will not tip over during the lifting and moving process, thus avoiding potential dangerous situations. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Figure 1 The following schematically shows a sling for disassembling and assembling an aircraft HSTA according to the prior art.

[0037] Figure 2 The utility model schematically shows a lifting device for disassembling and assembling an aircraft HSTA according to a preferred embodiment of the utility model.

[0038] Figure 3 Schematically shows Figure 2 The turning beam components in

[0039] Figure 4 Schematically shows Figure 2 A cross-sectional view of a turning beam assembly with pulleys and pulley connections in FIG.

[0040] Figure 5 Schematically shows Figure 2 The outer crossbeam assembly in

[0041] Figure 6 Schematically shows Figure 2 The upper frame beam assembly in. DETAILED DESCRIPTION

[0042] In order to make the purpose, technical solutions and advantages of the present application clearer, the technical solutions in the implementation mode of the present application will be clearly and completely described below in conjunction with the accompanying drawings showing multiple embodiments according to the present application. It should be understood that all other embodiments obtained by ordinary technicians in this field without spending creative work based on the embodiments recorded in the present application will fall within the scope of protection of the present application.

[0043] Unless otherwise defined, all technical and scientific terms used in this application have the same meanings as those generally understood by those skilled in the art to which this application belongs; the terms "including" and the like in the specification and claims of this application and the above-mentioned description of the drawings are open-ended terms. Moreover, it should be noted that the orientations or positional relationships indicated by the terms "top", "bottom", "upper", "lower", "inner", "outer" and "extension direction" are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and cannot be understood as limitations on the present invention.

[0044] like Figures 2 to 6 As shown, the utility model provides a lifting device for disassembling and assembling an aircraft horizontal stabilizer trim actuator (HSTA), which is installed on the skin of the aircraft fuselage, and includes an outer crossbeam assembly 1, a turning beam assembly 2, an upper frame beam assembly 3 and a lifting assembly 4. Among them, the outer crossbeam assembly 1 is detachably fixed on the skin and is located directly above the maintenance hatch, the upper frame beam assembly 3 is installed on the skin located at the maintenance port, the turning beam assembly 2 is arranged between the outer crossbeam assembly 1 and the upper frame beam assembly 3, and connects the outer crossbeam assembly 1 and the upper frame beam assembly 3. The lifting assembly 4 is arranged on the turning beam assembly 2 and can move along the turning beam assembly 2, so that the HSTA lifted by it can be lifted and moved between the outer crossbeam assembly 1 and the upper frame beam assembly 3.

[0045] It should be understood that the fuselage of the aircraft on which the HSTA is installed is a hollow closed cylindrical structure, and a maintenance hatch is installed on its bottom skin, through which aircraft parts, maintenance equipment or maintenance tools can be transported to the aircraft fuselage cabin. The HSTA can be vertically lifted from the bottom of the maintenance hatch and then enter the interior of the aircraft cabin through the maintenance hatch. A maintenance port is provided at the top skin of the aircraft fuselage, which deviates from the bottom maintenance hatch, and a vertical tail with a cavity structure is installed above the maintenance port. Through this maintenance port, maintenance and other related work can be performed on the upper vertical tail. The installation position of the HSTA is located in the cabin at the bottom of one side of the maintenance hatch, and deviates from the maintenance hatch in the vertical direction. Therefore, even if the HSTA is lifted vertically at the maintenance hatch and enters the fuselage cabin, it still needs to pass through a certain path to reach its installation device. Exemplarily, the maintenance port is usually in the shape of a circular opening.

[0046] The lifting device for disassembling and assembling an aircraft HSTA provided by the utility model is installed by using an outer cross beam assembly 1 and an upper frame beam assembly 3 to install the lifting device, and the outer cross beam assembly 1 is arranged above the maintenance door, so that the lifting can be performed at the maintenance door. Moreover, the lifting assembly 4 can be moved from the lifting point position to the installation position through the turning beam assembly 2 connecting the outer cross beam assembly 1 and the upper frame beam assembly 3, so as to facilitate the subsequent installation of the HSTA.

[0047] Specifically, Figure 3 and 4 As shown, the turning beam assembly 2 is formed with an inner cavity 21 extending along its extension direction and having a closed cross section, and the inner cavity 21 can receive the pulley 41 of the hoisting assembly 4. An L-shaped slot 22 extending along the extension direction of the turning beam assembly 2 is formed on the bottom wall of the inner cavity 21, and a pulley connector 42 connected to the intermediate shaft of the pulley 41 passes through the L-shaped slot 22 and moves along the L-shaped slot 22, so that the pulley 41 can move on the bottom wall along the L-shaped slot 22. Through the inner cavity 21 and the L-shaped slot 22 of the turning beam assembly 2, the pulley 41 and the pulley connector 42 can complete the installation of the hoisting assembly 4 on the turning beam assembly 2, and the movement of the hoisting assembly 4 between the outer cross beam assembly 1 and the upper frame beam assembly 3.

[0048] It should be understood that Figure 4 In order to show the inner cavity 21 and the narrow groove 22 and other components, one side wall of the turning beam assembly 2 is cut away or hidden, and the cross section of the inner cavity 21 is not closed.

[0049] For example, the turning beam assembly 2 is a square steel pipe with a groove at the bottom, and the cavity in the square steel pipe is equipped with a pulley 41. The overall shape of the square steel pipe is L-shaped, and the two ends of the L-shaped square steel pipe can be welded or installed with sealing plates to close the cavity as needed. The L-shaped structure can be formed by welding plates or bending square steel pipes.

[0050] Alternatively, an open opening portion 23 is formed at the end of the turning beam assembly 2 connected to the upper frame beam assembly 3, and the L-shaped slot 22 is connected to the opening portion 23, so that the pulley 41 and the pulley connector 42 can be installed in or removed from the inner cavity 21 of the turning beam assembly 2 through the opening portion 23.

[0051] By designing the opening portion 23 at the end of the turning beam assembly 2 to be open and making the L-shaped slot 22 connected to the opening portion 23, the end of the opening portion 23 of the turning beam assembly 2 connected to the L-shaped slot 22 can be connected to the external environment, thereby facilitating moving the pulley 41 and the pulley connector 42 for the lifting assembly 4 from the external environment to the inner cavity 21 of the turning beam assembly 2 via the opening portion 23 and the L-shaped slot 22 respectively, so as to install the lifting assembly 4 on the turning beam assembly 2 and allow the pulley 41 to move in the inner cavity 21.

[0052] The sling may further include a square block 24, which is configured to be fixed to the end of the turning beam assembly 2 connected to the upper frame beam assembly 3 by fasteners to close the opening 23. Therefore, after installation, the opening 23 can be closed by the square block 24 to prevent the pulley 41 from accidentally sliding out of the inner cavity 21 of the turning beam assembly 2. When necessary, the square block 24 can also be removed from the end of the turning beam assembly 2 so that the pulley 41 and the pulley connector 42 can be removed from the inner cavity 21 of the turning beam assembly 2 for subsequent repair and maintenance.

[0053] Preferably, if Figure 4 As shown, the square block 24 is in the shape of a block with a baffle on one side, wherein a through hole is provided on the block, and the square block 24 can be fixed to the end of the turning beam assembly 2 by a quick release pin, and the baffle can block and close the opening 23. After the quick release pin is removed, the square block 24 can be removed, so that the pulley 41 and the pulley connector 42 can be removed through the opening 23 of the turning beam assembly 2 for repair and maintenance.

[0054] In order to facilitate the control of the movement of the pulley 41 in the inner cavity 21, preferably, two L-shaped pulley moving tracks symmetrically distributed with the L-shaped narrow groove 22 as the symmetry axis are also provided on the bottom wall of the inner cavity 21 of the turning beam assembly 2, and the positions of the two L-shaped pulley moving tracks correspond to the positions of the pulley 41, so as to guide the movement of the pulley 41 in the inner cavity 21.

[0055] Alternatively, a stopper 26 for blocking the movement of the pulley 41 is further provided at a predetermined position on the side wall of the inner cavity 21 of the turning beam assembly 2. By blocking the movement of the pulley 41 in the inner cavity 21 by the stopper 26, on the one hand, it can ensure that the pulley 41 moves in the inner cavity 21 according to the desired trajectory, and on the other hand, it can ensure that the pulley 41 is positioned at the stopper 26 when it is idle, vertically hoisted, or reaches the installation position in the cabin instead of moving randomly. For example, Figure 4 As shown, a through hole is provided at a predetermined position on the side wall of the inner cavity 21 of the turning beam assembly 2, and the stopper 26 is a component such as a pin that can be detachably inserted into the through hole on the side wall of the inner cavity 21, and the part of the stopper 26 in the inner cavity 21 forms a barrier to the movement of the pulley 41.

[0056] In the connection between the turning beam assembly 2 and the lifting assembly 4, exemplarily, a connecting hole allowing a hook of a hand winch 43 to pass through is formed at the free end of the pulley connector 42 on the pulley 41 installed in the inner cavity 21 of the turning beam assembly 2, and the hand winch 43 connected to the HSTA is connected to the pulley 41 through the connecting hole 421 of the pulley connector 42, thereby forming a lifting assembly 4 together with the pulley 41 and the pulley connector 42, and then moving on the turning beam assembly 2.

[0057] Specifically, the specific structure of the lifting assembly 4 is as follows: Figure 2 and 4 As shown, a lifting belt 44 is hung by a hook at the free end of a hand chain hoist 43 connected to a pulley connector 42, and the lifting belt 44 is connected to two special eye bolts 45 of the HSTA, and the two special eye bolts 45 are installed at the specified positions of the HSTA to achieve the installation of the HSTA on the lifting assembly 4. Optionally, a binding belt 46 can be used to wrap the two lifting belts 44 to prevent the HSTA from rotating during the lifting and moving process.

[0058] In the connection between the turning beam assembly 2 and the outer cross beam assembly 1, as shown in FIG. Figure 2 As shown, the outer cross beam assembly 1 is connected to the turning beam assembly 2 through two L-shaped connectors 12 located at the middle of the outer wall surface of the outer cross beam assembly 2. The two L-shaped connectors 12 have a bent plate configuration, and can clamp the turning beam assembly 2 through legs 121 that are parallel to each other and extend in a direction away from the outer cross beam assembly 1, so as to achieve the connection between the outer cross beam assembly 1 and the turning beam assembly 2. Preferably, a gap is formed between the end of the turning beam assembly 2 connected to the outer cross beam assembly 1 and the outer wall surface of the outer cross beam assembly 1, so as to ensure that the turning beam assembly 2 and the outer cross beam assembly 1 can be finely adjusted up and down during the assembly process.

[0059] The specific structure of the outer beam assembly 1 is as follows: Figure 2 and 5 As shown, it specifically includes an outer crossbeam 13 extending along the extension direction of the outer crossbeam assembly 1 and an inner crossbeam 14 arranged in the cavity of the outer crossbeam 13 and capable of being telescopically extended along the extension direction. End blocks 15 are also provided at the free ends of the outer crossbeam 13 and the inner crossbeam 14, respectively. At the same time, the skin of the aircraft fuselage has two beams (not shown) arranged on both sides of the maintenance door along the transverse direction of the fuselage, respectively, above the maintenance door, and the shape of the end block 15 is designed to match the shape of the cavity of the beam, so that the left and right ends of the outer crossbeam assembly 1 can be installed on the beam through the close fit of the end block 15 and the cavity of the corresponding beam. Preferably, the two beams are arranged symmetrically above the maintenance door and with the center line of the maintenance door along the transverse direction of the fuselage as the symmetry axis.

[0060] For example, Figure 5As shown, the outer crossbeam 13 and the inner crossbeam 14 of the outer crossbeam assembly 1 have square steel tube structures, wherein the width of the inner crossbeam 14 is smaller than that of the outer crossbeam 13, so that the inner crossbeam 14 can be arranged in the cavity of the square steel tube of the outer crossbeam 13. In addition, a plurality of holes are provided on the opposite sides of the outer crossbeam 13 and the inner crossbeam 14, and the position of the inner crossbeam 14 can be positioned by pins passing through the holes on the outer crossbeam 13 and the inner crossbeam 14 at the same time, thereby determining the protruding length of the inner crossbeam 14 relative to the outer crossbeam 13, and further determining the overall length of the outer crossbeam assembly 1. By making the determined overall length of the outer crossbeam assembly 1 match the distance between the two beams above the maintenance hatch, it is ensured that the outer crossbeam assembly 1 can be installed on the two beams on the maintenance hatch.

[0061] Optionally, the pins are replaced with bolts to position the inner cross beam 14. In addition, nuts are welded at the through-hole positions on the outer wall of the outer cross beam 13. After the length adjustment of the outer cross beam assembly 1 is completed, the inner cross beam 14 and the outer cross beam 13 can be put in a compressed state by passing through the above-mentioned nuts and the butterfly bolts on the outer cross beam 13 and the inner cross beam 14 corresponding to the nuts, thereby ensuring that there will be no undesired relative movement between the inner and outer cross beams along the length direction of the outer cross beam. Preferably, the outer cross beam assembly 1 and the turning beam assembly 2 are both provided with components for receiving quick-release pins, dowels or bolts in an idle state, and these components receive fasteners or connectors such as pins through the through-holes thereon.

[0062] Exemplarily, the end block 15 is made of a rigid material and is fixed to the free ends of the outer cross beam 13 and the inner cross beam 14 by welding. Preferably, other sides of the end block 15 are also mounted with fixing seats made of soft materials such as nylon by screws or the like to reduce the wear and loss of the end block 15 and prevent the end block 15 from causing wear to the fuselage beam. To improve the reliability of the connection between the end block 15 and the inner cross beam 14 and the outer cross beam 13, exemplarily, the end block 15 is welded to the free ends of the inner cross beam 14 and the outer cross beam 13 via a sealing plate with a larger area.

[0063] Moreover, in order to enhance the reliability of the connection between the outer cross beam assembly 1 and the turning beam assembly 2, alternatively, an auxiliary cross beam 16 is welded on the bottom lower surface of the outer cross beam 13, so that each L-shaped connector 12 is welded to both the outer cross beam 13 and the auxiliary cross beam 16. Exemplarily, the L-shaped connector 12 is made of a rigid material and has a bent plate structure. The legs 121 of each L-shaped connector 12 extending away from the outer cross beam assembly 1 cooperate with each other to clamp the end of the turning beam assembly 2, and each leg 121 and the end of the turning beam assembly 2 are provided with through holes, so that the end of the turning beam assembly 2 can be fixed by a fastener passing through the through hole, thereby fixing one end of the turning beam assembly 2 to the beam above the maintenance hatch, so that the lifting position is located directly above the maintenance hatch.

[0064] In the connection between the turning beam assembly 2 and the upper frame beam assembly 3, as shown in FIG. Figure 2 and 6 As shown, the upper frame beam assembly 3 includes a rectangular frame beam 31 and a cross beam 32 connecting the two long sides of the frame beam 31. The cross beam 32 is provided with a single-ear mounting seat 33 for connecting the connecting seat 25 on the turning beam assembly 2 at a middle position away from the skin surface. A through hole 332 with a joint bearing is provided in the center of the single ear 331 of the single-ear mounting seat 33. The connecting seat 25 is provided at one end where the turning beam assembly 2 is connected to the upper frame beam assembly 3, and has two first ear portions 251 extending in parallel to each other in a direction toward the cross beam 32. A through hole 252 is provided in the center of the first ear portion 251, so that the turning beam assembly 2 can be connected to the upper frame beam assembly 3 by a fastener passing through the aforementioned through hole.

[0065] Exemplarily, the upper frame beam assembly 3 is a rectangular frame formed by welding square steel pipes, and a crossbeam is arranged in the middle of the rectangular frame. The frame beam 31, the crossbeam 32 and the single-ear mounting seat 33 are all fixed by welding. Moreover, a avoidance opening is formed on the short side of the rectangular frame beam 31 along the direction of the aircraft head, so as to avoid the pipelines in the cabin during installation. Preferably, the inner surface and the bottom surface of the frame beam 31 are also bonded with soft materials such as rubber sheets or nylon to increase the friction between the upper frame beam assembly 3 and the aircraft skin, and to prevent the upper frame beam assembly 3 from wearing the aircraft skin surface during installation and use. Preferably, the center of the upper frame beam assembly 3 is aligned with the center of the maintenance port.

[0066] In general, the lifting device for disassembling and assembling HSTA provided by the utility model adopts a split structure, and the structure of each component is simple and easy to install. When the HSTA is hoisted, it can ensure that the lifting point is at the center of the maintenance hatch, so that the HSTA can be lifted vertically from the maintenance hatch to avoid collision with the maintenance hatch and its surrounding frames. The upper frame beam assembly 3 and the outer cross beam assembly 1 are respectively installed at the end point and the starting point, and the turning beam assembly 2 is installed between the above two beams, so that the three can form a stable structure, so that the HSTA is in a safe and stable state during the lifting, moving process and the end position, and potential dangerous situations such as tipping will not occur.

[0067] In addition, the sling can form a stable sling structure by connecting the outer cross beam assembly 1 at the lifting point position and the upper frame beam assembly 3 near the HSTA installation position through the turning beam assembly 2. Moreover, by making the hoisting assembly 4 move on the turning beam assembly 2 between the outer cross beam assembly 1 and the upper frame beam assembly 3, a single-support-point suspension structure is avoided, thereby ensuring the stability of the HSTA lifting movement, so that the HSTA is always in a safe and stable state during the lifting process, and the HSTA will not tip over during the lifting movement, thereby avoiding the occurrence of potential dangerous situations.

[0068] The use process of the spreader may include installing the upper frame assembly 3 and the outer beam assembly 1, connecting the upper frame assembly 3 and the outer beam assembly 1 using the turning beam assembly 2, and installing the hand chain hoist 43 to connect the HSTA.

[0069] The process of installing the upper frame assembly 3 and the outer beam assembly 1 includes: firstly, the upper frame beam assembly 3 is moved into the cabin through the maintenance hatch on the bottom skin of the fuselage, and is placed on the outer surface of the skin at the top of the maintenance hatch through the maintenance hatch, and the placement position of the frame beam 31 is roughly located at the central symmetrical position of the maintenance hatch, and the direction of the avoidance hatch is facing the front of the aircraft; the outer beam assembly 1 is adjusted to the shortest distance, and the quick release pin is inserted, and the outer beam assembly 1 is moved into the cabin to be placed on the fuselage beam position vertically upward from the center of the maintenance hatch, and then the outer beam assembly 1 is adjusted to the maximum distance, and a quick release pin and a butterfly nut passing through the nut on the outer beam are inserted to fix the position of the outer beam assembly 1. It should be understood that the installation process of the upper frame assembly 3 and the outer beam assembly 1 can be carried out simultaneously or successively, and there is no limitation here.

[0070] The process of connecting the upper frame assembly 3 and the outer cross beam assembly 1 using the turning beam assembly 2 includes: installing the connecting seat 25 at one end of the turning beam assembly 2 on the single ear mounting seat 33 of the upper frame beam assembly 3, and inserting the pin assembly to fix it; then arranging the end of the other end of the turning beam assembly 2 between the legs 121 of the two L-shaped connecting members 12 of the outer cross beam assembly 1, and installing the pin assembly to fix it; fine-tuning the position between the turning beam assembly 2 and the outer cross beam assembly 1 and the upper frame beam assembly 3 as needed, thereby completing the installation of the sling on the aircraft fuselage.

[0071] After the lifting equipment is installed and fixed, the process of installing the hand winch 43 includes: installing the hand winch 43 on the connecting hole of the pulley connector 42 on the turning beam assembly 2, installing the two eye bolts 45 to the specified position of the HSTA, and then using the lifting belt 44 to connect the eye bolts 45 and the hooks of the hand winch 43 respectively, and wrapping the two lifting belts 44 with the straps 46 to prevent rotation during the HSTA lifting process.

[0072] By using the slings in the above embodiments and installing the slings on the skin of the aircraft fuselage according to the above scheme, the problems of the existing slings for disassembling and assembling HSTA being inconvenient to install, unable to vertically lift from the maintenance hatch, and unstable during the lifting and moving process can be solved. Moreover, the sling provided by the utility model is structurally optimized relative to the existing slings. The optimized sling is not only very convenient to install and use, but also can vertically lift the HSTA at the center of the maintenance hatch, while also ensuring the stability of the sling during movement.

[0073] Although the specific embodiments of the present invention are described above, those skilled in the art should understand that these are only examples, and the protection scope of the present invention is defined by the appended claims. Those skilled in the art may make various changes or modifications to these embodiments without departing from the principle and essence of the present invention, but these changes and modifications fall within the protection scope of the present invention.

Claims

1. A sling, used for disassembling and assembling an aircraft horizontal stabilizer trim actuator (HSTA), the sling being mounted on the skin of an aircraft fuselage, characterized in that: The sling comprises: an outer crossbeam assembly, the outer crossbeam assembly being detachably fixed to the skin and being located directly above the maintenance hatch; an upper frame beam assembly mounted on the skin at the maintenance opening; an L-shaped turning beam assembly configured to connect the outer cross beam assembly and the upper frame beam assembly; and A hoisting assembly for hoisting the HSTA is configured to be movable on the turning beam assembly so as to be movable between the outer cross beam assembly and the upper frame beam assembly.

2. The sling according to claim 1, characterized in that: The turning beam assembly is formed with an inner cavity extending along its extension direction and having a closed cross section. The inner cavity is configured to receive a pulley of the hoisting assembly and enable the pulley to move on the bottom wall of the inner cavity.

3. The sling according to claim 2, characterized in that: An L-shaped slot extending along the extension direction of the turning beam assembly is formed on the bottom wall, and the pulley connecting member on the intermediate shaft connected to the pulley is configured to pass through the L-shaped slot, extend out of the inner cavity and move along the L-shaped slot, so that the pulley can move along the L-shaped slot.

4. The sling according to claim 3, characterized in that: An open opening is formed at the end of the turning beam assembly connected to the upper frame beam assembly, and the L-shaped slot is connected to the opening, so that the pulley and the pulley connector can be installed into or removed from the inner cavity of the turning beam assembly through the opening.

5. The sling according to claim 4, characterized in that: The hanger further includes a square block, which is configured to be fixed to an end portion of the turning beam assembly connected to the upper frame beam assembly by a fastener to close the opening portion.

6. The sling according to claim 2, characterized in that: A stopper for blocking the movement of the pulley is provided at a predetermined position on the side wall of the inner cavity of the turning beam assembly.

7. The sling according to claim 3, characterized in that: The lifting assembly further comprises a hand chain hoist connected to the HSTA, and a free end of the pulley connector extending from the L-shaped slot is formed with a connecting hole allowing a hook of the hand chain hoist to pass through.

8. The sling according to claim 1, characterized in that: The outer cross beam assembly is provided with two L-shaped connectors at a middle position on the outer wall surface close to the turning beam assembly. The two L-shaped connectors are constructed to be able to clamp the end of the turning beam assembly connected to the outer cross beam assembly through legs that are parallel to each other and extend in a direction away from the outer cross beam assembly, so as to achieve the connection between the outer cross beam assembly and the turning beam assembly.

9. The sling according to claim 8, characterized in that: A gap is formed between the end of the turning beam assembly connected to the outer cross beam assembly and the outer wall surface of the outer cross beam assembly.

10. The sling according to claim 1, characterized in that: The left and right ends of the outer crossbeam assembly are respectively mounted on two beams above the maintenance hatch and on both sides of the maintenance hatch along the transverse direction of the fuselage skin.

11. The sling according to claim 10, characterized in that: Both ends of the outer cross beam assembly are respectively provided with end blocks whose shapes match the shapes of the cavities of the beams, so that the outer cross beam assembly can be installed on the beams through the close fit between the end blocks and the cavities of the corresponding beams.

12. The sling according to claim 11, characterized in that: The outer beam assembly includes an outer beam extending along an extending direction of the outer beam assembly and an inner beam arranged in a cavity of the outer beam and capable of extending out of the cavity or retracting along the extending direction.

13. The sling according to claim 1, characterized in that: The upper frame beam assembly includes a rectangular frame beam and a cross beam connecting two long sides of the frame beam. The cross beam is provided with a single-ear mounting seat at a middle position on a surface away from the skin for connecting to a connecting seat on the turning beam assembly and connected to the upper frame beam assembly.

14. The sling according to claim 13, characterized in that: A through hole with a spherical bearing is arranged at the center of the single-ear mounting seat, the connecting seat has two first ears extending parallel to each other in the direction toward the crossbeam, a through hole is arranged at the center of each of the first ears, and the single-ear mounting seat is configured to be clamped between the two first ears and fixed to the connecting seat by a fastener passing through the through hole on the single-ear mounting seat and the through holes on the two first ears.

15. The sling according to any one of claims 1 to 14, characterized in that: The center of the upper frame beam assembly is aligned with the center of the maintenance opening.

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