support device

Abstract

The utility model provides a kind of supporting device, it is related to aviation manufacturing technical field.Supporting device includes multiple relatively independent support mechanism, for supporting aircraft large skin, each support mechanism includes support frame, support backing plate, first adjusting assembly and second adjusting assembly: support backing plate is provided with the support portion compatible with aircraft large skin;First adjusting assembly is provided with two groups, two groups first adjusting assembly are spaced apart along the length direction and set in the upper end of support frame, the two ends of support backing plate are respectively connected in two groups first adjusting assembly, and two groups first adjusting assembly can drive support backing plate to lift along evenly;Second adjusting assembly is connected in the lower end of support frame, and can drive support frame to lift.The supporting device is convenient to shield operation to large skin, reduce labor intensity, and reduce the risk of deformation of large skin in shielding operation process.

Description

Technical Field

[0001] This utility model relates to the field of aerospace manufacturing technology, and in particular to a support device. Background Technology

[0002] Shot peening utilizes high-speed shot to impact the surface of parts, inducing severe plastic deformation of the outer layer, forming a reinforced layer and residual compressive stress field, effectively inhibiting the initiation and propagation of fatigue cracks, and significantly improving resistance to stress corrosion and wear resistance.

[0003] Fatigue fracture is one of the main failure modes in aircraft structures. Shot peening can establish beneficial residual compressive stress on the surface, thereby improving fatigue durability. Therefore, it is widely used in the aerospace manufacturing field to improve the life of metal components. Modern large aircraft typically use large skins to reduce connections and increase overall rigidity. Large skins have gently curved surfaces and large longitudinal and transverse dimensions, resulting in stress concentration around window and door frames. Therefore, local shot peening is required for the areas around window and door frames; other areas need to be shielded and protected during shot peening to prevent shot damage or shape alteration.

[0004] In practice, masking operations are mostly carried out on a platform. Operators need to bend down and crawl under the large skin to apply protective material piece by piece to non-shot-peened areas such as window frames and door frames. Due to the limited space, the operators' working posture is distorted during the masking operation, resulting in high labor intensity. At the same time, because the masking operation takes a long time, the large skin may deform if it is placed horizontally for a long time, thus affecting the curvature and shape of the large skin. Utility Model Content

[0005] The purpose of this utility model is to provide a support device that facilitates the covering operation of large skin panels, reduces labor intensity, and reduces the risk of deformation of large skin panels during the covering operation.

[0006] To achieve this objective, the present invention adopts the following technical solution:

[0007] A support device for supporting the large skin of an aircraft, the support device comprising multiple relatively independent support mechanisms, each of the support mechanisms including:

[0008] Support frame;

[0009] A support plate, wherein the support plate is provided with a support part adapted to the large skin of the aircraft;

[0010] The first adjustment component is provided in two sets, and the two sets of the first adjustment components are spaced apart along the length direction at the upper end of the support frame. The two ends of the support plate are respectively connected to the two sets of the first adjustment components, and both sets of the first adjustment components can drive the support plate to rise and fall.

[0011] The second adjustment component is connected to the lower end of the support frame and can drive the support frame to rise and fall.

[0012] As a further technical solution, the two opposite end faces of the support plate along the height direction are both configured as the support portion, and both support portions are configured as arc portions, with the radii of the two arc portions being the same or different.

[0013] As a further technical solution, the width of the two support parts along the width direction is greater than the thickness of the middle part of the support plate.

[0014] As a further technical solution, flexible buffers are provided on both of the support parts.

[0015] As a further technical solution, the first adjustment component includes a spiral positioner, a support and a support screw, and the support plate is provided with a connecting screw hole;

[0016] The spiral positioner is disposed at the upper end of the support frame, the support is drivenly connected to the spiral positioner, the support screw is connected to the support and screwed into the corresponding connecting screw hole.

[0017] As a further technical solution, the first adjustment component also includes an adjustment support plate and an adjustment drive component. The upper end of the support frame is provided with a guide rail extending along the length direction. The lower end surface of the adjustment support plate is provided with a guide groove that slides in cooperation with the guide rail. The adjustment drive component is disposed on the support frame. The output shaft of the adjustment drive component is drivenly connected to the adjustment support plate and extends and retracts along the length direction. The spiral positioner is disposed on the adjustment support plate.

[0018] As a further technical solution, the first adjustment component includes a push rod motor, which is disposed at the upper end of the support frame. The output shaft of the push rod motor extends and retracts along the height direction and is connected to the support plate in a transmission manner.

[0019] As a further technical solution, the second adjustment component includes a plurality of adjustable support feet, and at least one of the adjustable support feet is provided on both sides of the support frame along the width direction, and the plurality of adjustable support feet are spaced apart along the length direction.

[0020] As a further technical solution, the support frame includes two sets of crossbeams and multiple sets of longitudinal beams. The two sets of crossbeams are arranged parallel to each other along the height direction, and the multiple sets of longitudinal beams are arranged between the two sets of crossbeams along the length direction. Reinforcing members are provided at the connection between the longitudinal beams and the crossbeams.

[0021] As a further technical solution, the support mechanism also includes a plurality of casters, which are spaced apart at the lower end of the support frame.

[0022] Compared with the prior art, the supporting device provided by this utility model has the following advantages:

[0023] 1. The support frame has two sets of first adjustment components spaced along its length at its upper end. The two ends of the support plate are connected to these first adjustment components, and both sets can raise and lower the support plate. Simultaneously, the lower end of the support frame has a second adjustment component capable of raising and lowering the support frame itself. Therefore, before shot peening the large aircraft skin, the large aircraft skin is placed on multiple support mechanisms. Then, according to actual needs, the overall height of the support frame is adjusted using the second adjustment component, and the height of the support plate is adjusted using the two sets of first adjustment components. This ensures that the height of the large aircraft skin is suitable for masking operations. Afterward, operators can mask the non-shot-peened areas of the large aircraft skin. This increases the working space during the entire masking process, making it easier for operators of different heights to perform masking operations, easing their posture, and reducing labor intensity.

[0024] 2. Because the support plate is equipped with support components adapted to the large aircraft skin, during the shielding operation, the support components fit snugly against the outer wall of the large aircraft skin to eliminate cantilever sections. If the large aircraft skin experiences regional sagging during the shielding operation, the height of the corresponding support mechanism can be adjusted in real time to compensate for the deformation trend. Simultaneously, the cooperation of multiple support mechanisms ensures that the load is evenly distributed across multiple points, significantly reducing the internal bending moment of the large aircraft skin and thus lowering the risk of deformation caused by its own weight or operational forces. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the description of the embodiments of this utility model will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on the content of the embodiments of this utility model and these drawings without creative effort.

[0026] Figure 1 This is a schematic diagram of the structure of the support device provided in an embodiment of the present utility model;

[0027] Figure 2 This is a partial structural schematic diagram of the support device provided in an embodiment of the present utility model;

[0028] Figure 3 This is a schematic diagram of the structure of the support tray in the support device provided in this embodiment of the utility model.

[0029] In the picture:

[0030] 10. Supporting structures;

[0031] 100. Support frame; 110. Reinforcing member; 120. Support beam; 130. Support longitudinal beam; 140. Support auxiliary beam; 150. Reinforcing auxiliary beam;

[0032] 200. Support plate; 210. Flexible buffer; 220. Connecting screw hole;

[0033] 300. First adjusting component; 310. Screw positioner; 320. Support; 330. Support screw; 340. Adjusting support plate;

[0034] 400. Adjustable support feet;

[0035] 500. Casters. Detailed Implementation

[0036] Before explaining any implementation of this application in detail, it should be understood that this application is not limited to its application to the structural details and component arrangements set forth in the following description or shown in the above drawings.

[0037] In this application, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0038] In this application, the term "and / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent three cases: A existing alone, A and B existing simultaneously, and B existing alone. Additionally, the character " / " in this application generally indicates that the preceding and following related objects have an "and / or" relationship.

[0039] In this application, the terms "connection," "combination," "coupling," and "installation" can refer to direct connection, combination, coupling, or installation, or indirect connection, combination, coupling, or installation. For example, a direct connection refers to two parts or components being connected together without the need for an intermediary, while an indirect connection refers to two parts or components each being connected to at least one intermediary, with the connection achieved through the intermediary. Furthermore, "connection" and "coupling" are not limited to physical or mechanical connections or couplings, but can also include electrical connections or couplings.

[0040] In this application, those skilled in the art will understand that relative terms (e.g., “about,” “approximately,” “basically,” etc.) used in conjunction with quantities or conditions are to include the values ​​and have the meaning indicated by the context. For example, such relative terms include at least the degree of error associated with the measurement of a particular value, tolerances associated with the particular value due to manufacturing, assembly, use, etc. Such terms should also be considered as disclosing a range defined by the absolute values ​​of the two endpoints. Relative terms may refer to a certain percentage (e.g., 1%, 5%, 10% or more) of the indicated value. Numerical values ​​not using relative terms should also be disclosed as specific values ​​with tolerances. Furthermore, “basically” when expressing relative angular relationships (e.g., substantially parallel, substantially perpendicular) may refer to a certain degree (e.g., 1 degree, 5 degrees, 10 degrees or more) added to or subtracted from the indicated angle.

[0041] In this application, those skilled in the art will understand that the function performed by a component can be performed by one component, multiple components, one part, or multiple parts. Similarly, the function performed by a part can also be performed by one part, one component, or a combination of multiple parts.

[0042] In this application, the directional terms "upper," "lower," "left," "right," "front," and "rear" are used to describe the orientation and positional relationships shown in the accompanying drawings and should not be construed as limiting the embodiments of this application. Furthermore, in the context, it should be understood that when an element is mentioned as being connected "upper" or "lower" to another element, it can be directly connected to the other element "upper" or "lower," or indirectly connected through an intermediate element. It should also be understood that directional terms such as upper side, lower side, left side, right side, front side, and rear side not only represent positive orientation but can also be understood as lateral orientation. For example, "below" can include directly below, lower left, lower right, lower front, and lower rear.

[0043] Combination Figures 1 to 3As shown, the support device provided in this embodiment is used to support the large skin of an aircraft, facilitating the shielding operation of the large skin, reducing labor intensity, and reducing the risk of deformation of the large skin during the shielding operation. Specifically, the support device includes multiple relatively independent support mechanisms 10 for supporting the large skin of the aircraft. Each support mechanism 10 includes a support frame 100, a support plate 200, a first adjustment component 300, and a second adjustment component. The support plate 200 is provided with a support part adapted to the large skin of the aircraft. Two sets of first adjustment components 300 are provided, and the two sets of first adjustment components 300 are spaced apart along the length direction at the upper end of the support frame 100. The two ends of the support plate 200 are respectively connected to the two sets of first adjustment components 300, and both sets of first adjustment components 300 can drive the support plate 200 to rise and fall along the height direction. The second adjustment component is connected to the lower end of the support frame 100 and can drive the support frame 100 to rise and fall along the height direction.

[0044] Because the upper end of the support frame 100 is provided with two sets of first adjustment components 300 spaced apart along its length, and both ends of the support plate 200 are respectively connected to the two sets of first adjustment components 300, and both sets of first adjustment components 300 can drive the support plate 200 to rise and fall; at the same time, the lower end of the support frame 100 is provided with a second adjustment component that can drive the support frame 100 to rise and fall. Therefore, before shot peening the large aircraft skin, the large aircraft skin is first placed on multiple support mechanisms 10, and then, according to actual needs, the overall height of the support frame 100 is adjusted by the second adjustment component, and the height of the support plate 200 is adjusted by the two sets of first adjustment components 300, so that the height of the large aircraft skin is at a height that is convenient for masking operations. Afterwards, the operator can perform masking operations on the non-shot-peened areas of the large aircraft skin. In this way, during the entire masking operation, the working space can be increased, making it easier for operators of different heights to perform masking operations, easing the working posture of the operators, and reducing labor intensity.

[0045] Because the support plate 200 is equipped with a support section adapted to the large skin of the aircraft, during the shielding operation, the support section is fitted with the outer wall of the large skin of the aircraft to eliminate cantilever sections. During the shielding operation, if the large skin of the aircraft experiences regional deflection, the height of the corresponding support mechanism 10 can be finely adjusted in real time to compensate for the deformation trend. At the same time, multiple support mechanisms 10 cooperate with each other, and the load is evenly distributed at multiple points, significantly reducing the internal bending moment of the large skin of the aircraft, thereby reducing the risk of deformation caused by its own weight or operating force.

[0046] In this embodiment, the number of support mechanisms 10 in the support device is not specifically limited. It can be set to three, four, six, eight, etc. The number of support mechanisms 10 can be increased or decreased according to the length of the large aircraft skin.

[0047] In addition, in this embodiment, the support plate 200 is detachably connected to the two corresponding first adjustment components 300. With this configuration, the support plate 200 of the corresponding specification can be replaced according to the size of the large skin of the aircraft to be covered, thereby ensuring the support effect and anti-deformation effect of the large skin of the aircraft to be covered and improving the applicability of the support mechanism 10.

[0048] Preferably, the two opposite end faces of the support plate 200 along the height direction are both configured as support portions, and both support portions are configured as arc portions.

[0049] Combination Figure 1 and Figure 3 As shown, this configuration allows the arc-shaped portion to continuously fit against the small-curvature outer surface of the aircraft's large skin during the masking operation. This disperses the skin's weight and operational forces, preventing dents or deformations caused by localized stress concentration. Simultaneously, the arc-shaped portions serve as opposing mounting surfaces, allowing for adaptation to aircraft skins placed in opposite directions. During the masking operation, the front and back of the aircraft skin can be masked without replacing the support plate 200, reducing the number of support plates 200 used and thus lowering the cost of the support mechanism 10. The radii of the two arc-shaped portions can be the same or different. When the radii are the same, they can adapt to aircraft skins placed in opposite directions; when the radii are different, they can adapt to aircraft skins with different curvatures. The specific configuration can be adapted to actual needs, and this embodiment does not impose specific limitations.

[0050] In some other embodiments, the width of the two support portions along the width direction is greater than the thickness of the middle portion of the support plate 200. That is, the cross-section of the support plate 200 along its length direction is "I" shaped. This arrangement increases the area of ​​the support portions, thereby increasing the contact area between the support plate 200 and the large aircraft skin, ensuring the support effect on the large aircraft skin while improving the anti-deformation effect on the large aircraft skin; on the other hand, while ensuring the support effect, it minimizes the weight of the support plate 200, making it easier to disassemble, assemble, and adjust the state of the support plate 200.

[0051] Preferably, both support sections are equipped with flexible buffers 210. By providing the flexible buffers 210, on the one hand, during the shielding operation, transient impacts may be transmitted to the large aircraft skin. The flexible buffers 210 can absorb and dissipate this energy through elastic deformation, suppressing micro-resonance of the large aircraft skin and reducing the probability of deformation. On the other hand, after the large aircraft skin is placed on the support plate 200, the flexible buffers 210 can compensate for the gap and manufacturing errors between the arc portion and the curved surface of the large aircraft skin, reducing the large aircraft skin's dependence on the precision of the support plate 200, simplifying the leveling process, and thus improving work efficiency.

[0052] The material of the flexible buffer 210 can be polyurethane elastomer, silicone rubber, nitrile rubber, neoprene rubber, fluororubber, etc., depending on actual needs. No specific limitation is made in this embodiment.

[0053] Preferably, the first adjustment component 300 includes a screw positioner 310, a support 320, and a support screw 330. The support plate 200 has a connecting screw hole 220. The screw positioner 310 is located at the upper end of the support frame 100. The support 320 is connected to the screw positioner 310. The support screw 330 is connected to the support 320 and screwed into the corresponding connecting screw hole 220. By threading the support screw 330 into the corresponding threaded hole, the support plate 200 can be connected to the corresponding first adjustment component 300. Simultaneously, this prevents the support plate 200 connected to the first adjustment component 300 from wobbling or shifting in the width direction, thus ensuring effective support for the aircraft's large skin. Furthermore, the height of the support plate 200 is adjusted via the screw positioner 310. Since the screw positioner 310 achieves micron-level feed through its threaded joint, the adjustment accuracy during the height adjustment process of the support plate 200 is guaranteed, ensuring high-precision support and positioning of the aircraft's large skin. Simultaneously, the screw positioner 310 typically employs trapezoidal or rectangular threads, which possess self-locking capabilities to prevent jamming during shielding operations, thus ensuring the stability of the support for the aircraft's large skin. The specific structure and working principle of the screw positioner 310 are described in existing technology and will not be repeated here.

[0054] Furthermore, the first adjustment assembly 300 also includes an adjustment support plate 340 and an adjustment drive (not shown in the figure). The upper end of the support frame 100 is provided with a guide rail (not shown in the figure) extending along its length. The lower end face of the adjustment support plate 340 is provided with a guide groove (not shown in the figure) that slides in cooperation with the guide rail. The adjustment drive is mounted on the support frame 100, and its output shaft is drivenly connected to the adjustment support plate 340 and extends and retracts along its length. A helical positioner 310 is mounted on the adjustment support plate 340. With this configuration, before the masking operation, the distance between the two helical positioners 310 is adjusted by extending and retracting the output shaft of the adjustment drive, according to the size of the large skin of the aircraft to be masked. This allows for the installation of a support plate 200 of the corresponding size, facilitating support for the large skin of the current-specification aircraft. The sliding cooperation between the guide rail and the guide groove ensures convenience and stability when adjusting the distance between the two helical positioners 310. The specific structure and working principle of the adjustment drive are described in the prior art and will not be repeated here.

[0055] In some other embodiments, the first adjustment component 300 includes a push rod motor, which is disposed at the upper end of the support frame 100. The output shaft of the push rod motor extends and retracts along the height direction and is connected to the support plate 200. A support screw 330 is provided on the output shaft of the push rod motor, which is screwed into a corresponding connecting screw hole 220 to connect the support plate 200 to the push rod motor. During the shielding operation, the push rod motor can adjust the height of the support plate 200 by extending and retracting the output shaft according to actual needs, thereby adjusting the height of the large skin of the aircraft. The specific structure and working principle of the push rod motor are described in accordance with the prior art and will not be repeated here.

[0056] Preferably, the second adjustment component includes a plurality of adjustable support feet 400, and at least one adjustable support foot 400 is provided on both sides of the support frame 100 along the width direction, and the plurality of adjustable support feet 400 are spaced apart along the length direction.

[0057] Combination Figure 1 and Figure 2 As shown, in this embodiment, the support frame 100 is provided with two adjustable support feet 400. The two adjustable support feet 400 are arranged on both sides of the support frame 100 along the width direction and at both ends of the support frame 100 along the length direction. This ensures the adjustment effect when adjusting the overall height of the support frame 100, and also ensures the stability of the support frame 100 after the height adjustment is completed. The specific structure and working principle of the adjustable support feet 400 are described in the prior art and will not be repeated here.

[0058] In other embodiments, along the width direction, the adjustable support feet 400 on both sides of the support frame 100 may be provided in two, three, four, etc., and are not limited to one in this embodiment.

[0059] Furthermore, the support frame 100 includes two sets of crossbeams and multiple sets of longitudinal beams. The two sets of crossbeams are arranged relatively parallel and spaced apart along the height direction, and the multiple sets of longitudinal beams are arranged spaced apart between the two sets of crossbeams along the length direction. Reinforcing members 110 are provided at the connection between the longitudinal beams and the crossbeams.

[0060] Combination Figure 1 and Figure 2As shown, in this embodiment, four sets of longitudinal beams are provided, which are evenly spaced and relatively parallel along the length direction. Each set of longitudinal beams includes two supporting longitudinal beams 130 that are spaced and relatively parallel along the width direction. Each set of transverse beams includes two supporting transverse beams 120 that are spaced and relatively parallel along the width direction. Triangular reinforcing members 110 are provided at multiple connection points between the longitudinal beams and transverse beams to improve the strength and stability of the support frame 100. In addition, the support frame 100 also includes two auxiliary support beams 140 and multiple reinforcing auxiliary beams 150. The two auxiliary support beams 140 are respectively located at both ends of the transverse beam set below. The two auxiliary support beams 140 are spaced and relatively parallel, and both extend along the width direction so that the two auxiliary support beams 140 are stacked with the first adjustment component 300, thereby improving the support effect on the corresponding first adjustment component 300 and ensuring the support effect on the large skin of the aircraft placed on the support plate 200. Each auxiliary support beam 140 is equipped with a reinforcing auxiliary beam 150 at the connection point between itself and the crossbeam assembly to improve the connection strength and stability of the corresponding auxiliary support beam 140.

[0061] In order to ensure the support effect while minimizing the weight of the support frame 100, in this embodiment, all beams are hollow beams, and the ends of the beams exposed at both ends are equipped with baffles to prevent external debris, moisture, etc. from entering the hollow beams and affecting the use effect and service life of the support frame 100.

[0062] Preferably, the support mechanism 10 further includes a plurality of casters 500, which are spaced apart at the lower end of the support frame 100.

[0063] Specific combination Figure 1 and Figure 2 As shown, in this embodiment, both ends of the two auxiliary support beams 140 are equipped with casters 500 with brake structures. With this configuration, during the use of the support mechanism 10, the placement position of the support mechanism 10 can be adjusted according to actual needs by pushing the support frame 100 and using the casters 500, thereby improving the applicability of the support mechanism 10.

[0064] Obviously, the above embodiments of this utility model are merely examples for clearly illustrating the present utility model, and are not intended to limit the implementation of the present utility model. Those skilled in the art can make various obvious changes, readjustments, and substitutions without departing from the protection scope of this utility model. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this utility model should be included within the protection scope of the claims of this utility model.

Claims

1. A support device for supporting large aircraft skin, characterized in that, The support device includes multiple relatively independent support mechanisms (10), each of which includes: Support frame (100); A support plate (200) is provided with a support portion adapted to the large skin of the aircraft; The first adjustment component (300) is provided in two sets. The two sets of the first adjustment components (300) are spaced apart along the length direction at the upper end of the support frame (100). The two ends of the support plate (200) are respectively connected to the two sets of the first adjustment components (300), and both sets of the first adjustment components (300) can drive the support plate (200) to rise and fall. The second adjustment component is connected to the lower end of the support frame (100) and can drive the support frame (100) to rise and fall.

2. The support device according to claim 1, characterized in that, The two end faces of the support plate (200) along the height direction are both set as the support parts, and the two support parts are both set as arc parts, and the radii of the two arc parts are the same or different.

3. The support device according to claim 2, characterized in that, The width of the two support portions along the width direction is greater than the thickness of the middle portion of the support plate (200).

4. The support device according to claim 2, characterized in that, Both of the aforementioned support portions are provided with flexible buffers (210).

5. The support device according to claim 1, characterized in that, The first adjustment component (300) includes a screw positioner (310), a support (320) and a support screw (330), and the support plate (200) is provided with a connecting screw hole (220); The spiral positioner (310) is disposed at the upper end of the support frame (100), the support (320) is connected to the spiral positioner (310) in a driving manner, and the support screw (330) is connected to the support (320) and screwed into the corresponding connecting screw hole (220).

6. The support device according to claim 5, characterized in that, The first adjustment component (300) further includes an adjustment support plate (340) and an adjustment drive component. The upper end of the support frame (100) is provided with a guide rail extending along the length direction. The lower end surface of the adjustment support plate (340) is provided with a guide groove that slides with the guide rail. The adjustment drive component is disposed on the support frame (100). The output shaft of the adjustment drive component is connected to the adjustment support plate (340) and extends and retracts along the length direction. The spiral positioner (310) is disposed on the adjustment support plate (340).

7. The support device according to claim 1, characterized in that, The first adjustment component (300) includes a push rod motor, which is disposed at the upper end of the support frame (100). The output shaft of the push rod motor extends and retracts along the height direction and is connected to the support plate (200) in a transmission manner.

8. The support device according to claim 1, characterized in that, The second adjustment component includes a plurality of adjustable support feet (400), and at least one of the adjustable support feet (400) is provided on both sides of the support frame (100) along the width direction, and the plurality of adjustable support feet (400) are spaced apart along the length direction.

9. The support device according to claim 1, characterized in that, The support frame (100) includes two sets of crossbeams and multiple sets of longitudinal beams. The two sets of crossbeams are arranged parallel to each other along the height direction and spaced apart. The multiple sets of longitudinal beams are arranged spaced apart between the two sets of crossbeams along the length direction. Reinforcing members (110) are provided at the connection between the longitudinal beams and the crossbeams.

10. The support device according to any one of claims 1-9, characterized in that, The support mechanism (10) also includes a plurality of casters (500), which are spaced apart at the lower end of the support frame (100).

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