Magnetic levitation separation support device for satellite payload cabin

Abstract

The application provides a satellite load cabin magnetic levitation separation support device, which comprises a main support frame and upper, lower, left and right support legs arranged vertically on the upper end, lower end, left end and right end of the main support frame respectively; the lower support leg is provided with a first air cushion mounting column and a second air cushion mounting column; the main support frame has an octagonal structure and is provided with a third air cushion mounting column arranged in the same direction with the first air cushion mounting column and the second air cushion mounting column on the end side of the lower end. The application can simulate the load cabin body when the satellite is subjected to the magnetic levitation test, is connected with the air cushion and is used for supporting the load cabin, can support the gravity unloading when the satellite load cabin is subjected to the magnetic levitation separation, the unloading process is stable and reliable, the efficiency of the satellite load cabin magnetic levitation separation is improved, the support rigidity of the satellite load cabin is improved, and the application has the advantages of simple structure, small deformation, safety and reliability and the like.

Description

Technical Field

[0001] This invention relates to the field of spacecraft ground magnetic levitation separation test technology, specifically to a magnetic levitation separation support device for satellite payload compartments. Background Technology

[0002] During the magnetic levitation separation test between the satellite payload compartment and the platform compartment, the payload compartment needs to be air-floated on the marble platform to verify the pointing accuracy of the load inside the payload compartment. Because the payload compartment side panels themselves are made of carbon fiber honeycomb structure, which is relatively weak and easily deformed, and because the side panels lack an interface for installing air-floating pads, a support unloading device needs to be designed to connect with the payload compartment floor plate to simulate the payload compartment and install air-floating pads for unloading onto the marble platform. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the purpose of this invention is to provide a magnetic levitation separation support device for satellite payload compartments.

[0004] According to the present invention, a magnetic levitation separation support device for a satellite payload compartment includes a main support frame and upper support leg, lower support leg, left support leg and right support leg respectively vertically arranged at the upper end, lower end, left end and right end of the main support frame;

[0005] The lower support leg is provided with a first air cushion mounting column and a second air cushion mounting column. The main support frame has an octagonal outline and a third air cushion mounting column arranged in the same direction as the first air cushion mounting column and the second air cushion mounting column on the lower end side.

[0006] Preferably, the main support frame is equipped with multiple gas cylinder mounting plate fixing structures.

[0007] Preferably, both the upper support leg and the lower support leg are adjustable vertically on the main support frame;

[0008] The left and right support legs are both adjustable left and right on the main support frame.

[0009] Preferably, the main support frame is provided with an upper support leg mounting surface, a lower support leg mounting surface, a left support leg mounting surface, and a right support leg mounting surface, respectively, for mounting the upper support leg, the lower support leg, the left support leg, and the right support leg.

[0010] Preferably, the upper support leg mounting surface, lower support leg mounting surface, left support leg mounting surface, and right support leg mounting surface are each provided with multiple mounting holes.

[0011] Preferably, the upper support leg, lower support leg, left support leg, and right support leg each have a first connection structure that matches a plurality of the mounting holes.

[0012] Preferably, the upper support leg, lower support leg, left support leg, and right support leg are each provided with a second connecting structure at the end away from the main support frame.

[0013] Preferably, both the left and right support legs are equipped with lifting rings.

[0014] Preferably, the upper support leg, lower support leg, left support leg, and right support leg are each provided with a load compartment connection end at the end away from the main support frame.

[0015] Preferably, the upper support leg, lower support leg, left support leg, and right support leg are all I-shaped structures.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] During satellite maglev tests, this invention is fixedly connected to the payload compartment floor to simulate the payload compartment body. The air-bearing pad mounting column below the support device connects to the air-bearing pad, providing air-bearing support for the payload compartment on the air-bearing platform. Because the four support legs of the support device all adopt an I-beam structure, the structure is simple, and the entire support device is made of stainless steel. Finite element analysis shows that the deformation of the fixed assembly between the support device and the payload compartment floor is small, ensuring stability and reliability during unloading. This avoids wasted time due to rework and repairs, and improves the efficiency of maglev separation of the satellite payload compartment. Therefore, this invention improves the support stiffness of the satellite payload compartment in maglev separation tests, and has advantages such as simple structure, small deformation, and safety and reliability. Attached Figure Description

[0018] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0019] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0020] Figure 2 yes Figure 1 Top view;

[0021] Figure 3 yes Figure 1 The main view;

[0022] Figure 4 yes Figure 1 The left view;

[0023] Figure 5 This is a front view of a support frame according to an embodiment of the present invention;

[0024] Figure 6 These are the front view and left view of an upper support leg in an embodiment of the present invention;

[0025] Figure 7 These are the front view and left view of a lower support leg in an embodiment of the present invention;

[0026] Figure 8 These are a front view and a left view of a left support leg in an embodiment of the present invention;

[0027] Figure 9 These are the front view and left view of a right support leg in an embodiment of the present invention.

[0028] The diagram shows:

[0029] Upper support leg 1

[0030] Right supporting leg 2

[0031] Rings 21

[0032] Lower support leg 3

[0033] Left supporting leg 4

[0034] Main support frame 5

[0035] First air-bearing cushion mounting column 31

[0036] Second air cushion mounting column 32

[0037] Upper support leg mounting surface 51

[0038] Right support leg mounting surface 52

[0039] Lower support leg mounting surface 53

[0040] Left support leg mounting surface 54

[0041] Third air-bearing cushion mounting column 55

[0042] Gas cylinder mounting plate fixing structure 56

[0043] Mounting hole 57

[0044] First connection structure 571

[0045] Second connection structure 572

[0046] Third connection structure 573

[0047] Mounting surface 574 connected to the bottom plate of the load compartment Detailed Implementation

[0048] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0049] Example 1:

[0050] This invention addresses the shortcomings of weak side plate rigidity and lack of air buoyancy pad installation interface in satellite payload compartments by providing a magnetic levitation separation support device. This device features a gravity unloading interface, a simple structure, and convenient installation. Furthermore, the support device is entirely constructed from stainless steel square tubing, resulting in higher rigidity and better stability in the assembly formed by the support device and the payload compartment during magnetic levitation testing. The magnetic levitation separation support device for the satellite payload compartment includes a main support frame 5 and upper support legs 1, lower support legs 3, left support legs 4, and right support legs 2, which are vertically arranged at the upper, lower, left, and right ends of the main support frame 5, respectively. The upper support legs 1, lower support legs 3, right support legs 2, and left support legs 4 are preferably of an I-shape, and the lower support leg 3 is preferably of a hollow shape. The lower support leg 3 is provided with a first air buoyancy pad mounting column 31 and a second air buoyancy pad mounting column 32. The main support frame 5 has an octagonal outline and a third air buoyancy pad mounting column 55 is provided on the lower end side, which is arranged in the same direction as the first air buoyancy pad mounting column 31 and the second air buoyancy pad mounting column 32. The first air buoyancy pad mounting column 31, the second air buoyancy pad mounting column 32, and the third air buoyancy pad mounting column 55 are used together to fix the air buoyancy pad.

[0051] The main support frame 5 is equipped with multiple gas cylinder mounting plate fixing structures 56. These fixing structures 56 can employ various structures, such as hole-type structures or support plate structures; etc. Preferably, the gas cylinder mounting plate fixing structures 56 use through holes, which, along with screws and other connecting parts, secure the gas cylinder mounting plates.

[0052] The main support frame 5 is equipped with upper support leg mounting surfaces 51, lower support leg mounting surfaces 53, left support leg mounting surfaces 54, and right support leg mounting surfaces 52, respectively, for mounting the upper support leg 1, lower support leg 3, left support leg 4, and right support leg 2. Each of the upper support leg mounting surfaces 51, lower support leg mounting surfaces 53, left support leg mounting surfaces 54, and right support leg mounting surfaces 52 is provided with multiple mounting holes 57. Each of the upper support leg 1, lower support leg 3, left support leg 4, and right support leg 2 has a first connecting structure 571 that matches the multiple mounting holes 57. The first connecting structure 571 is preferably an oblong hole, and the oblong hole and the mounting holes 57 can be fixed by screws or other connectors. To increase the versatility of the device, the upper support leg 1 and the lower support leg 3 are adjustable up and down on the upper support leg mounting surface 51 and the lower support leg mounting surface 53 of the main support frame 5, respectively, and the left support leg 4 and the right support leg 2 are adjustable left and right on the left support leg mounting surface 54 and the right support leg mounting surface 52 of the main support frame 5, respectively.

[0053] Each of the upper support leg 1, lower support leg 3, left support leg 4, and right support leg 2 has a load compartment connection end at its end furthest from the main support frame 5. Each of the upper support leg 1, lower support leg 3, left support leg 4, and right support leg 2 has a second connection structure 572 at its end furthest from the main support frame 5. The second connection structure 572 preferably has a hole structure. The second connection structure 572 is used to connect to the load compartment floor plate.

[0054] To facilitate assembly, lifting rings 21 are provided on both the left support leg 4 and the right support leg 2, which can realize the hoisting and assembly of the entire device and improve assembly efficiency.

[0055] Example 2:

[0056] This embodiment is a preferred example of Embodiment 1.

[0057] In this embodiment, as Figures 1-9 As shown, a magnetic levitation separation support device for a satellite payload compartment is provided, comprising: an upper support leg 1, a right support leg 2, a lower support leg 3, a left support leg 4, and a main support frame 5. The main support frame 5 is an octagonal structure with four surfaces: an upper support leg mounting surface 51, a lower support leg mounting surface 53, a left support leg mounting surface 54, and a right support leg mounting surface 52. Each mounting surface is provided with mounting holes 57, preferably two threaded holes, for screw connection of each support leg.

[0058] The upper support leg 1 has an I-shaped structure. The mounting surface connected to the main support frame 5 is provided with a first connecting structure 571. The first connecting structure 571 preferably has four waist-shaped through holes. The mounting surface 574 connected to the load compartment bottom plate is provided with a third connecting structure 573. The third connecting structure 573 preferably has two waist-shaped through holes. The axial directions of the waist-shaped through holes at both ends of the upper support leg 1 are perpendicular to each other.

[0059] The lower support leg 3 has an I-shaped structure. The mounting surface connected to the main support frame 5 is provided with a first connecting structure 571, which preferably has four waist-shaped through holes. The mounting surface 574 connected to the load chamber bottom plate is provided with a third connecting structure 573, which preferably has two waist-shaped through holes. The axial directions of the waist-shaped through holes at both ends of the lower support leg 3 are perpendicular to each other. The lower support leg 3 is provided with two air-bearing support columns, namely a first air-bearing pad mounting column 31 and a second air-bearing pad mounting column 32, for connecting the air-bearing pad.

[0060] The left support leg 4 has an I-shaped structure. The mounting surface connected to the main support frame 5 is provided with a first connecting structure 571, which preferably has four oblong through holes. The mounting surface 574 connected to the load compartment bottom plate is provided with a third connecting structure 573, which preferably has two oblong through holes. The axial directions of the oblong through holes at both ends of the left support leg 4 are perpendicular to each other. The left support leg 4 is provided with two lifting rings 21, which are preferably lifting ring screws for lifting.

[0061] The right support leg 2 has an I-shaped structure. The mounting surface connected to the main support frame 5 is provided with a first connecting structure 571, which preferably has four oblong through holes. The mounting surface 574 connected to the load compartment bottom plate is provided with a third connecting structure 573, which preferably has two oblong through holes. The axial directions of the oblong through holes at both ends of the right support leg 2 are perpendicular to each other. The right support leg 2 is provided with two lifting rings 21, which are preferably lifting ring screws for lifting.

[0062] This invention uses screws to connect the various support legs to the threaded holes in the honeycomb plate on the bottom plate of the satellite payload compartment, forming a tooling clamp that holds the bottom plate of the payload compartment. This simulates and fixes the payload compartment, and the I-shaped support legs spatially avoid interference from various loads on the bottom plate of the payload compartment. The octagonal structure of the main support frame 5 provides the main support force, and the eight through holes on the main support frame 5 are used for bolting the gas cylinder mounting plates, thus ensuring a continuous and stable gas supply to the air levitation pad during the magnetic levitation separation test of the satellite payload compartment. This invention has the advantages of simple structure, convenient installation, and high rigidity. It can provide fixed support for the magnetic levitation separation test of the satellite payload compartment with small deformation and high safety and reliability.

[0063] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0064] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A magnetic levitation separation support device for a satellite payload compartment, characterized in that, Includes a main support frame (5) and upper support leg (1), lower support leg (3), left support leg (4) and right support leg (2) respectively arranged vertically at the upper end, lower end, left end and right end of the main support frame (5); The lower support leg (3) is provided with a first air cushion mounting column (31) and a second air cushion mounting column (32). The main support frame (5) has an octagonal structure and a third air cushion mounting column (55) is provided on the lower end side, which is arranged in the same direction as the first air cushion mounting column (31) and the second air cushion mounting column (32). The main support frame (5) is equipped with multiple gas cylinder mounting plate fixing structures (56). The upper support leg (1) and the lower support leg (3) are both adjustable up and down on the main support frame (5); The left support leg (4) and the right support leg (2) are both adjustable left and right on the main support frame (5); The main support frame (5) is provided with an upper support leg mounting surface (51), a lower support leg mounting surface (53), a left support leg mounting surface (54), and a right support leg mounting surface (52) for mounting the upper support leg (1), the lower support leg (3), the left support leg (4), and the right support leg (2), respectively. The upper support leg (1), lower support leg (3), left support leg (4), and right support leg (2) are each provided with a second connecting structure (572) at the end away from the main support frame (5). Both the left support leg (4) and the right support leg (2) are equipped with hanging rings (21); The upper support leg (1), lower support leg (3), left support leg (4), and right support leg (2) are respectively provided with load chamber connection ends at the ends away from the main support frame (5); The upper support leg (1), lower support leg (3), left support leg (4), and right support leg (2) are all I-shaped structures.

2. The magnetic levitation separation support device for satellite payload compartment according to claim 1, characterized in that, Multiple mounting holes (57) are provided on the upper support leg mounting surface (51), lower support leg mounting surface (53), left support leg mounting surface (54), and right support leg mounting surface (52).

3. The magnetic levitation separation support device for satellite payload compartment according to claim 2, characterized in that, The upper support leg (1), lower support leg (3), left support leg (4), and right support leg (2) each have a first connection structure (571) that matches a plurality of the mounting holes (57).

Images