A rotary indexing device for satellite horizontal mounting

Abstract

The utility model relates to a kind of rotary displacement devices for satellite horizontal installation, the device includes driving mechanism, chassis and rotating frame rotationally mounted on chassis, rotating frame is installed with rotating mechanism, rotating mechanism is installed with satellite force cylinder away from rotating frame, several satellite installation platforms are installed on satellite force cylinder along its circumference, and satellite installation platform is used to install satellite;Rotating mechanism and rotating frame at least include first connecting rod between, rotating frame is connected with rotating mechanism by first connecting rod, and mounting platform is installed on first connecting rod, and driving mechanism and rotating mechanism transmission cooperation are matched.The utility model can make satellite be installed on satellite force cylinder in the mode of horizontal installation, improve the convenience and security of gravity unloading and deployment test operation, and also can meet the needs of mechanical environment test.

Description

Technical Field

[0001] This utility model relates to the field of satellite installation technology, and in particular to a rotational positioning device for horizontal satellite installation. Background Technology

[0002] Satellites are typically installed in two ways: vertical and horizontal. Currently, with the increasing variety of satellites and the installation of numerous precision instruments, coupled with the need for subsequent gravity unloading and deployment tests, many satellites are limited to horizontal installation.

[0003] Therefore, there is an urgent need for a reversible positioning device for horizontal satellite installation to meet the current requirement of horizontal installation for many satellites, thereby improving the convenience and safety of gravity unloading and deployment testing operations, while also meeting the needs of mechanical environment testing. Utility Model Content

[0004] The purpose of this invention is to provide a rotational positioning device for horizontal satellite installation, in order to solve the problems existing in the prior art.

[0005] To achieve the above objectives, this utility model provides the following solution:

[0006] This utility model provides a rotating positioning device for horizontal satellite installation, comprising a base frame and a rotating frame rotatably mounted on the base frame, wherein:

[0007] A rotating mechanism is installed on the rotating frame, and a satellite support cylinder is installed at the end of the rotating mechanism away from the rotating frame. Several satellite mounting platforms are installed on the satellite support cylinder along its circumference, and the satellite mounting platforms are used to install satellites.

[0008] The rotating mechanism and the rotating frame include at least a first connecting rod, the rotating frame is connected to the rotating mechanism through the first connecting rod, and an installation platform is mounted on the first connecting rod;

[0009] The device further includes a drive mechanism, which is in transmission cooperation with the rotation mechanism.

[0010] According to one embodiment of the present invention, an adjustment mechanism is installed between the base frame and the rotating frame, and the two ends of the adjustment mechanism are rotatably connected to the base frame and the rotating frame respectively. The adjustment mechanism is used to unfold or fold the rotating frame.

[0011] The adjustment mechanism includes a telescopic cylinder, the two ends of which are rotatably connected to the base frame and the rotating frame, respectively. The telescopic cylinder is used to unfold or fold the rotating frame.

[0012] According to one embodiment of the present invention, the rotating mechanism and the rotating frame further include a mounting frame, a second flange, and a third flange;

[0013] The mounting bracket is mounted on the rotating frame, the second flange is mounted on the end of the mounting bracket away from the rotating frame, the third flange is mounted on the rotating mechanism, and the first connecting rod is located between the second flange and the third flange, with its two ends connected to the second flange and the third flange respectively.

[0014] According to one embodiment of the present invention, the second flange and the third flange are coaxially arranged;

[0015] The number of the first connecting rods is several, and the several first connecting rods are arranged sequentially along the circumference of the second flange.

[0016] According to one embodiment of the present invention, a first flange is provided between the mounting bracket and the second flange, and the first flange and the second flange are coaxially arranged, with both ends of the first flange connected to the mounting bracket and the second flange respectively.

[0017] The rotating frame is connected to the rotating mechanism via the first flange, the second flange, the first connecting rod, and the third flange.

[0018] According to one embodiment of the present invention, the rotating mechanism includes a slewing bearing, the inner ring and outer ring of the slewing bearing being connected to the third flange and the satellite support cylinder respectively, and the third flange, the slewing bearing and the satellite support cylinder are all coaxially arranged;

[0019] The drive mechanism is mounted on the third flange, and the drive mechanism is in drive engagement with the outer ring of the slewing bearing.

[0020] According to one embodiment of the present invention, the drive mechanism includes a reducer, which is mounted on the third flange;

[0021] The reducer includes a gear reducer, and an external gear ring is coaxially mounted on the outer ring of the slewing bearing. The output end of the gear reducer meshes with the external gear ring.

[0022] A motor is mounted on the reducer, and the output shaft of the motor is driven by the input end of the gear reducer.

[0023] According to one embodiment of the present invention, a fourth flange, a second connecting rod, and a fifth flange are provided between the slewing bearing and the satellite support cylinder, and the slewing bearing, the fourth flange, the fifth flange, and the satellite support cylinder are all coaxially arranged.

[0024] The outer ring of the slewing bearing is connected to the fourth flange, the fifth flange is connected to the satellite support cylinder, the second connecting rod is located between the fourth flange and the fifth flange and its two ends are respectively connected to the fourth flange and the fifth flange, and the outer ring of the slewing bearing is connected to the satellite support cylinder through the fourth flange, the second connecting rod and the fifth flange.

[0025] According to one embodiment of the present invention, a hook is installed at the top of the mounting bracket.

[0026] According to one embodiment of the present invention, a plurality of foot supports are installed on the base frame.

[0027] Beneficial effects

[0028] This utility model has at least the following technical effects:

[0029] 1. By setting up a base frame and a rotating frame, this utility model allows the satellite to be installed horizontally on the satellite support cylinder, which improves the convenience and safety of the satellite's gravity unloading and deployment test operations, while also meeting the needs of mechanical environment testing.

[0030] 2. By setting up a rotating mechanism and a driving mechanism, this utility model can make the satellite support cylinder and the satellite mounting platform rotate, thereby enabling multiple satellite mounting platforms to be rotated to suitable installation positions, so as to enable multiple satellites to be installed horizontally. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments 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 these drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0033] Figure 2 for Figure 1 A magnified view of a portion of point A in the middle;

[0034] Figure 3 for Figure 1A magnified view of a portion of point B in the middle;

[0035] Figure 4 for Figure 1 A schematic diagram of the overall structure from another angle;

[0036] Figure 5 for Figure 4 A magnified view of a portion of point C in the middle;

[0037] Figure 6 for Figure 4 A schematic diagram of the overall structure from another angle;

[0038] Figure 7 for Figure 6 A schematic diagram of the overall structure from another angle;

[0039] Figure 8 This is a schematic diagram of the overall structure of the satellite support cylinder and the satellite mounting platform in this utility model;

[0040] Figure 9 for Figure 8 A schematic diagram of the overall structure from another angle;

[0041] Figure 10 for Figure 1 A schematic diagram of the overall structure in a folded state.

[0042] Explanation of reference numerals in the attached figures:

[0043] 1. Base frame; 2. Foot support; 3. Rotating frame; 4. Telescopic cylinder; 5. Mounting frame; 6. First flange; 7. Second flange; 8. First connecting rod; 9. Mounting platform; 10. Third flange; 11. Slewing bearing; 12. Reducer; 13. Motor; 14. Fourth flange; 15. Second connecting rod; 16. Fifth flange; 17. Satellite support cylinder; 18. Satellite mounting platform; 19. Hook; 20. Electrical control box. Detailed Implementation

[0044] The features and exemplary embodiments of various aspects of this utility model will be described in detail below. To make the objectives, technical solutions, and advantages of this utility model clearer, the following detailed description is provided in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain this utility model and to exemplarily illustrate the principles of this utility model, and are not configured to limit this utility model. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of this utility model.

[0045] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of this utility model. In the description of this utility model, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0046] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0047] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., without specifically indicating order or sequence, and should not be considered restrictive. Similar terms are used throughout the description to represent similar elements.

[0048] For those skilled in the art, this invention can be implemented without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples.

[0049] In the following embodiments, there may be descriptions such as "this device" or "the device". Those skilled in the art should understand that "this device" or "the device" refers to a gyroscopic positioning device for horizontal satellite installation provided by this utility model.

[0050] like Figures 1-10 As shown, this utility model provides a rotational positioning device for horizontal satellite installation. Figure 1 , Figure 4 , Figure 6 and Figure 7 As shown, the device includes at least a base frame 1 and a rotating frame 3 rotatably mounted on the base frame 1, wherein:

[0051] In this embodiment, as Figure 4 As shown, the base frame 1 can be a rectangular parallelepiped structure as a whole, and the base frame 1 can be made of multiple square beams (known in the art) welded together, without any particular limitation.

[0052] In this embodiment, as Figure 4 and Figure 6 As shown, the rotating frame 3 can be considered as a two-layer structure, one of which (i.e. Figure 4 The central rotating frame 3, located on the left-hand layer, can be an octagonal structure formed by welding together multiple square beams. The other layer (i.e....) Figure 4 The rotating frame 3 (located on the right side) can be roughly a circular plate structure, and the two layers of the rotating frame 3 can be concentrically arranged and welded together, without any particular limitation.

[0053] In this embodiment, as Figure 4 As shown, the rotating frame 3 is located Figure 4 The bottom end of the middle part can be rotatably mounted (hinged) on the base frame 1. Figure 4 At the top right of the center. The rotating frame 3 can be rotatably connected to the rotating frame 3 via hinges known in the art, without particular limitation here.

[0054] like Figure 1 , Figure 4 , Figure 6 and Figure 7 As shown, an adjustment mechanism is installed between the base frame 1 and the rotating frame 3, and the two ends of the adjustment mechanism are rotatably connected to the base frame 1 and the rotating frame 3 respectively. The adjustment mechanism can be used to unfold or fold the rotating frame 3, that is, the adjustment mechanism can make the base frame 1 and the rotating frame 3 in the unfolded state, and can also make the base frame 1 and the rotating frame 3 in the folded state.

[0055] Specifically, such as Figure 4 As shown, the adjustment mechanism includes a telescopic cylinder 4. The two ends of the telescopic cylinder 4 (i.e., the telescopic end and the fixed end of the telescopic cylinder 4) are rotatably connected to the base frame 1 and the rotating frame 3, respectively. The telescopic cylinder 4 can be used to unfold or fold the rotating frame 3. That is, the telescopic cylinder 4 can extend itself to make the base frame 1 and the rotating frame 3 unfolded, and it can also retract itself to make the base frame 1 and the rotating frame 3 folded.

[0056] In this embodiment, as Figure 4 As shown, the telescopic cylinder 4 is located Figure 4 The top of the rotating frame 3 is rotatably connected (hinged) to the top of the rotating frame 3. Figure 4 At the top, telescopic cylinder 4 is located Figure 4 The bottom end of the cylinder can be rotatably connected (hinged) to the base frame 1. The telescopic cylinder 4 can be rotatably connected to the rotating frame 3 and the base frame 1 respectively via hinges known in the art, without any particular limitation.

[0057] In this embodiment, as Figure 4 As shown, the rotatable connection between the telescopic cylinder 4 and the base frame 1 can be located between the rotatable connection between the base frame 1 and the rotating frame 3 and the center line of the base frame 1.

[0058] In this embodiment, the telescopic cylinder 4 is a prior art known in the art. For example, it can be an electric cylinder (also known as an electric cylinder or electric telescopic cylinder) or a hydraulic cylinder (also known as a hydraulic cylinder or hydraulic telescopic cylinder) known in the art, etc., preferably an electric cylinder, and is not particularly limited here.

[0059] like Figure 1 and Figure 4 As shown, a rotating mechanism is mounted on the rotating frame 3, and the end of the rotating mechanism away from the rotating frame 3 (i.e., Figure 4 The right end of the satellite is equipped with a satellite support cylinder 17, and several satellite mounting platforms 18 are installed on the satellite support cylinder 17 along its circumference. The satellite mounting platforms 18 are used to install satellites (not shown in the figure).

[0060] In this embodiment, as Figure 8 and Figure 9 As shown, Figure 8 and Figure 9 An exemplary schematic diagram of the overall structure of the satellite support cylinder 17 and the satellite mounting platform 18 in this embodiment is shown. Both the satellite support cylinder 17 and the satellite mounting platform 18 are existing technologies known in the art. The satellite support cylinder 17 can be or is approximately a hollow cylindrical structure. There can be three satellite mounting platforms 18, which are sequentially welded or bolted to the outer wall of the satellite support cylinder 17 along its circumference.

[0061] In this embodiment, the satellite (not shown in the figure) can be mounted on the satellite mounting platform 18. How the satellite is mounted on the satellite mounting platform 18 is prior art known in the art and will not be described in detail here. For example... Figure 8 and Figure 9 As shown, in this embodiment, there can be three satellite mounting platforms 18, and the three satellite mounting platforms 18 are sequentially installed along the circumference of the satellite support cylinder 17 on the outer wall of the satellite support cylinder 17. It should be understood that, due to the different types of satellites, therefore, as... Figure 9 As shown, the shape of the opening (i.e., the satellite mounting position) on the satellite mounting platform 18 in this embodiment is also different; for example, it can be... Figure 9 The circular and square-like structures in this text are not specifically limited here.

[0062] like Figure 2 and Figure 5As shown, the rotating mechanism and the rotating frame 3 are connected by at least a first connecting rod 8, meaning the rotating frame 3 is connected to the rotating mechanism via the first connecting rod 8. A mounting platform 9 is mounted on the first connecting rod 8.

[0063] In this embodiment, as Figure 2 As shown, the mounting platform 9 can be a flat, rectangular plate structure, and it can be positioned horizontally. During satellite installation, the operator (not shown) can stand or sit on the mounting platform 9.

[0064] According to one embodiment of the present invention, the device further includes a drive mechanism, which is in transmission cooperation with the rotating mechanism, that is, the drive mechanism can provide power to the rotating mechanism, thereby causing the rotating mechanism to rotate.

[0065] According to one embodiment of the present invention, such as Figure 2 and Figure 5 As shown, the rotating mechanism and the rotating frame 3 also include at least a mounting bracket 5, a second flange 7, and a third flange 10. The mounting bracket 5 is mounted on the rotating frame 3, and the second flange 7 is mounted on the end of the mounting bracket 5 furthest from the rotating frame 3 (i.e.,...). Figure 2 The third flange 10 is mounted on the rotating mechanism (right end of the first flange 7). The first connecting rod 8 is located between the second flange 7 and the third flange 10, and its two ends are connected to the second flange 7 and the third flange 10 respectively.

[0066] In this embodiment, as Figure 1 As shown, the mounting frame 5 can be a cuboid structure composed of multiple square beams welded together. The connection between the mounting frame 5 and the rotating frame 3 can be achieved using bolt connections known in the art, and is not particularly limited here.

[0067] In this embodiment, as Figure 2 As shown, the second flange 7 can be coaxially arranged with the third flange 10, and both the second flange 7 and the third flange 10 can be circular.

[0068] In this embodiment, as Figure 5 As shown, the number of first connecting rods 8 is several, preferably... Figure 5 The seven in the middle. And several first connecting rods 8 are arranged sequentially along the circumference of the second flange 7 or along the circumference of the third flange 10.

[0069] In this embodiment, as Figure 2 As shown, the bottom surfaces of both ends of the mounting platform 9 can be welded to any two first connecting rods 8 respectively, so as to ensure that the mounting platform 9 is set in the horizontal direction.

[0070] In this embodiment, the connection between the first connecting rod 8 and the second flange 7, and between the first connecting rod 8 and the third flange 10, can all be achieved through welding connections known in the art, and are not particularly limited here.

[0071] It should be understood that since the second flange 7 and the third flange 10 are coaxially arranged, the circumferential direction along the second flange 7 and the circumferential direction along the third flange 10 are defined in the same way.

[0072] According to one embodiment of the present invention, such as Figure 2 As shown, a first flange 6 is provided between the mounting bracket 5 and the second flange 7, and the first flange 6 and the second flange 7 are coaxially arranged. The two ends of the first flange 6 are connected to the mounting bracket 5 and the second flange 7 respectively. That is, the rotating bracket 3 is connected to the rotating mechanism in sequence through the first flange 6, the second flange 7, the first connecting rod 8 and the third flange 10.

[0073] In this embodiment, the first flange 6 can be identical in shape to the second flange 7, and the first flange 6 can be connected to the second flange 7 by bolts, or the first flange 6 can be connected to the mounting bracket 5 by welding; no particular limitation is made here. Since the second flange 7 and the third flange 10 are coaxially arranged, and the first flange 6 and the second flange 7 are coaxially arranged, the first flange 6, the second flange 7, and the third flange 10 are all coaxially arranged.

[0074] In this embodiment, by setting the first flange 6, the second flange 7 and the third flange 10, a detachable connection can be achieved while ensuring a stable connection between the various components.

[0075] Specifically, such as Figure 5 As shown, the rotating mechanism includes at least a slewing bearing 11. The inner and outer rings of the slewing bearing 11 are connected to the third flange 10 and the satellite support cylinder 17, respectively. The third flange 10, the slewing bearing 11 and the satellite support cylinder 17 are all coaxially arranged.

[0076] In this embodiment, the slewing bearing 11 is a prior art known in the art, and will not be described in detail here.

[0077] In this embodiment, since the first flange 6, the second flange 7, and the third flange 10 are all coaxially arranged, and the third flange 10, the slewing bearing 11, and the satellite support cylinder 17 are also coaxially arranged, the first flange 6, the second flange 7, the third flange 10, the slewing bearing 11, and the satellite support cylinder 17 are all coaxially arranged. The drive mechanism can be mounted on the third flange 10, and the drive mechanism is in transmission engagement with the outer ring of the slewing bearing 11, meaning the drive mechanism enables the outer ring of the slewing bearing 11 to rotate.

[0078] In this embodiment, the inner ring of the slewing bearing 11 can be connected to the third flange 10 by bolts, which is not particularly limited here.

[0079] In this embodiment, the drive mechanism can be connected to the third flange 10 by welding, which is not particularly limited here.

[0080] More specifically, such as Figure 5 As shown, the drive mechanism includes at least a reducer 12, which can be mounted on the third flange 10 by welding. The reducer 12 includes at least a gear reducer known in the art, preferably a gear reducer known in the art. An external gear ring (not shown) is coaxially mounted on the outer ring of the slewing bearing 11. The output end of the gear reducer meshes with the external gear ring, thereby achieving a transmission connection between the reducer 12 and the slewing bearing 11, i.e., a transmission connection between the drive mechanism and the outer ring of the slewing bearing 11. A motor 13 is mounted on the reducer 12, and the output shaft of the motor 13 (i.e., the output end of the motor 13) is in transmission connection with the input end of the gear reducer.

[0081] In this embodiment, the motor 13 can be a servo motor or the like known in the art, and is not particularly limited here.

[0082] It should be understood that gear reducers can include various reducers capable of reducing speed and increasing torque and whose output end is a gear. For example, the gear reducer in this embodiment can have a pinion at the input end and a large gear at the output end that meshes with the pinion. The large gear at the output end will mesh with the outer gear ring of the outer ring of the slewing bearing 11, thereby realizing the transmission connection between the reducer 12 and the slewing bearing 11.

[0083] Furthermore, the reducer 12 in this embodiment can also be a planetary gear reducer known in the art, and is not particularly limited here.

[0084] According to one embodiment of the present invention, such as Figure 2 and Figure 5As shown, a fourth flange 14, a second connecting rod 15, and a fifth flange 16 are also provided between the slewing bearing 11 and the satellite support cylinder 17, and the slewing bearing 11, the fourth flange 14, the fifth flange 16, and the satellite support cylinder 17 are all coaxially arranged.

[0085] In this embodiment, since the first flange 6, the second flange 7, the third flange 10, the slewing bearing 11 and the satellite support cylinder 17 are all coaxially arranged, and the slewing bearing 11, the fourth flange 14, the fifth flange 16 and the satellite support cylinder 17 are also coaxially arranged, the first flange 6, the second flange 7, the third flange 10, the slewing bearing 11, the fourth flange 14, the fifth flange 16 and the satellite support cylinder 17 are all coaxially arranged.

[0086] like Figure 5 As shown, the outer ring of the slewing bearing 11 is connected to the fourth flange 14, the fifth flange 16 is connected to the satellite support cylinder 17, and the second connecting rod 15 is located between the fourth flange 14 and the fifth flange 16, with both ends of the second connecting rod 15 connected to the fourth flange 14 and the fifth flange 16 respectively. That is, the outer ring of the slewing bearing 11 is connected to the satellite support cylinder 17 through the fourth flange 14, the second connecting rod 15 and the fifth flange 16.

[0087] In this embodiment, the outer ring of the slewing bearing 11 can be connected to the fourth flange 14 by bolts, which is not particularly limited here.

[0088] In this embodiment, the end of the satellite support cylinder 17 near the fifth flange 16 may be provided with an inner or outer flange, and the satellite support cylinder 17 can be connected to the fifth flange 16 by bolts through the aforementioned inner or outer flange, without any particular limitation.

[0089] In this embodiment, as Figure 5 As shown, both the fifth flange 16 and the fourth flange 14 can be circular, and the diameter of the fifth flange 16 can be smaller than the diameter of the fourth flange 14. The number of second connecting rods 15 can be several, and they are evenly arranged between the fourth flange 14 and the fifth flange 16, and the second connecting rods 15 can be inclined.

[0090] In this embodiment, the installation platform 9 and the satellite mounting platform 18 can be extended by setting the fourth flange 14, the second connecting rod 15 and the fifth flange 16, thereby providing sufficient operating space for the operators and ensuring the smooth progress of the satellite installation work.

[0091] Furthermore, such as Figure 3As shown, a hook 19 is installed at the top of the mounting bracket 5. The hook 19 can be connected to the mounting bracket 5 by bolts or welding, which is not particularly limited here.

[0092] When operators stand or sit on the installation platform 9 to perform satellite installation work, a safety rope (not shown in the figure and known in the art) can be tied to the operator, and the end of the safety rope can be tied to the hook 19, thereby ensuring the safety of the operator and preventing the operator from falling and getting injured.

[0093] Furthermore, such as Figure 1 , Figure 4 , Figure 6 and Figure 7 As shown, a number of legs 2 are installed on the base frame 1, preferably eight legs 2, which are arranged evenly along the circumference of the base frame 1.

[0094] In this embodiment, the foot support 2 makes the device more stable, thereby improving its overall stability. The foot support 2 can be connected to the base frame 1 via bolts, which is not specifically limited here.

[0095] According to one embodiment of the present invention, such as Figure 1 As shown, an electrical control box 20 is mounted on the mounting bracket 5.

[0096] In this embodiment, the electrical control box 20 can be electrically connected to both the telescopic cylinder 4 and the motor 13, thereby controlling the start and stop of the telescopic cylinder 4 and the motor 13 and distributing electrical energy. The electrical control box 20 can also be equipped with an emergency stop switch (not shown in the figure), which enables the telescopic cylinder 4 and the motor 13 to stop suddenly, further improving the safety of the device during use.

[0097] It should be understood that the internal structure of the electrical control box 20, the electrical connection between the electrical control box 20 and the telescopic cylinder 4 and the motor 13, and the emergency stop switch are all existing technologies known in the art, and will not be elaborated here.

[0098] The working process of this device will be briefly described below with reference to the above embodiments:

[0099] Before this device is used, its state will be as follows: Figure 10 As shown, the rotating frame 3 and the base frame 1 are folded together, that is, not flipped.

[0100] In use, firstly, using external hoisting equipment (known in the art), the satellite support cylinder 17 and the satellite mounting platform 18 installed on it are hoisted together onto the fifth flange 16, and then the satellite support cylinder 17 and the satellite mounting platform 18 installed on it are bolted to the fifth flange 16 using bolts and nuts (known in the art) and other components (the state after hoisting can be referred to). Figure 10 ).

[0101] Then, the telescopic cylinder 4 is extended via the electrical control box 20. At this time, the rotating frame 3 will rotate (i.e., flip) along the position where it is rotatably connected to the base frame 1. When the rotating frame 3 and the base frame 1 rotate to a position of 90° or approximately 90° relative to each other, the extension of the telescopic cylinder 4 is stopped (the state after flipping can be referred to...). Figure 4 In this regard, the extension speed of the telescopic cylinder 4 can be set to be relatively slow, which allows the rotating frame 3 to slowly rotate, thus ensuring the stability of the other components of the device.

[0102] After the flipping is complete, the satellite support cylinder 17 and the satellite mounting platform 18 will be in a horizontal or roughly horizontal state. At this time, the operator stands or sits on the mounting platform 9 and ties the safety rope to the hook 19, so that the satellite can be installed horizontally on the satellite mounting platform 18.

[0103] In the above process, since there are multiple satellite mounting platforms 18, meaning this device needs to install multiple satellites, and the operator can only install satellites facing the direction directly in front of them, that is, the position directly facing the operator is the suitable installation position. Therefore, at this time, the motor 13 can be started through the electrical control box 20. The power of the motor 13 will be transmitted to the slewing bearing 11 through the reducer 12, thereby enabling the satellite support cylinder 17 to rotate clockwise or counterclockwise. This allows the multiple satellite mounting platforms 18 to be rotated to suitable installation positions, thus enabling the horizontal installation of multiple satellites.

[0104] It should be understood that the above-described embodiments or examples of this utility model can be combined with each other and have corresponding technical effects.

[0105] The above are merely preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A rotational positioning device for horizontally mounted satellites, characterized in that, Includes a base frame (1) and a rotating frame (3) rotatably mounted on the base frame (1), wherein: A rotating mechanism is installed on the rotating frame (3). A satellite support cylinder (17) is installed at one end of the rotating mechanism away from the rotating frame (3). Several satellite mounting platforms (18) are installed on the satellite support cylinder (17) along its circumference. The satellite mounting platforms (18) are used to install satellites. The rotating mechanism and the rotating frame (3) include at least a first connecting rod (8), the rotating frame (3) is connected to the rotating mechanism through the first connecting rod (8), and an installation platform (9) is installed on the first connecting rod (8). The device further includes a drive mechanism, which is in transmission cooperation with the rotation mechanism.

2. The gyroscopic positioning device for horizontal satellite installation according to claim 1, characterized in that, An adjustment mechanism is installed between the base frame (1) and the rotating frame (3). The two ends of the adjustment mechanism are rotatably connected to the base frame (1) and the rotating frame (3) respectively. The adjustment mechanism is used to unfold or fold the rotating frame (3). The adjustment mechanism includes a telescopic cylinder (4), the two ends of which are rotatably connected to the base frame (1) and the rotating frame (3) respectively. The telescopic cylinder (4) is used to unfold or fold the rotating frame (3).

3. The gyroscopic positioning device for horizontal satellite installation according to claim 1, characterized in that, The rotating mechanism and the rotating frame (3) also include a mounting frame (5), a second flange (7) and a third flange (10). The mounting bracket (5) is mounted on the rotating bracket (3), the second flange (7) is mounted on the end of the mounting bracket (5) away from the rotating bracket (3), the third flange (10) is mounted on the rotating mechanism, and the first connecting rod (8) is located between the second flange (7) and the third flange (10) and its two ends are respectively connected to the second flange (7) and the third flange (10).

4. The gyration positioning device for horizontal satellite installation according to claim 3, characterized in that, The second flange (7) is coaxially arranged with the third flange (10); The number of the first connecting rods (8) is several, and the several first connecting rods (8) are arranged sequentially along the circumference of the second flange (7).

5. The gyroscopic positioning device for horizontal satellite installation according to claim 3, characterized in that, A first flange (6) is provided between the mounting bracket (5) and the second flange (7), and the first flange (6) and the second flange (7) are coaxially arranged. The two ends of the first flange (6) are respectively connected to the mounting bracket (5) and the second flange (7). The rotating frame (3) is connected to the rotating mechanism via the first flange (6), the second flange (7), the first connecting rod (8), and the third flange (10).

6. The gyroscopic positioning device for horizontal satellite installation according to claim 3, characterized in that, The rotating mechanism includes a slewing bearing (11), the inner ring and outer ring of which are connected to the third flange (10) and the satellite support cylinder (17) respectively. The third flange (10), the slewing bearing (11) and the satellite support cylinder (17) are all coaxially arranged. The drive mechanism is mounted on the third flange (10), and the drive mechanism is in drive engagement with the outer ring of the slewing bearing (11).

7. The gyroscopic positioning device for horizontal satellite installation according to claim 6, characterized in that, The drive mechanism includes a reducer (12) which is mounted on the third flange (10); The reducer (12) includes a gear reducer, and an external gear ring is coaxially mounted on the outer ring of the slewing bearing (11). The output end of the gear reducer meshes with the external gear ring. A motor (13) is mounted on the reducer (12), and the output shaft of the motor (13) is in transmission cooperation with the input end of the gear reducer.

8. The gyroscopic positioning device for horizontal satellite installation according to claim 6, characterized in that, A fourth flange (14), a second connecting rod (15), and a fifth flange (16) are provided between the slewing bearing (11) and the satellite support cylinder (17), and the slewing bearing (11), the fourth flange (14), the fifth flange (16), and the satellite support cylinder (17) are all coaxially arranged. The outer ring of the slewing bearing (11) is connected to the fourth flange (14), the fifth flange (16) is connected to the satellite support cylinder (17), the second connecting rod (15) is located between the fourth flange (14) and the fifth flange (16) and its two ends are connected to the fourth flange (14) and the fifth flange (16) respectively, and the outer ring of the slewing bearing (11) is connected to the satellite support cylinder (17) through the fourth flange (14), the second connecting rod (15) and the fifth flange (16).

9. The gyroscopic positioning device for horizontal satellite installation according to claim 3, characterized in that, The top of the mounting bracket (5) is fitted with a hook (19).

10. The gyroscopic positioning device for horizontal satellite installation according to claim 1, characterized in that, Several foot supports (2) are installed on the base frame (1).

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