Satellite hoisting assisting mechanism and satellite hoisting method

Abstract

This invention provides a satellite lifting auxiliary mechanism and method, relating to the field of satellite ground assembly technology. The invention includes an inclined support assembly and a ring support assembly. First, the satellite is placed within the ring space of a ring-shaped component. Then, the lower end of the inclined support rod is connected to the lifting point at the bottom of the satellite, and the upper end of the inclined support rod is connected to the ring component, forming a radial support structure. This support structure is connected to external lifting equipment via lifting lugs, allowing for stable lifting of the satellite. The evenly distributed circumferentially arranged inclined support rods and lifting lugs ensure balanced force on the satellite during lifting, solving the problem that conventional lifting methods cannot be used at the lower lifting point of the satellite. This invention features a simple and stable structure, adaptable to various satellite configurations. Simultaneously, the evenly distributed circumferential support structure ensures a stable lifting process, avoids uneven force distribution on the satellite, and allows for reuse, improving ground assembly efficiency.

Description

Technical Field

[0001] This invention belongs to the field of satellite ground assembly technology, and in particular relates to a satellite lifting auxiliary mechanism and a satellite lifting method. Background Technology

[0002] With the continuous development of commercial aerospace technology, satellite configurations have also taken on many different forms, which has put forward higher assembly requirements and wider applicability requirements for ground satellite assembly, especially in the lifting operation process during satellite transportation and assembly.

[0003] Traditional satellite lifting points are usually designed at the top of the satellite, with lifting connection points on the outside of the satellite body. While this method is convenient for lifting operations, the lifting connection points of many current satellites have been moved to the lower part of the satellite. Due to the limitations of the satellite's shape, conventional lifting methods are difficult to meet the actual operational requirements. Therefore, it is urgent to design a special auxiliary support mechanism to solve the lifting adaptation problem of this type of satellite. Summary of the Invention

[0004] In view of this, the present invention aims to provide a satellite lifting auxiliary mechanism and a satellite lifting method to solve the above-mentioned technical problems.

[0005] To achieve the above objectives, the technical solution of the present invention is implemented as follows: In a first aspect, the present invention provides a satellite lifting auxiliary mechanism, comprising: The inclined support assembly includes multiple inclined support rods, one end of which is connected to the satellite lifting point; A ring-shaped support assembly includes a ring-shaped component and multiple lifting lugs, wherein the multiple lifting lugs are arranged circumferentially on the ring-shaped component along its central axis; the other end of the inclined support rod is connected to the rod body of the ring-shaped component. The plurality of the inclined support rods are arranged at intervals around the central axis of the annular component.

[0006] In conjunction with the first aspect, in one embodiment, the inclined support rod is further provided with a locking pin and a connecting support member, one end of the connecting support member is connected to the satellite lifting point, and one end of the inclined support rod is connected to the other end of the connecting support member through the locking pin.

[0007] In conjunction with the first aspect, in one embodiment, the annular component includes multiple arc rods and multiple connecting components. The multiple arc rods are connected end to end to form an annular structure. The connecting components are disposed at the joint of two connected arc rods to connect the two connected arc rods.

[0008] In conjunction with the first aspect, in one embodiment, the connecting assembly includes two steering connectors, which are rotatably connected to the ends of the arc rod; the two steering connectors are respectively disposed at both ends of the arc rod; and two adjacent steering connectors are connected by lugs.

[0009] In conjunction with the first aspect, in one embodiment, the steering connector is rotatably connected to the lug.

[0010] In conjunction with the first aspect, in one embodiment, the lifting lug is a U-shaped structure, and the two parallel rods of the U-shaped structure are respectively rotatably connected to the two steering connectors via lifting pins.

[0011] In conjunction with the first aspect, in one embodiment, the arc rod is a hollow structure, and the oblique support rod is an adjustable rod-shaped object along its length.

[0012] In conjunction with the first aspect, in one embodiment, the steering connector is connected to one end of the arc rod via a pin.

[0013] In conjunction with the first aspect, in one embodiment, there are three arc rods, and the three arc rods are of equal length.

[0014] Secondly, the present invention provides a satellite lifting method, characterized in that it includes the satellite lifting auxiliary mechanism involved in the first aspect, specifically including the following steps: The satellite is placed within the annular space of the annular component; One end of the inclined support assembly is connected to the satellite lifting point, and the other end of the inclined support assembly is connected to the ring-shaped component; The lifting lugs on the annular component are lifted using a crane.

[0015] Beneficial effects: The satellite lifting auxiliary mechanism provided by this invention includes an inclined support assembly and a ring support assembly. First, the satellite is placed within the annular space of the ring component. Then, the lower end of the inclined support rod is connected to the lifting point at the bottom of the satellite, and the upper end of the inclined support rod is connected to the ring component, forming a radial support structure. This support structure is connected to external lifting equipment via lifting lugs, allowing for stable lifting of the satellite. The circumferentially evenly distributed inclined support rods and lifting lugs ensure balanced force on the satellite during lifting, solving the problem that conventional lifting methods cannot be used at the lower lifting point of the satellite. This application features a simple and stable structure that can adapt to various satellite configurations. Simultaneously, the circumferentially evenly distributed support structure ensures a stable lifting process, avoids uneven force distribution on the satellite, and allows for reuse, improving ground assembly efficiency. Attached Figure Description

[0016] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a perspective view of a specific embodiment of the multi-bar auxiliary lifting mechanism of this invention. Figure 2 for Figure 1 Schematic diagram of the inclined support group in the multi-bar auxiliary lifting mechanism; Figure 3 for Figure 1 Schematic diagram of the annular support group in a multi-bar auxiliary lifting mechanism; Figure 4 for Figure 3 Schematic diagram of the lifting mechanism in the central ring support assembly; Explanation of reference numerals in the attached figures: 1. Diagonal support assembly; 101. Diagonal support rod; 102. Locking pin; 103. Connecting support component; 2. Circular support assembly; 201. Arc rod; 202. Lifting lug; 203. Lifting pin; 204. Steering connector; 205. Pin shaft. Detailed Implementation

[0017] It should be noted that, unless otherwise specified, the embodiments and features described in the present invention can be combined with each other.

[0018] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention 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, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first," "second," etc., may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0019] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" 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 mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art will understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0020] The following will refer to the appendix. Figure 1-4 The present invention will be described in detail with reference to the embodiments.

[0021] This invention provides a lifting auxiliary mechanism for satellites, as shown in the attached figure. Figure 1-2 As shown, it includes a diagonal support group 1 and a ring support group 2. The diagonal support group 1 includes multiple diagonal support rods 101, one end of which is connected to the satellite lifting point; the ring support group 2 includes a ring-shaped component and multiple lifting lugs 202, which are spaced around the central axis of the ring-shaped component; the other end of the diagonal support rod 101 is connected to the body of the ring-shaped component. Multiple inclined support rods are spaced around the central axis of the ring-shaped component.

[0022] In this embodiment, the satellite is first placed within the annular space of the annular component. Then, the lower end of the inclined support rod 101 is connected to the lifting point at the bottom of the satellite, and the upper end of the inclined support rod 101 is connected to the annular component, forming a radial support. This support is connected to external lifting equipment via lifting lugs 202, allowing the satellite to be lifted smoothly. The evenly distributed circumferentially arranged inclined support rods 101 and lifting lugs 202 ensure balanced force on the satellite during lifting, solving the problem that conventional lifting methods cannot be used at the lower lifting point of the satellite. This application features a simple and stable structure that can adapt to various satellite configurations. Simultaneously, the evenly distributed circumferentially arranged support structure ensures a stable lifting process, avoids uneven force distribution on the satellite, and allows for reuse, improving ground assembly efficiency.

[0023] Specifically, the inclined support rod 101 is also provided with a locking pin 102 and a connecting support 103. One end of the connecting support 103 is connected to the satellite lifting point, and one end of the inclined support rod 101 is connected to the other end of the connecting support 103 through the locking pin 102.

[0024] One end of the connecting support 103 is provided with a connecting interface (such as a threaded hole or pin hole) that matches the satellite lifting point, and the other end is provided with a connecting groove or connecting hole for the end of the inclined support rod 101 to be inserted. As a transitional connector, it reliably connects the inclined support rod 101 to the satellite lifting point, while providing a stable support surface, distributing the lifting load, and avoiding excessive stress on a single point.

[0025] The locking pin 102 is made of high-strength alloy material and has a cylindrical body. One end is equipped with a limiting structure to prevent it from falling off (such as a head, retaining ring, etc.), and the other end can be equipped with a thread or quick-release structure for easy installation and disassembly.

[0026] Pin holes are opened at the corresponding positions on the end of the inclined support rod 101 and the connecting support 103. During installation, the end of the inclined support rod 101 is inserted into the connecting groove of the connecting support 103, and then the locking pin 102 is inserted into the pin holes of both to fix it, forming a stable hinged connection.

[0027] First, fix the connecting support 103 to the lifting point at the bottom of the satellite; second, insert the end of the inclined support rod 101 into the connecting groove of the connecting support 103, and finally insert the locking pin 102 and lock it to complete the connection between the inclined support rod 101 and the satellite.

[0028] The combined design of the locking pin 102 and the connecting support 103 ensures a stable connection between the inclined support rod 101 and the satellite lifting point, preventing accidental detachment and improving lifting safety. By replacing the connecting support 103 with different specifications, it can be adapted to various satellite lifting point designs, improving the versatility of the auxiliary mechanism. The connecting support 103 provides an easy-to-install interface, and the locking pin 102 has a simple structure and is easy to operate, enabling quick assembly and disassembly, improving ground assembly efficiency.

[0029] In one embodiment, the annular component includes a plurality of arc rods 201 and a plurality of connecting components. The plurality of arc rods 201 are connected end to end to form an annular structure. The connecting components are disposed at the joint of two connected arc rods 201 to connect the two connected arc rods 201.

[0030] First, multiple arc rods 201 are sequentially spliced ​​end to end using connecting components to form a complete ring and ensure a stable connection. Then, one end of the connecting support 103 is fixed to the lifting point at the bottom of the satellite. After inserting one end of the inclined support rod 101 into the corresponding interface of the connecting support 103, the locking pin 102 is inserted into the pin hole of both to lock them, thus forming a reliable connection between the inclined support rod 101 and the satellite. Subsequently, the other end of the inclined support rod 101 is connected to the rod body of the ring, and the evenly distributed inclined support rods 101 form a radial support. Finally, the external lifting equipment is connected to the lifting lugs 202 on the ring. During lifting, the ring evenly transfers the weight of the satellite to each lifting lug 202 through the inclined support rods 101, and then the lifting equipment smoothly lifts the satellite. Throughout the process, the locking pin 102 always locks the inclined support rod 101 and the connecting support 103. The connecting components ensure that the ring remains intact and stable, jointly ensuring the smooth and safe lifting process.

[0031] The combined design of the connecting support 103 and the locking pin 102 makes the connection between the inclined support rod 101 and the satellite lifting point more reliable, avoiding accidental separation during lifting. At the same time, the connecting support 103 can be adapted to various satellite lifting point interfaces by changing different specifications, improving the versatility of the mechanism. The locking pin 102 has a simple structure and is easy to assemble and disassemble quickly, improving the efficiency of ground assembly. The ring part adopts a split design of multiple arc rods 201 and connecting components, which not only facilitates transportation and storage, but also allows for flexible adjustment of the number or length of arc rods 201 according to the satellite size, adapting to satellite lifting scenarios with different diameter requirements. The connecting components ensure that the assembled ring part has sufficient structural strength. Combined with the circumferentially evenly distributed inclined support rods 101 and lifting lugs 202, the force is balanced during satellite lifting, reducing the impact of local stress concentration on the satellite structure. This effectively solves the problem that conventional lifting methods cannot be used for the lower lifting point of the satellite. The overall structure is simple, stable, and reusable, further improving the convenience and safety of satellite ground assembly.

[0032] In one embodiment, the connecting assembly includes two steering connectors 204, which are rotatably connected to the ends of the arc rods 201. The two steering connectors 204 are respectively located at both ends of the arc rods 201. Two adjacent steering connectors 204 are connected by lifting lugs 202. Multiple arc rods 201 are sequentially spliced ​​together end-to-end through the steering connectors 204 to form a ring. The lifting lugs 202 are evenly distributed around the outer circumference of the ring, serving both as components connecting adjacent steering connectors 204 and as connection points for external lifting equipment. The ring adopts a detachable design, facilitating transportation and storage, and solving the problem of inconvenient transportation of a single ring. The number or length of the arc rods 201 can be adjusted according to the satellite size to adapt to satellites of different diameters, significantly improving the versatility of the mechanism. The steering connectors 204 and the arc rods 201 are rotatably connected, allowing for minute angle adjustments to adapt to dynamic changes during lifting. Adjacent steering connectors 204 are connected by lifting lugs 202, forming a stable hinged structure. The lifting lugs 202 also serve a dual function (connecting adjacent arc rods 201 and the lifting connection point). The entire structure provides multi-point support, ensuring uniform stress distribution during satellite lifting and reducing localized stress concentration.

[0033] Specifically, the steering connector 204 is rotatably connected to the lifting lug 202.

[0034] The lifting lug 202 has a U-shaped structure. The two parallel rods of the U-shaped structure are rotatably connected to the two steering connectors 204 through the lifting pins 203.

[0035] First, the ring-shaped component is assembled using connecting components. The ends of two adjacent arc rods 201 are rotatably connected to the steering connectors 204. Then, the two parallel rods of the U-shaped lifting lugs 202 are hinged to the two steering connectors 204 via lifting pins 203. Utilizing the rotational engagement between the steering connectors 204 and the arc rods 201, and between the steering connectors 204 and the U-shaped lifting lugs 202, the angles of each arc rod 201 can be adaptively adjusted during the assembly process to ensure a consistent ring structure. Subsequently, the connecting support 103 is fixed to the lifting point at the bottom of the satellite. One end of the inclined support rod 101 is inserted into the corresponding interface of the connecting support 103, and a locking pin 102 is inserted into the pin holes of both to achieve quick locking, ensuring a reliable connection between the inclined support rod 101 and the satellite. Finally, the other end of the inclined support rod 101 is fixed to the rod of the ring-shaped component. A radial support system is constructed using circumferentially evenly distributed diagonal support rods 101. During lifting, the external lifting equipment is engaged with the middle of the U-shaped lifting lug 202. The lifting force is transmitted through the U-shaped lifting lug 202 to the steering connector 204, and then distributed to each diagonal support rod 101 via the arc rod 201. Finally, the diagonal support rods 101 are evenly transmitted to multiple lifting points of the satellite through the connecting support 103. Throughout the process, the rotational engagement of the U-shaped lifting lug 202 and the lifting pin 203 can adapt to changes in the force direction of the lifting equipment. The rotational engagement of the steering connector 204 and the arc rod 201 can buffer minor vibrations during the lifting process. The locking pin 102 always maintains a stable connection between the diagonal support rod 101 and the connecting support 103, jointly achieving a smooth and safe lifting of the satellite. During disassembly, simply pull out the locking pin 102 and remove the lifting pin 203 to disassemble the components, facilitating transportation and storage.

[0036] Specifically, the arc rod 201 has a hollow structure, and the diagonal support rod is an adjustable rod-shaped object along its length. The hollow structure of the arc rod 201 effectively achieves lightweight design of the mechanism while ensuring that the structural strength meets the lifting load requirements. This reduces the burden of transportation and disassembly of individual components, while also reducing additional load consumption during the lifting process, thus improving operational convenience and economy. The inclined support rod 101 is adjustable along its length, which can flexibly adapt to the lifting point height and installation spacing requirements of satellites of different sizes. The support angle and length can be precisely adjusted without replacing the entire rod, further improving the adaptability of the mechanism to diverse satellite configurations. At the same time, it ensures that each inclined support rod 101 is subjected to uniform force, ensuring lifting stability.

[0037] The steering connector 204 is connected to one end of the arc rod 201 via a pin 205. The pin 205 connection facilitates the disassembly and installation of the arc rod 201 and the steering connector 204.

[0038] There are three arc rods 201, and the three arc rods 201 are of equal length. On the one hand, the manufacturing cost can be reduced through standardized production, and the equal length structure can quickly achieve symmetrical splicing of the ring parts. It can form a uniform ring structure without complex angle adjustments. Combined with the rotation characteristics of the steering connector 204, the assembly efficiency of the ring parts is further improved. On the other hand, the three arc rods 201 of equal length are evenly distributed circumferentially (at 120° intervals), so that the stress points of the ring parts are symmetrically distributed. This works in conjunction with the circumferentially arranged diagonal support rods 101 and lifting lugs 202 to ensure that the lifting load is evenly transferred to each component, enhancing the stress stability of the overall structure. At the same time, the individual arc rods 201 are of regular size after disassembly, making them easier to transport and store.

[0039] During hoisting, traditional threaded connections are prone to loosening due to strong vibrations, impacts, or alternating loads, leading to displacement or even structural failure. This invention fundamentally solves this problem through the mechanical engagement of asymmetric anti-loosening teeth.

[0040] Firstly, an anti-slip washer is installed between the lifting pin 203 and the steering connector 204, and the tail of the lifting pin 203 is connected by a nut. Asymmetrical anti-loosening teeth are provided on the inner side of the lifting pin 203 where it contacts the anti-slip washer, and on the tail of the lifting pin 203 where it is connected to the corresponding threaded nut. The first set of asymmetrical anti-loosening teeth is on the inner side of the lifting pin 203 where it contacts the anti-slip washer, and the second set of asymmetrical anti-loosening teeth is on the tail of the lifting pin 203 where it is connected to the corresponding threaded nut.

[0041] On the anti-slip washer, a continuous first asymmetric anti-loosening tooth is machined along the circumference. On the contact surface between the lifting pin 203 and the anti-slip washer, a second asymmetric anti-loosening tooth is machined. The first asymmetric anti-loosening tooth and the second asymmetric anti-loosening tooth together form the first asymmetric anti-loosening tooth surface.

[0042] The anti-slip washer has a diameter 15–25% larger than that of the lifting pin 203 to increase the contact area. The internal thread of the nut mates with the external thread of the lifting pin 203 and is connected by a second set of asymmetrical anti-loosening teeth. The external thread profile of the lifting pin 203 can be a standard triangular thread or an asymmetrical thread profile.

[0043] Secondly, the present invention provides a satellite lifting method, characterized in that it includes the satellite lifting auxiliary mechanism involved in the first aspect, specifically including the following steps: The satellite is placed within the annular space of the annular component; One end of the inclined support assembly 1 is connected to the satellite lifting point, and the other end of the inclined support assembly 1 is connected to the ring-shaped component. The lifting lug 202 on the ring-shaped component is lifted using a crane.

[0044] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A lifting auxiliary mechanism for satellites, characterized in that, include: The inclined support assembly includes multiple inclined support rods, one end of which is connected to the satellite lifting point; A ring-shaped support assembly includes a ring-shaped component and multiple lifting lugs, wherein the multiple lifting lugs are arranged circumferentially on the ring-shaped component along its central axis; the other end of the inclined support rod is connected to the rod body of the ring-shaped component. The plurality of the inclined support rods are arranged at intervals around the central axis of the annular component.

2. The hoisting assisting mechanism for a satellite according to claim 1, characterized by The inclined support rod is also provided with a locking pin and a connecting support. One end of the connecting support is connected to the satellite lifting point, and one end of the inclined support rod is connected to the other end of the connecting support through the locking pin.

3. The satellite lifting auxiliary mechanism according to claim 2, characterized in that, The annular component includes multiple arc rods and multiple connecting components. The multiple arc rods are connected end to end to form an annular structure. The connecting components are located at the joint of two connected arc rods to connect the two connected arc rods.

4. The hoisting assisting mechanism for a satellite according to claim 3, characterized by The connecting assembly includes two steering connectors, which are rotatably connected to the ends of the arc rod; the two steering connectors are respectively located at both ends of the arc rod; and two adjacent steering connectors are connected by lugs.

5. The hoisting assisting mechanism for a satellite according to claim 4, characterized by The steering connector is rotatably connected to the lifting lug.

6. The satellite lifting auxiliary mechanism according to claim 5, characterized in that, The lifting lug has a U-shaped structure, and the two parallel rods of the U-shaped structure are rotatably connected to the two steering connectors through lifting pins.

7. The satellite lifting auxiliary mechanism according to claim 6, characterized in that, The arc-shaped rod has a hollow structure, and the inclined support rod is an adjustable rod-shaped object along its length.

8. The satellite lifting auxiliary mechanism according to claim 7, characterized in that, The steering connector is connected to one end of the arc rod via a pin.

9. The satellite lifting auxiliary mechanism according to claim 3, characterized in that, There are three circular arc rods, and the three circular arc rods are of equal length.

10. A method for lifting a satellite, characterized in that, The satellite lifting auxiliary mechanism, as described in any one of claims 1-9, specifically includes the following steps: The satellite is placed within the annular space of the annular component; One end of the inclined support assembly is connected to the satellite lifting point, and the other end of the inclined support assembly is connected to the ring-shaped component; The lifting lugs on the annular component are lifted using a crane.

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