Special-shaped spacecraft lifting appliance and lifting equipment

Abstract

The invention relates to the technical field of spacecraft hoisting, in particular to a special-shaped spacecraft hoisting sling and hoisting equipment, the special-shaped spacecraft hoisting sling comprises hanging assemblies, the hanging assemblies are arranged around a spacecraft, the hanging assemblies are annularly distributed along the central axis of the spacecraft, and each hanging assembly comprises a first supporting rod and a second supporting rod; the first supporting rod is provided with a first end and a second end, the first end is connected with the surface of a spacecraft, and the first supporting rod is of a curved rod structure. The second supporting rod is provided with a third end and a fourth end, the third end is connected with the surface of the spacecraft, and the fourth end is connected with the second end to form a lifting point; the height of the lifting point relative to the ground is larger than the height of the mass center of the spacecraft relative to the ground, the first supporting rod is arranged to be the curved rod, on the basis that it is guaranteed that the lifting point is higher than the mass center of the spacecraft, the minimum distance between the first supporting rod and the avoiding equipment is increased, and intersection between the first supporting rod and the avoiding equipment is prevented; the first supporting rod is prevented from colliding with the spacecraft in the hoisting process.

Description

Technical Field

[0001] The present application relates to the technical field of spacecraft hoisting, and in particular to a hoisting device and equipment for lifting special-shaped spacecraft. Background Art

[0002] During the assembly, testing and packing of spacecraft, special hoists are required to complete the hoisting operation. A large special-shaped spacecraft adopts a configuration layout with wider upper and lower sections and a narrower middle section. The hoisting points are respectively set on the upper and lower end surfaces of the conical cabin in the middle narrow section, that is, the hoisting points are located within the spacecraft envelope. At present, a straight rod hoisting point support structure is used to extend the spacecraft hoisting point to a safe distance outside the spacecraft envelope to avoid bumping into the spacecraft.

[0003] However, due to the configuration of the spacecraft, the upper support rod may interfere with the components on the spacecraft. Currently, the main way to avoid the interfering components is to move the upper support rod away from the interfering components. However, this will cause the position of the hanging point to be too low. When the hanging point is lower than the center of mass of the spacecraft, the stability of the lifting will become poor due to the larger size of the spacecraft structure above the hanging point. This will be reflected in the lifting process, especially in the translation process, the amplitude of the spacecraft shaking will become larger, thereby increasing the risk of collision between the spacecraft and the lifting mechanism. Summary of the invention

[0004] The present application provides a special-shaped spacecraft lifting hoist and lifting equipment, which are used to solve the problems in the prior art of interference between the straight rod type lifting point support structure and the components on the spacecraft and poor lifting stability.

[0005] On the one hand, the present application provides a special-shaped spacecraft lifting device, comprising:

[0006] The hanging components are arranged around the spacecraft and are distributed in a ring along the central axis of the spacecraft. Each hanging component includes:

[0007] A first support rod having a first end and a second end, wherein the first end is connected to the surface of the spacecraft, and the first support rod is a curved rod structure;

[0008] A second support rod has a third end and a fourth end, the third end is connected to the surface of the spacecraft, and the fourth end is connected to the second end to form a suspension point;

[0009] The height of the suspension point relative to the ground is greater than the height of the center of mass of the spacecraft relative to the ground.

[0010] In a possible design, the curvature change rate of the first support rod is less than or equal to 8%.

[0011] In a possible design, a first adjustment hole is formed at a position of the first support rod close to the second end; and / or a second adjustment hole is formed at a position of the second support rod close to the fourth end.

[0012] In a possible design, the hanging assembly further includes:

[0013] A first support, mounted on the surface of the spacecraft, and configured to be rotatably connected to the first end of the first support rod;

[0014] A second support, mounted on the surface of the spacecraft, and configured to be rotatably connected to the third end of the second support rod;

[0015] The beam seat is rotatably connected to the second end of the first support rod and the fourth end of the second support rod respectively.

[0016] In a possible design, a damping coating is provided on a side of the first support and the second support close to the spacecraft.

[0017] In one possible design, the special-shaped spacecraft lifting device also includes:

[0018] A first suspension rod, one end of which is connected to the beam seat;

[0019] a support member connected to all the first suspension rods and used to keep the first suspension rods separated from the spacecraft;

[0020] A second suspension rod, one end of the second suspension rod is connected to the other end of the first suspension rod, and the other end of the second suspension rod is connected to the suspension hook.

[0021] In one possible design, the support member includes at least two support rods, the length direction of each support rod is perpendicular to the central axis of the spacecraft, and the ends of the support rods are respectively connected to corresponding first suspension rods so that each first suspension rod is kept separated from the spacecraft.

[0022] In a possible design, a third adjustment hole is provided on the support rod.

[0023] In a possible design, reinforcing ribs are respectively provided on the surfaces of the first support rod and the second support rod.

[0024] On the other hand, the present application also provides a special-shaped spacecraft lifting device, including the special-shaped spacecraft lifting hoist as described above.

[0025] The beneficial effects of this application are as follows:

[0026] The special-shaped spacecraft lifting sling of the present application connects the first support rod and the second support rod to the surface of the spacecraft, so that each lifting position can form a triangular lifting structure, which is beneficial to maintaining the stability of the spacecraft during the lifting process; by bending the first support rod in the direction away from the avoidance device to form a curved rod structure, on the first hand, when the safety angle between the first support rod and the middle section of the spacecraft is constant, it is beneficial to increase the minimum distance between the first support rod and the avoidance device, prevent the first support rod from colliding with the avoidance device, and ensure that a safe distance can be maintained between the first support rod and the middle section of the spacecraft, so as to avoid a collision between the first support rod and the middle section of the spacecraft during the lifting process; on the second hand, since the first support rod is a curved rod structure, it can be By extending the second support rod, the position of the lifting point is raised, so that the first support rod avoids the components of the spacecraft while ensuring that the lifting point is higher than the center of mass of the spacecraft, thereby improving the stability of the lifting and reducing the shaking of the spacecraft during lifting. At the same time, extending the second support rod can also increase the horizontal distance between the lifting point and the spacecraft, thereby effectively reducing the risk of collision between the hoist and the spacecraft during the lifting process; thirdly, since the first support rod is under pressure during the lifting process, based on the characteristic that the curved rod itself can withstand greater pressure, the first support rod with a curved rod structure can resist greater external pressure during lifting, preventing the first support rod from breaking or deforming; at the same time, the curved rod is conducive to dispersing the pressure perpendicular to the surface of the spacecraft to the top of the spacecraft, thereby improving the safety of lifting.

[0027] The special-shaped spacecraft lifting equipment provided in the present application includes the special-shaped spacecraft lifting hoisting device in the present application, and therefore also includes all the above-mentioned advantages of the special-shaped spacecraft lifting hoisting device. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the specific implementation methods of the present application or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0029] Figure 1 It is a structural schematic diagram of a special-shaped spacecraft lifting device in the prior art;

[0030] Figure 2 A schematic diagram of the structure of a lifting device for a special-shaped spacecraft provided in an embodiment of the present application;

[0031] Figure 3 A top view of a special-shaped spacecraft lifting device provided in an embodiment of the present application;

[0032] Figure 4A schematic diagram of the structure of a first support rod and a second support rod of a special-shaped spacecraft lifting device provided in an embodiment of the present application;

[0033] Figure 5 A schematic diagram of the structure of the support ring of the special-shaped spacecraft lifting device provided in an embodiment of the present application.

[0034] Reference numerals:

[0035] 1', upper support rod; 2', lower support rod;

[0036] 100, first support rod; 110, first end; 120, second end; 130, first adjustment hole; 200, second support rod; 210, third end; 220, fourth end; 230, second adjustment hole; 300, hanging point; 410, first support; 420, second support; 430, beam seat; 500, first suspension rod; 600, support member; 610, support rod; 611, third adjustment hole; 620, support ring; 700, second suspension rod; 800, hook; 900, spacecraft; 910, center of mass. DETAILED DESCRIPTION

[0037] The technical solution of the present application will be described clearly and completely below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0038] Reference Figure 1 As shown, in the prior art, the special-shaped spacecraft has a configuration in which the upper and lower sections are wider and the middle section (conical section) is narrower, and the fulcrum of the hoist is at the edge of the upper end surface and the lower end surface of the middle section. Specifically, the inner end of the upper support rod 1' is connected to the upper end of the middle section, the inner end of the lower support rod 2' is connected to the lower end of the middle section, and the other ends of the upper support rod 1' and the lower support rod 2' are connected to each other to form a hanging point. Among them, if the size of the equipment on the upper section of the spacecraft is large, in order to avoid the equipment, it is necessary to reduce the angle between the upper support rod 1' and the middle section (the generatrix of the conical section), and the height of the corresponding hanging point will be reduced, resulting in a smaller height difference between the center of mass height of the spacecraft and the extended hanging point, and even the hanging point is lower than the center of mass. During the hoisting process, especially during the translation process, there is a risk of collision due to the shaking of the spacecraft; at the same time, due to the adjustment of the angle between the upper support rod 1' and the lower support rod 2', the reaction force on each hanging point of the spacecraft will be changed, and there is a safety hazard.

[0039] In order to solve the above problems, the present application embodiment provides a special-shaped spacecraft lifting device. Figure 2-Figure 5 , describing the special-shaped spacecraft lifting equipment provided in the embodiments of the present application.

[0040] Reference Figure 2 As shown, the lifting device for the special-shaped spacecraft 900 provided in the embodiment of the present application includes a hanging assembly, and the number of the hanging assemblies is multiple, and the multiple hanging assemblies are arranged around the spacecraft 900, and the multiple hanging assemblies are distributed in a ring along the central axis of the spacecraft 900; in some specific embodiments, the number of the hanging assemblies includes four, which are evenly distributed in a ring in the four directions of the front, back, left and right of the spacecraft 900 to improve the stability of the lifting of the spacecraft 900. Among them, each hanging assembly includes a first support rod 100 and a second support rod 200, the first support rod 100 has a first end 110 and a second end 120, the first end 110 is connected to the surface of the spacecraft 900, and the first support rod 100 is a curved rod structure; the second support rod 200 has a third end 210 and a fourth end 220, the third end 210 is connected to the surface of the spacecraft 900, and the fourth end 220 is connected to the second end 120 to form a hanging point 300; the height of the hanging point 300 relative to the ground is greater than the height of the center of mass 910 of the spacecraft 900 relative to the ground. In some specific embodiments, the first support rod 100 is arched, and the first support rod 100 is bent downward near the middle. The first support rod 100 is made of high-strength steel and has high rigidity to withstand the lifting pressure; specifically, the curvature change rate of the first support rod 100 is less than or equal to 8%, which is conducive to controlling the curvature of different positions of the first support rod 100 within a certain range to prevent material yielding and causing instability. In some specific embodiments, the surfaces of the first support rod 100 and the second support rod 200 are respectively provided with reinforcing ribs, which extend along the length direction of the first support rod 100 or the second support rod 200, respectively, so as to increase the compressive capacity or tensile capacity of the first support rod 100 and the second support rod 200 in the length direction.

[0041] By using the technical solution provided by the above embodiment, on the one hand, when the safety angle between the first support rod 100 and the middle section of the spacecraft 900 is constant, it is helpful to increase the minimum distance between the first support rod 100 and the avoidance device, prevent the first support rod 100 from colliding with the avoidance device, and ensure that the first support rod 100 and the middle section of the spacecraft 900 can maintain a safe distance, so as to avoid the first support rod 100 and the middle section of the spacecraft 900 from colliding during the hoisting process; on the other hand, since the first support rod 100 is a curved rod structure, the position of the hanging point 300 can be raised by extending the second support rod 200, so that the first support rod 100 can avoid the components of the spacecraft 900 while ensuring the hanging point 300. 0 is higher than the center of mass 910 of the spacecraft 900, thereby improving the stability of the hoisting and reducing the shaking of the spacecraft 900 during hoisting. At the same time, extending the second support rod 200 can also increase the horizontal distance between the lifting point 300 and the spacecraft 900, thereby effectively reducing the risk of collision between the hoist and the spacecraft 900 during the hoisting process; thirdly, since the first support rod 100 is in a compressed state during the hoisting process, based on the characteristic that the curved rod itself can withstand a large pressure, the first support rod 100 with a curved rod structure can withstand greater external pressure during hoisting, thereby preventing the first support rod 100 from breaking or deforming; at the same time, the curved rod is conducive to dispersing the pressure perpendicular to the surface of the spacecraft 900 to the top of the spacecraft 900, thereby improving the safety of hoisting.

[0042] Reference Figure 4As shown, in some embodiments provided in the present application, a first adjustment hole 130 is provided at a position of the first support rod 100 near the second end 120, and a second adjustment hole 230 is provided at a position of the second support rod 200 near the fourth end 220. In this way, it is convenient to adjust the effective length of the first support rod 100 and the second support rod 200 so as to maintain a safe distance between the first support rod 100 and the avoidance device, and at the same time make the hanging point 300 higher than the center of mass 910 of the spacecraft 900, so that it can be applicable to more models of spacecraft 900 or avoidance devices. In some specific embodiments, permanent magnets are respectively arranged at the ends of the first support rod 100 and the second support rod 200 away from the spacecraft 900, and the permanent magnets are distributed near the first adjustment hole 130 or the second adjustment hole 230 along the length direction of the first support rod 100 or the second support rod 200. For example, the permanent magnets are ring-shaped and are respectively embedded in the first support rod 100 / the outside of the first adjustment hole 130 of the first support rod 100 / the periphery of the second adjustment hole 230, and the magnetic pole of the permanent magnet on the first support rod 100 away from the first support rod 100 is far from the permanent magnet on the second support rod 200. The magnetic pole on the side away from the second support rod 200 is opposite. In this way, in the process of connecting the first support rod 100 and the second support rod 200, the mutual adsorption of the permanent magnets can be used to pre-position the first support rod 100 and the second support rod 200, so as to facilitate the adjustment of the height of the hanging point 300 and the angle of the first support rod 100 to determine the appropriate position of the hanging point 300. After the position of the hanging point 300 is determined, the first support rod 100 and the second support rod 200 are separated, and the corresponding adjustment holes of the first support rod 100 and the second support rod 200 are respectively connected to the beam seat 430.

[0043] Reference Figure 2As shown, in some embodiments provided in the present application, the suspension assembly also includes a first support 410, a second support 420 and a beam seat 430. The first support 410 is installed on the surface of the spacecraft 900, and is used to be rotatably connected to the first end 110 of the first support rod 100; the second support 420 is installed on the surface of the spacecraft 900, and is used to be rotatably connected to the third end 210 of the second support rod 200; the beam seat 430 is rotatably connected to the second end 120 of the first support rod 100 and the fourth end 220 of the second support rod 200, respectively. Specifically, the first support 410 is fixed to the position of the middle section of the spacecraft 900 near the upper end by bolts, and the second support 420 is fixed to the position of the middle section of the spacecraft 900 near the lower end by bolts. The first support 410 and the second support 420 respectively have double-ear structures, and the double-ear structures are provided with pin holes. The first support rod 100 and the second support rod 200 are respectively provided with single-ear structures at both ends, and the single-ear structures are provided with pin holes. The single-ear structure at the inner end of the first support rod 100 and the double-ear structure of the first support 410 are connected to the double-ear structure of the first support 410. The structure is connected by a pin, and the single ear structure at the inner end of the second support rod 200 is connected to the double ear structure of the second support seat 420 by a pin; three groups of double ear structures are provided on the beam seat 430, among which the middle double ear structure is connected to the single ear structure at the outer end of the first support rod 100 by a pin, and the double ear structures on both sides are respectively connected to the corresponding single ear structures at the outer end of the second support rod 200 by a pin; in this way, a triangular structure is formed between the first support seat 410, the second support seat 420 and the beam seat 430 to ensure the stability of the lifting. Among them, a small clearance is adopted between the pin shaft and the pin hole at the connection between the inner end of the first support rod 100 and the first support 410 to control the rotation range of the first support rod 100 around the pin shaft, so as to avoid collision between the first support rod 100 and the spacecraft 900 during installation; a large clearance is adopted between the pin shaft and the pin hole at the connection between the outer end of the first support rod 100 and the beam seat 430, so that the first support rod 100 can be translated between the double-ear structure on the beam seat 430 along the pin shaft, so as to achieve the assemblability between the outer end of the first support rod 100 and the beam seat 430 after the inner end of the first support rod 100 is fixed to the first support 410; a small clearance is adopted between the pin shaft and the pin hole at the connection between the inner end of the second support rod 200 and the second support 420, so that the second support rod 200 does not move after being fixed to the second support 420 of the spacecraft 900.

[0044] In some specific embodiments, a damping coating is provided on the side of the first support 410 and the second support 420 close to the spacecraft 900. Specifically, the damping coating is a tungsten carbide coating, which can increase the friction between the first support 410 and the second support 420 and the surface of the spacecraft 900, thereby improving the stability of the sling. At the same time, the tungsten carbide coating is wear-resistant, high-temperature-resistant, and oxidation-resistant, and can not fall off in the use environment of the spacecraft 900. In some specific embodiments, the side of the first support 410 and the second support 420 close to the spacecraft 900 is an arc surface, so that it can fit with the conical cabin of the spacecraft 900, thereby improving the stability of the sling.

[0045] Reference Figure 2 As shown, in some embodiments provided in the present application, the lifting device for the special-shaped spacecraft 900 further includes a first suspension rod 500, a support member 600, and a second suspension rod 700. One end of the first suspension rod 500 is connected to the beam seat 430; the support member 600 is connected to all the first suspension rods 500, and is used to keep the first suspension rods 500 and the spacecraft 900 separated; one end of the second suspension rod 700 is connected to the other end of the first suspension rod 500, and the other end of the second suspension rod 700 is connected to the hook 800. Specifically, the first suspension rods 500 are evenly distributed around the spacecraft 900, and the number of the first suspension rods 500 is consistent with the number of the beam seat 430. The upper ends of the first suspension rods 500 and the beam seat 430 are connected by a pin shaft, the lower end of the second suspension rod 700 is connected to the rotation of the first suspension rod 500, and the upper ends of the second suspension rods 700 gather toward the central position above the spacecraft 900 and are connected to the hook 800; refer to Figure 3As shown, in some specific embodiments, the support member 600 includes at least two support rods 610, and the length direction of each support rod 610 is perpendicular to the central axis of the spacecraft 900. For example, there are two support rods 610, and the two support rods 610 are perpendicular to each other. The two ends of one support rod 610 are respectively rotatably connected to the first suspension rods 500 on the left and right sides of the spacecraft 900 through a pin shaft, and the two ends of the other support rod 610 are respectively rotatably connected to the first suspension rods 500 on the front and rear sides of the spacecraft 900 through a pin shaft. In this way, when the lifting equipment grabs the hook 800 to lift the spacecraft 900 upward, under the action of the support rods 610, the first suspension rods 500 at the two ends of the support rods 610 are subjected to a force facing away from the spacecraft 900, so that each first suspension rod 500 is kept separated from the spacecraft 900 during the lifting process, so that each first suspension rod 500 is kept at a safe distance from the spacecraft 900 during the lifting process to prevent collision. In some specific embodiments, a plurality of third adjustment holes 611 are provided on the support rod 610, and a pin is disposed in the third adjustment hole 611. Specifically, the third adjustment holes 611 are spaced apart and arranged near the end of the support rod 610. In this way, the connection position between the first suspension rod 500 and the support rod 610 can be adjusted according to the diameter of the spacecraft 900, that is, the position of the third adjustment hole 611 where the pin is located is adjusted, thereby adjusting the distance between the first suspension rod 500 and the spacecraft 900 to a suitable distance; specifically, when the distance between the first suspension rod 500 and the spacecraft 900 is small, the pin is moved toward the middle of the support rod 610; when the distance between the first suspension rod 500 and the spacecraft 900 is large, the pin is moved toward the end of the support rod 610. Refer to Figure 5 As shown, in some other specific embodiments, the support member 600 also includes a support ring 620, and the support rods 610 are evenly distributed on the support ring 620. The support rods 610 extend in a radial direction away from the support ring 620 along the radial direction of the support ring 620, and a plurality of third adjustment holes 611 are also evenly provided on the support rod 610. In this way, the support ring 620 serves to limit the support rod 610, effectively reducing the shaking of the first suspension rod 500, thereby improving the lifting stability.

[0046] The installation process of the special-shaped spacecraft 900 lifting device in this application:

[0047] The first support 410 and the second support 420 are respectively installed at corresponding positions of the spacecraft 900;

[0048] Connect the first end 110 of the first support rod 100 to the first support seat 410, and connect the third end 210 of the second support rod 200 to the second support seat 420;

[0049] Adjust the second end 120 of the first support rod 100 and the fourth end 220 of the second support rod 200, determine the position of the suspension point 300, and connect the second end 120 of the first support rod 100 and the fourth end 220 of the second support rod 200 to the beam seat 430 respectively;

[0050] The lower ends of the first suspension rod 500 pre-installed on the support member 600 and the second suspension rod 700 are respectively connected to the corresponding beam seats 430 in preparation for suspension.

[0051] The embodiment of the present application also provides a lifting device for a special-shaped spacecraft 900, including the lifting equipment for the special-shaped spacecraft 900 in the above embodiment.

[0052] It should be noted that the special-shaped spacecraft 900 lifting equipment includes the special-shaped spacecraft 900 lifting sling, which also includes all the above-mentioned advantages of the special-shaped spacecraft 900 lifting sling, which will not be repeated here.

[0053] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0054] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of this application, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0055] In this application, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0056] In the present application, the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0057] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A lifting device for a special-shaped spacecraft, characterized in that: include: The suspension components are arranged around the spacecraft, and the suspension components are distributed in a ring along the central axis of the spacecraft. Each of the suspension components includes: A first support rod having a first end and a second end, wherein the first end is connected to the surface of the spacecraft, and the first support rod is a curved rod structure; A second support rod having a third end and a fourth end, wherein the third end is connected to the surface of the spacecraft, and the fourth end is connected to the second end to form a suspension point; The height of the suspension point relative to the ground is greater than the height of the center of mass of the spacecraft relative to the ground.

2. The special-shaped spacecraft lifting device according to claim 1 is characterized in that: The curvature change rate of the first support rod is less than or equal to 8%.

3. The special-shaped spacecraft lifting device according to claim 1, characterized in that: A first adjustment hole is formed at a position of the first support rod close to the second end; and / or a second adjustment hole is formed at a position of the second support rod close to the fourth end.

4. The special-shaped spacecraft lifting device according to any one of claims 1 to 3, characterized in that: The hanging assembly also includes: a first support, mounted on the surface of the spacecraft and configured to be rotatably connected to the first end of the first support rod; a second support, mounted on the surface of the spacecraft, and configured to be rotatably connected to the third end of the second support rod; A beam seat is rotatably connected to the second end of the first support rod and the fourth end of the second support rod respectively.

5. The special-shaped spacecraft lifting device according to claim 4 is characterized in that: A damping coating is provided on a side of the first support and the second support close to the spacecraft.

6. The special-shaped spacecraft lifting device according to any one of claims 1 to 3, characterized in that: Also includes: a first suspension rod, one end of which is connected to the beam seat; a support member connected to all of the first suspension rods and used to keep the first suspension rods separated from the spacecraft; A second suspension rod, one end of which is connected to the other end of the first suspension rod, and the other end of which is connected to a hook.

7. The special-shaped spacecraft lifting device according to claim 6, characterized in that: The support member includes at least two support rods, the length direction of each support rod is perpendicular to the central axis of the spacecraft, and the ends of the support rods are respectively connected to the corresponding first suspension rods, so that each first suspension rod is kept separated from the spacecraft.

8. The special-shaped spacecraft lifting device according to claim 7, characterized in that: The support rod is provided with a third adjustment hole.

9. The special-shaped spacecraft lifting device according to claim 1, characterized in that: Reinforcing ribs are respectively arranged on the surfaces of the first support rod and the second support rod.

10. A special-shaped spacecraft lifting device, characterized in that: A lifting device for a special-shaped spacecraft comprising the lifting device for a special-shaped spacecraft as described in any one of claims 1 to 9.

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