Composite damping device and vibration isolation and noise reduction system of spacecraft

Abstract

The utility model relates to the technical field of damping vibration attenuation, in particular to a composite vibration attenuation device and a vibration isolation and noise reduction system of a spacecraft, the composite vibration attenuation device is installed between a first component and a second component and comprises a first damping assembly and a second damping assembly, the first damping assembly comprises a damping rod and a container, and the second damping assembly comprises a second damping rod and a third damping rod. The first damping assembly comprises a first component and a second component, the second damping assembly comprises a container, the container is filled with particle damping, the damping rod is connected with the first component, the container is connected with the second component, the damping rod stretches into the container to make contact with the particle damping and is movably connected with the container, and the two ends of the second damping assembly are connected with the first component and the second component respectively. The composite damping device can effectively isolate vibration under high-frequency vibration and adaptively increase the damping coefficient under low-frequency vibration so as to restrain resonance. The utility model discloses a vibration isolation and noise reduction system of a spacecraft. The composite vibration reduction device is used for connecting a control moment gyroscope and a bay support.

Description

Technical Field

[0001] The utility model relates to the technical field of damping and vibration reduction, and more specifically, to a composite vibration reduction device and a vibration isolation and noise reduction system for a spacecraft. Background Art

[0002] In some devices, vibrations may occur between different components, which may affect the accuracy of the device or cause damage to the device. Therefore, vibration reduction is required. The commonly used damping and vibration reduction structure is formed by connecting a damping block and a structural member, which has a relatively stable damping coefficient and provides a certain axial stiffness while achieving the vibration reduction effect to ensure reliable connection between components. In the prior art, in order to ensure sufficient axial stiffness, a damping structure with a small damping coefficient is usually adopted. However, in some working scenarios, the vibration state of the device will change greatly. Although a small damping coefficient has a good blocking effect on high-frequency vibrations, it will generate a large resonance amplification factor for low-frequency vibrations, resulting in resonance and unstable connection between components. The existing damping structure cannot ensure effective vibration isolation at high frequencies and suppression of resonance at low frequencies. Summary of the Utility Model

[0003] To overcome the problem that the damping structure in the above prior art cannot ensure effective vibration isolation at high frequencies and suppression of resonance at low frequencies, the utility model provides a composite vibration reduction device, which can effectively isolate vibrations at high frequencies and adaptively increase the damping coefficient at low frequencies to suppress resonance.

[0004] To solve the above technical problems, the technical solution adopted by the utility model is: a composite vibration reduction device is installed between a first component and a second component. The composite vibration reduction device includes a first damping component and a second damping component. The first damping component includes a damping rod and a container filled with particle damping. One end of the damping rod is connected to the first component, and the container is connected to the second component. The other end of the damping rod extends into the container to contact the particle damping and is movably connected to the container. Both ends of the second damping component are respectively connected to the first component and the second component.

[0005] In the technical solution of the present utility model, the damping rod of the first damping assembly is in contact with the particle damping in the container, and the magnitude of its damping coefficient is positively correlated with the displacement of the damping rod. During high-frequency vibration, the displacement of the damping rod in the container is small, and the damping coefficient of the first damping assembly is small. During low-frequency vibration, the displacement of the damping rod in the container is large, and the damping coefficient of the first damping assembly is large. The second damping assembly has a stable damping coefficient. Through the second damping assembly, effective vibration isolation can be achieved under high-frequency vibration and stable connection between components can be ensured. At this time, the damping coefficient of the first damping assembly can be ignored. Under low-frequency vibration, the damping coefficient of the first damping assembly will increase to avoid a large resonance amplification factor caused by a low damping coefficient, thereby ensuring the stability of the connection. Therefore, the composite vibration damping device of the present utility model can achieve vibration isolation with a small and stable damping coefficient during high-frequency vibration, and increase the damping coefficient during low-frequency vibration to suppress resonance.

[0006] Further, a plurality of blocking rods in contact with the particle damping are radially connected to the part of the damping rod located in the container. In this solution, the blocking rods extending radially can increase the contact with the particle damping and improve the damping and vibration reduction effect.

[0007] Further, the particle damping is silicone rubber particles, which have good damping effects.

[0008] Further, the composite vibration damping device further includes a transverse groove spring. The transverse groove spring is sleeved on the container. A chute extending axially is provided on the outer surface of one end of the transverse groove spring. The first component is connected with a limiting member, and the limiting member is axially slidably connected in the chute. The other end of the transverse groove spring is connected with the second component. In this solution, the transverse groove spring with an axially opened chute can improve the axial stiffness without affecting the performance of the first damping assembly.

[0009] Further, the chute is annular and axially provided on the circumferential surface of the transverse groove spring. The limiting member has an annular limiting portion, and the limiting portion is axially slidably connected in the chute. In this solution, the annular chute and the annular limiting portion are not easily separated, and the connection is more stable.

[0010] Furthermore, the composite vibration damping device further includes an anti-sway component, which includes an anti-sway sleeve, an anti-sway ejector rod, and a ball. The anti-sway sleeve is connected to the first component, the anti-sway ejector rod is connected to the second component. An installation groove is formed in the anti-sway sleeve, and the end of the anti-sway ejector rod is movably connected to the installation groove. A first ball groove is axially formed in the part of the anti-sway ejector rod located in the installation groove, and a second ball groove is axially formed in the installation groove of the anti-sway sleeve. The ball is rollingly installed between the first ball groove and the second ball groove. In this solution, the anti-sway component can provide stable lateral stiffness, and at the same time, the ball can minimize the axial frictional resistance as much as possible without affecting the vibration isolation effect.

[0011] Furthermore, a limiting shoulder for preventing the ball from falling off is respectively provided at the end of the anti-sway ejector rod and at the outlet of the installation groove of the anti-sway sleeve. In this solution, the ball is restricted in the ball groove by the limiting shoulder to prevent the ball from falling off.

[0012] Furthermore, the second damping component includes damping blocks, side connection plates, and a middle connection plate. There are two damping blocks which are respectively connected to both sides of the middle connection plate. The other sides of the two damping blocks are respectively connected with the side connection plates, and the other sides of the two side connection plates are respectively connected to the first component and the second component. In this solution, the two damping blocks are connected in series through the side connection plates and the middle connection plate, which can improve the damping effect.

[0013] The present utility model also provides a vibration isolation and noise reduction system for a spacecraft, including at least one group of any one of the above composite vibration damping devices, wherein the first component is a control moment gyro, the second component is an isolation cabin support, and the composite vibration damping device is installed between the control moment gyro and the isolation cabin support. In this solution, the composite vibration damping device can effectively attenuate the high-frequency micro-vibrations during the on-orbit operation stage of the control moment gyro, and at the same time, suppress the resonance amplification factor generated by the low-frequency disturbance vibration of the control moment gyro.

[0014] Furthermore, the vibration isolation and noise reduction system further includes at least one group of locking and releasing devices. One end of the locking and releasing device is connected to the control moment gyro, and the other end is connected to the isolation cabin support. The locking and releasing device includes an upper support block and a lower support block. The lower support block is movably sleeved with the upper support block through a fiber rope loop, and a hot knife component is clamped in front of the lower support block. In this solution, the locking and releasing device can provide an axial pre-tightening force and does not affect the vibration isolation and noise reduction effect between the control moment gyro and the isolation cabin support after release.

[0015] Compared with the prior art, the beneficial effects of the present utility model are:

[0016] For the composite vibration damping device of the present utility model, the damping rod of the first damping component is in contact with the particle damping in the container, and the magnitude of its damping coefficient is positively correlated with the displacement of the damping rod. During high-frequency vibration, the displacement of the damping rod in the container is small, and the damping coefficient of the first damping component is small. During low-frequency vibration, the displacement of the damping rod in the container is large, and the damping coefficient of the first damping component is large. The second damping component has a stable damping coefficient, and its connection between the first component and the second component can provide basic axial stiffness and damping effect, so as to effectively isolate vibration under high-frequency vibration and ensure stable connection between components. Under low-frequency vibration, the damping coefficient of the first damping component will increase to avoid a large resonance amplification factor caused by a low damping coefficient, thereby ensuring the stability of the connection. Therefore, the composite vibration damping device of the present utility model can achieve vibration isolation with a small damping coefficient during high-frequency vibration and suppress resonance with a large damping coefficient during low-frequency vibration. Description of the Drawings

[0017] Figure 1 is a schematic diagram of the overall structure of the vibration isolation and noise reduction system of the spacecraft of the present utility model;

[0018] Figure 2 is an enlarged cross-sectional view of part A of the present utility model;

[0019] Figure 3 is an enlarged view of part B of the present utility model;

[0020] Figure 4 is a schematic diagram of the structure of the first damping component of the present utility model;

[0021] Figure 5 is a cross-sectional view of the first damping component of the present utility model;

[0022] Figure 6 is a cross-sectional view of the anti-sway component of the present utility model;

[0023] Figure 7 is a schematic diagram of the structure of the cabin support of the present utility model.

[0024] In the drawings: 100, the first component; 200, the second component; 300, the control moment gyro; 400, the cabin support; 1, the first damping component; 11, the damping rod; 12, the container; 121, the cavity body; 122, the flange end cover; 13, the particle damping; 14, the blocking rod; 2, the second damping component; 21, the damping block; 22, the side connecting plate; 23, the middle connecting plate; 3, the cross-slot spring; 31, the chute; 4, the anti-sway component; 41, the anti-sway sleeve; 42, the anti-sway ejector rod; 43, the ball; 44, the limiting shoulder; 45, the reinforcing rib; 46, the connecting flange; 5, the locking and releasing device; 6, the limiting member; 61, the limiting part. Detailed Embodiments

[0025] The accompanying drawings are only for illustrative purposes and should not be construed as limiting the present patent; for a better illustration of the present embodiment, some components in the accompanying drawings may be omitted, enlarged or reduced, which do not represent the dimensions of the actual product; for those skilled in the art, it is understandable that some well-known structures and their descriptions in the accompanying drawings may be omitted. The positional relationships described in the accompanying drawings are only for illustrative purposes and should not be construed as limiting the present patent.

[0026] In the accompanying drawings of the embodiments of the present utility model, the same or similar reference numerals correspond to the same or similar components; in the description of the present utility model, it should be understood that if there are terms such as "upper", "lower", "left", "right", "long", "short", etc. indicating the orientation or positional relationship, they are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the terms describing the positional relationship in the accompanying drawings are only for illustrative purposes and should not be construed as limiting the present patent. For those of ordinary skill in the art, the specific meanings of the above terms can be understood according to specific circumstances.

[0027] The technical solutions of the present utility model will be further specifically described below through specific embodiments in conjunction with the accompanying drawings:

[0028] Embodiment 1

[0029] Refer to Figure 2 and Figure 5 , this embodiment discloses a composite vibration damping device, which is installed between a first component 100 and a second component 200. The composite vibration damping device includes a first damping component 1 and a second damping component 2. The first damping component 1 includes a damping rod 11 and a container 12. The container 12 is filled with particulate damping 13. One end of the damping rod 11 is connected to the first component 100, and the container 12 is connected to the second component 200. The other end of the damping rod 11 extends into the container 12 to contact the particulate damping 13 and is movably connected to the container 12. Both ends of the second damping component 2 are respectively connected to the first component 100 and the second component 200. Optionally, the damping rod 11 and the first component 100 may be connected by threads, and the container 12 and the second component 200 may be connected by bolts.

[0030] Among them, the container 12 can be formed by connecting multiple parts. For example, in this embodiment, the container 12 includes a cavity body 121 and a flange end cover 122. An opening is provided on one side of the cavity body 121 facing the second component 200, and the flange end cover 122 is fixedly sealed outside the opening. The flange end cover 122 is bolted to the second component 200. A through hole is provided on the other side of the container 12 away from the flange end cover 122, and the damping rod 11 passes through the through hole and enters the cavity body 121 to contact the particle damping 13. Preferably, there can be an annular gap of 0.5 mm between the damping rod 11 and the through hole, and this gap plays a role in venting air to prevent the first damping assembly 1 from being damaged due to air pressure changes when going from the ground to space. The two ends of the second damping assembly 2 are respectively bolted to the first component 100 and the second component 200. The second damping assembly 2 can adopt a damping assembly in the prior art, for example, it is composed of a damping block connected to a structural member.

[0031] In this embodiment, the first damping assembly 1 generates an adaptively adjusted damping coefficient, and the second damping assembly 2 generates a stable damping. The damping rod 11 of the first damping assembly 1 contacts the particle damping 13 in the container 12, and the generated damping magnitude is positively correlated with the displacement of the damping rod 11. During high-frequency vibration, the displacement of the damping rod 11 in the container 12 is small, and the damping generated by the first damping assembly 1 is small. During low-frequency vibration, the displacement of the damping rod 11 in the container 12 is large, and the damping generated by the first damping assembly 1 is large. Therefore, vibration isolation is achieved with a smaller damping during high-frequency vibration, and resonance is suppressed with a larger damping during low-frequency vibration.

[0032] Reference Figure 2 and Figure 5 , in this embodiment, a plurality of blocking rods 14 in contact with the particle damping 11 are radially connected to the part of the damping rod 11 located in the container 12. Specifically, the blocking rods 14 are evenly distributed radially on the damping rod 11, which can further increase the contact area with the particle damping 13 in the container 12 and improve the damping effect.

[0033] In this embodiment, the particle damping 13 is silicone rubber particles, preferably the aerospace special silicone rubber ZN-35 with a frequency-variable damping effect. Of course, in other embodiments, particles made of some other damping materials can be selected.

[0034] In this embodiment, the particle damper 13 fills the container 12, and the particle damper 13 is compressed by 10% to 25%. Defining the way of filling the container in the compressed state of the particle damper as overfilling, overfilling can be achieved by filling the container 12 with the particle damper 13 and further squeezing the internal space of the container 12. For example, the container 12 of this embodiment includes a cavity body 121 and a flange end cover 122. An opening is provided on one side of the cavity body 121 facing the second component 200, and the flange end cover 122 is fixedly sealed outside the opening. A boss is provided on the side of the flange end cover 122 facing the cavity body 121. When the flange end cover 122 is installed on the cavity body 121, the boss can further squeeze the particle damper 13 in the cavity body 121 to achieve overfilling. In some special working environments, such as in the weightless state in space, overfilling is beneficial to overcome the problem of insufficient contact of particles in the weightless state in space.

[0035] Reference Figure 2 , in this embodiment, the second damping assembly 2 includes damping blocks 21, side connection plates 22 and an intermediate connection plate 23. There are two damping blocks 21, which are respectively connected to both sides of the intermediate connection plate 23. The other sides of the two damping blocks 21 are respectively connected with side connection plates 22, and the other sides of the two side connection plates 22 are respectively connected to the first component 100 and the second component 200. Specifically, the side connection plates 22 at both ends can be respectively connected to the first component 100 and the second component 200 by bolts. The ability to suppress high-frequency vibration can be further improved by two series-connected damping blocks 21. The material of the damping block 21 is preferably aerospace special silicone rubber ZN-35 with frequency-variable damping effect, and the side connection plates 22 and the intermediate connection plate 23 can be made of aluminum alloy.

[0036] Embodiment 2

[0037] Reference Figure 1 、 Figure 2 、 Figure 4 and Figure 5 , this embodiment is similar to Embodiment 1. The difference is that the composite vibration damping device of this embodiment further includes a transverse groove spring 3. The transverse groove spring 3 is sleeved on the container 12. A chute 31 extending axially is provided on the outer surface of one end of the transverse groove spring 3. The first component 100 is connected with a limiting member 6, and the limiting member 6 is slidably connected to the chute 31 axially. The other end of the transverse groove spring 3 is connected to the second component 200. When there is no large axial impact between the first component 100 and the second component 200, the limiting member 6 is movably connected in the chute 31, so there is no acting force between the limiting member 6 and the transverse groove spring 3. When a large impact force is generated between the first component 100 and the second component 200, the limiting member 6 slides to the end in the chute 31, and the impact force causes the limiting member 6 to tighten the transverse groove spring 3, playing a role in increasing the axial stiffness and being able to protect the first damping assembly 1 from being damaged by the impact force.

[0038] Reference Figure 4 and Figure 5 In this embodiment, the sliding groove 31 is annular and circumferentially formed on the circumferential surface of the transverse groove spring 3. The limiting member 6 has an annular limiting portion 61, and the limiting portion 61 is slidably connected to the sliding groove 31 along the axial direction. Specifically, the limiting member 6 can be formed by two semi-circular snap rings, and each semi-circular snap ring is respectively bolted to the first component 100, which facilitates the installation of the annular limiting portion 61 into the annular sliding groove 31. Since the sliding groove 31 and the limiting portion 61 are arranged annularly, the limiting member 6 can surround the transverse groove spring 3 along the outer circumference, so that the limiting member 6 will not fall off from the sliding groove 31 radially, improving the connection stability. When there is no large axial impact, the limiting portion 61 can be in the middle position of the sliding groove 31, for example, 1 mm to 2 mm away from both sides of the sliding groove 31, so that the transverse groove spring 3 does not generate a force. When a large impact force is received, the first component 100 moves significantly, and the limiting portion 61 of the limiting member 6 contacts the end of the sliding groove 31 to resist the impact force.

[0039] Embodiment 3

[0040] Reference Figure 1 、 Figure 3 and Figure 6 This embodiment is similar to Embodiment 2, the difference is that the composite shock absorption device of this embodiment further includes an anti-sway assembly 4. The anti-sway assembly 4 includes an anti-sway sleeve 41, an anti-sway ejector rod 42 and a ball 43. The anti-sway sleeve 41 is connected to the first component 100, the anti-sway ejector rod 42 is connected to the second component 200. An installation groove is formed in the anti-sway sleeve 41, and the end of the anti-sway ejector rod 42 is movably connected to the installation groove. A first ball groove is axially formed in the portion of the anti-sway ejector rod 42 located in the installation groove, and a second ball groove is axially formed in the installation groove of the anti-sway sleeve 41. The ball 43 is rollingly installed between the first ball groove and the second ball groove, and the ball 43 is in rolling contact with the anti-sway sleeve 41 and the anti-sway ejector rod 42. Limiting shoulders 44 for preventing the ball 43 from falling off are respectively provided at the end of the anti-sway ejector rod 42 and the outlet of the installation groove of the anti-sway sleeve 41.

[0041] Specifically, the anti-sway sleeve 41 has a connecting flange 46 on the side facing the first component 100, and the anti-sway push rod 42 also has a connecting flange 46 on the side facing the second component 200. Bolts are used to connect the connecting flanges 46 to the first component 100 and the second component 200 respectively. Reinforcing ribs 45 are also provided on the back of the connecting flange 46 to enhance the structural load-bearing capacity. When a lateral moment is generated between the first component 100 and the second component 200, the anti-sway sleeve 41 will transmit it to the anti-sway push rod 42 through the balls 43, avoiding affecting the working accuracy of the first component 100. Moreover, the balls 43 can reduce the friction existing during the axial relative movement between the anti-sway sleeve 41 and the anti-sway push rod 42, reducing the influence on the vibration isolation effect. The balls 43 can roll axially in the ball grooves, and the anti-sway sleeve 41 and the anti-sway push rod 42 have a certain amount of movable displacement in the axial direction, ensuring stable load-bearing while not affecting the vibration reduction effect. The anti-sway sleeve 41, the anti-sway push rod 42, and the balls 43 can all be processed from 30CrMnSiA high-strength steel material.

[0042] Embodiment 4

[0043] Reference Figures 1 to 7 , this embodiment discloses a vibration isolation and noise reduction system for a spacecraft, including at least one set of the composite vibration reduction devices in Embodiment 1 and / or Embodiment 2, where the first component 100 is a control moment gyro 300, the second component 200 is an inter-module support 400, and the composite vibration reduction device is installed between the control moment gyro 300 and the inter-module support 400.

[0044] Specifically, four sets of composite vibration reduction devices can be provided between the control moment gyro 300 and the inter-module support 400. The four sets of composite vibration reduction devices are evenly distributed around and form a pairwise opposite layout. The inter-module support 400 is welded from 5A06 or 2A14T6 aluminum alloy, and its lower end face is fixed to the spacecraft shell. During the orbital operation stage of the spacecraft, the vibration isolation and noise reduction system has a large damping in the low-frequency band to suppress resonance and a small damping in the high-frequency band to achieve efficient vibration isolation. Therefore, it can isolate the micro-vibrations generated during the operation of the control moment gyro 300 from affecting the cabin, prevent the generation of high-energy noise from affecting the health of astronauts, and prevent interference with the operation of precision components inside the spacecraft.

[0045] In some alternative embodiments, since the composite vibration reduction device is provided with a transverse groove spring, it ensures the ability of the spacecraft to cope with axial large impact loads during the launch stage and improves the connection safety.

[0046] In some alternative embodiments, since the composite vibration reduction device is provided with an anti-sway assembly, it ensures the ability of the spacecraft to cope with lateral impact loads during the launch stage, improves the connection safety, and does not affect the damping effect of the composite vibration reduction device.

[0047] ReferenceFigure 1 , in this embodiment, it further includes at least one set of locking and releasing device 5. One end of the locking and releasing device 5 is connected to the first component 100, and the other end is connected to the second component 200. The locking and releasing device 5 includes an upper support block and a lower support block. The lower support block is movably sleeved on the upper support block through a fiber rope loop, and a hot knife assembly is clamped on the front side of the lower support block.

[0048] Specifically, four sets of locking and releasing devices 5 can be provided between the first component 100 and the second component 200, and they are evenly distributed around like the composite vibration damping device. The locking and releasing method of the first component 100 is a thermal cutting unlocking method with the characteristic of low impact. Therefore, the locking and releasing device 5 includes a lower support block, a hot knife assembly, a fiber rope loop, and an upper support block. The locking and releasing device 5 includes a lower support block. The lower support block is movably sleeved on the upper support block through a fiber rope loop, and a hot knife assembly is clamped on the front side of the lower support block. The lower support block and the upper support block are processed and manufactured with titanium alloy materials, the fiber rope loop is wound with ultra-high molecular weight polyethylene fibers, and the hot knife assembly can perform thermal cutting on the fiber rope loop under the control of the satellite control system, so as to unlock and release the first component 100. For the locking and releasing device 5, reference can be further made to Chinese Patent CN117759679A, which will not be elaborated here.

[0049] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, rather than limiting the implementation manners of the present invention. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to enumerate all the implementation manners here. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the present invention shall be included in the protection scope of the claims of the present invention.

Claims

1. A composite vibration reduction device, installed between a first component (100) and a second component (200), characterized in that: The invention comprises a first damping component (1) and a second damping component (2), wherein the first damping component (1) comprises a damping rod (11) and a container (12), wherein the container (12) is filled with a particle damping (13), one end of the damping rod (11) is connected to the first component (100), and the container (12) is connected to the second component (200), the other end of the damping rod (11) extends into the container (12) to contact the particle damping (13) and is movably connected to the container (12), and the two ends of the second damping component (2) are respectively connected to the first component (100) and the second component (200).

2. The composite vibration damping device according to claim 1, characterized in that: The portion of the damping rod (11) located in the container (12) is radially connected to a plurality of blocking rods (14) in contact with the particle damping (13).

3. The composite vibration damping device according to claim 1, characterized in that: The particle damping (13) is silicone rubber particles.

4. The composite vibration damping device according to claim 1, characterized in that: The first damping assembly (1) further comprises a transverse groove spring (3), wherein the transverse groove spring (3) is sleeved on the container (12), wherein an outer surface of one end of the transverse groove spring (3) is provided with a slide groove (31) extending in the axial direction, wherein the first component (100) is connected to a limiting component (6), wherein the limiting component (6) is axially slidably connected in the slide groove (31), and the other end of the transverse groove spring (3) is connected to the second component (200).

5. The composite vibration damping device according to claim 4, characterized in that: The slide groove (31) is annular and is circumferentially opened on the circumferential surface of the transverse groove spring (3); the limiting member (6) has an annular limiting portion (61); and the limiting portion (61) is axially slidably connected in the slide groove (31).

6. The composite vibration damping device according to claim 1, characterized in that: The composite vibration reduction device also includes an anti-sway component (4), the anti-sway component (4) including an anti-sway sleeve (41), an anti-sway top rod (42) and a ball (43), the anti-sway sleeve (41) is connected to the first component (100), the anti-sway top rod (42) is connected to the second component (200), a mounting groove is provided in the anti-sway sleeve (41), an end of the anti-sway top rod (42) is movably connected to the mounting groove, a first ball groove is axially provided in the portion of the anti-sway top rod (42) located in the mounting groove, a second ball groove is axially provided in the mounting groove of the anti-sway sleeve (41), and the ball (43) is rollingly installed between the first ball groove and the second ball groove.

7. The composite vibration damping device according to claim 6, characterized in that: The end of the anti-sway top rod (42) and the exit of the installation groove of the anti-sway sleeve (41) are respectively provided with a limiting shoulder (44) for preventing the ball (43) from falling off.

8. The composite vibration damping device according to any one of claims 1 to 7, characterized in that: The second damping assembly (2) comprises a damping block (21), a side connecting plate (22) and a middle connecting plate (23); the damping block (21) is provided with two and is respectively connected to two sides of the middle connecting plate (23); the other sides of the two damping blocks (21) are respectively connected to the side connecting plates (22); and the other sides of the two side connecting plates (22) are respectively connected to the first component (100) and the second component (200).

9. A vibration isolation and noise reduction system for a spacecraft, characterized in that: The invention comprises at least one group of composite vibration reduction devices as described in any one of claims 1 to 8, wherein the first component (100) is a control moment gyro (300), the second component (200) is a bulkhead support (400), and the composite vibration reduction device is installed between the control moment gyro (300) and the bulkhead support (400).

10. The vibration isolation and noise reduction system for a spacecraft according to claim 9, characterized in that: The vibration isolation and noise reduction system also includes at least one set of locking and releasing devices (5), one end of the locking and releasing device (5) is connected to the control moment gyro (300), and the other end is connected to the compartment support (400), the locking and releasing device (5) includes an upper support block and a lower support block, the lower support block is movably connected to the upper support block through a fiber rope loop, and a hot knife assembly is clamped on the front side of the lower support block.

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