Satellite flywheel compound vibration isolator

Abstract

The present application relates to a kind of satellite flywheel composite vibration isolator, including particle damping device, active vibration isolation device and control system, the particle damping device includes first vibration reduction spring, damping cavity, second vibration reduction spring, particle group;The active vibration isolation device includes connecting rod, piezoelectric sensor, piezoelectric actuator.Particle damping device is suitable for passive vibration isolation of space vibration isolator by special structure design, and the damping band is wider by friction energy dissipation and spring two-stage vibration reduction;Active vibration isolation device realizes low-frequency vibration isolation.The oblique arrangement of damping cavity and connecting rod can realize 6 degrees of freedom vibration isolation.The present application combines a variety of vibration isolation methods, and the vibration isolation effect is better with light mass, simple structure and convenient assembly.

Description

Technical Field

[0001] This invention belongs to the field of aerospace technology, specifically relating to a composite vibration isolator that can effectively reduce the vibration of satellite flywheels. Background Technology

[0002] In recent years, with the development of aerospace technology, satellite platforms have required higher pointing accuracy and attitude stability. Flywheel vibration is a significant interference factor affecting the pointing accuracy and stability of precision payloads on satellites. Flywheel vibration has a small amplitude, high frequency, and wide vibration bandwidth, which can excite multi-mode vibrations in satellites and affect optical satellite imaging.

[0003] Vibration isolation is the primary means of solving the aforementioned problems. Existing vibration isolation methods often employ passive isolation, which can suppress most high-frequency vibrations, but its effect on low-frequency vibrations is not significant. Isolation elements often use slotted springs or rubber components. The structure and size of slotted spring isolators cannot be made compact and lightweight; rubber isolators have a single direction, making multi-degree-of-freedom isolation difficult. While ordinary particle damping vibration isolation is widely used, it cannot be applied to the space environment because there is no gravity and no compression friction between particles. Active vibration isolation can suppress low-frequency vibrations, but the system is complex, consumes onboard resources, and occupies valuable weight and space. Therefore, combined active and passive vibration isolation is difficult to implement on satellites. How to select a reasonable structure and control design to effectively suppress flywheel micro-vibrations has become a crucial technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0004] To overcome the above-mentioned technical problems, the present invention provides a satellite flywheel composite vibration isolator, which is equipped with a particle damping device and an active vibration isolation device, combining the two vibration isolation methods to meet the vibration reduction requirements of the satellite flywheel.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] This invention provides a satellite flywheel composite vibration isolator, comprising: a particle damping device, an active vibration isolation device, an upper connecting plate, a lower connecting plate, and a control system. The particle damping device includes a first damping spring, a damping cavity, a second damping spring, and a particle cluster. The active vibration isolation device includes a connecting rod, a piezoelectric sensor, and a piezoelectric actuator. The control system is connected to the piezoelectric sensor and the piezoelectric actuator.

[0007] One end of the first damping spring is connected to the upper connecting plate, and the other end is connected to the damping cavity. The other end of the damping cavity is connected to the second damping spring, and the other end of the second damping spring is connected to the lower connecting plate. The stiffness of the first damping spring and the second damping spring may be different.

[0008] One end of the connecting rod is connected to the upper connecting plate, and the other end is connected to the lower connecting plate. The connecting rod is a bent rod, with a piezoelectric sensor installed at the upper part of the bent part and a piezoelectric actuator installed at the lower part. The stiffness of the bent part of the connecting rod should not be too large.

[0009] The damping cavity is a cylindrical cavity made of metal-silicone rubber. The damping cavity features a flexible design; two-stage springs provide pressure, compressing the particle group and causing it to move. This adapts to the weightless environment of space. Under pressure, the particles collide and rub against each other, and the collision and friction with the damping cavity walls dissipates vibration energy, meeting vibration isolation requirements.

[0010] The particle group consists of several spherical particles, and the particle material is either metal or non-metal.

[0011] The piezoelectric sensor and the piezoelectric actuator are made of piezoelectric material PVDF.

[0012] The piezoelectric sensor and piezoelectric actuator are connected to the control system by wires.

[0013] The first damping spring, the second damping spring, and the connecting rod are all arranged obliquely, forming an angle with the axis of the connecting plate on the vibration isolator.

[0014] The particle damping device and the active vibration isolation device are distributed at intervals and are evenly distributed relative to the periphery of the lower connecting plate.

[0015] The upper connecting plate is parallel to the lower connecting plate, the upper connecting plate is connected to the flywheel, and the lower connecting plate is connected to the honeycomb panel.

[0016] Compared with the prior art, the advantages of the present invention are as follows: 1. This invention combines the advantages of passive and active vibration isolation, achieving good results through multiple vibration reduction mechanisms, and has a wider range of applications; the oblique arrangement of the damping cavity and connecting rod can achieve 6-degree-of-freedom vibration isolation; 2. The reasonable combination of the two-stage damping springs in the particle damping device of the present invention makes the damping frequency band wider and the damping effect better, which can better meet the vibration isolation requirements of spacecraft; 3. The active vibration isolation device of the present invention is driven by intelligent materials and has the advantages of light weight, small size, simple structure, convenient assembly and low manufacturing cost; 4. This invention can be used independently or in combination. Each particle damping device and active vibration isolation device is independent and does not affect each other. If a single device fails, the entire device can still be used, providing fail-safety. The upper and lower connecting plates are parallel and have installation interfaces, resulting in uniform mass distribution, convenient installation, and saving satellite resources. Attached Figure Description

[0017] Figure 1 This is a three-dimensional schematic diagram of the present invention;

[0018] Figure 2 This is a top view of a three-dimensional schematic diagram of the present invention;

[0019] Figure 3 This is a partial cross-sectional view of the present invention;

[0020] Figure 4 This is a schematic diagram of the connecting rod.

[0021] In the diagram: 1-Upper connecting plate, 2-First damping spring, 3-Connecting rod, 4-Piezoelectric sensor, 5-Piezoelectric actuator, 6-Damping cavity, 7-Second damping spring, 8-Lower connecting plate, 9-Particle group, 10-Active vibration isolation device, 20-Particle damping device. Detailed Implementation

[0022] The specific embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0023] like Figures 1 to 3 As shown, the present invention discloses a satellite flywheel composite vibration isolator, mainly comprising: an upper connecting plate 1, a particle damping device 20, an active vibration isolation device 10, and a lower connecting plate 8. The particle damping device 20 includes: a first damping spring 2, a damping cavity 6, a second damping spring 7, and a particle cluster 9; the active vibration isolation device 10 includes: a connecting rod 3, a piezoelectric sensor 4, and a piezoelectric actuator 5.

[0024] The first damping spring 2 is connected at one end to the upper connecting plate 1 and at the other end to the damping cavity 6. The other end of the damping cavity 6 is connected to the second damping spring 7, and the other end of the second damping spring 7 is connected to the lower connecting plate 8. The stiffness of the first damping spring 2 and the second damping spring 7 may be different. The damping cavity 6 is a cylindrical cavity made of metal silicone rubber. The particle group 9 consists of several round particles, and the particle material may be metal or non-metal.

[0025] The flywheel vibration drives the upper connecting plate 1 and the lower connecting plate 8 to vibrate, thereby forcing the first damping spring 2 and the second damping spring 7 to extend and compress. The damping cavity 6 also extends and compresses accordingly. The particle group 9 within the damping cavity 6 collides and rubs against each other, as well as against the cavity wall, thus consuming energy and suppressing vibration. In the weightless environment of space, the particle group does not compress or rub against each other. The damping cavity 6 is made of silicone rubber. The combined compression of the two damping springs under the flywheel vibration causes the damping cavity 6 to expand and contract. This deformation forces the particle group 9 to collide and rub against the cavity wall, thus consuming energy. The appropriate combination of the two damping springs results in a wider damping frequency band.

[0026] One end of the connecting rod 3 is connected to the upper connecting plate 1, and the other end is connected to the lower connecting plate 8. For example... Figure 4The connecting rod 3 is a bent rod, with a piezoelectric sensor 4 installed at the upper part of the bent section and a piezoelectric actuator 5 installed at the lower part. The stiffness of the bent section of the connecting rod 3 should not be too large. The piezoelectric sensor and the piezoelectric actuator are made of piezoelectric material PVDF. The piezoelectric sensor and the piezoelectric actuator are connected to the control system by wires.

[0027] The flywheel vibration causes the upper connecting plate 1 and the lower connecting plate 8 to vibrate. Since the stiffness of the bent part of the connecting rod 3 is not high, the connecting rod 3 deforms. The piezoelectric sensor 4 collects the vibration acceleration signal of the bent part of the connecting rod 3 and transmits the signal to the control system. The control system feeds back to the piezoelectric actuator 5 of the same connecting rod 3 through the corresponding algorithm, so that it generates the action force to counteract the vibration of the connecting rod 3, suppress the vibration of the connecting rod 3, and thus ultimately suppress the flywheel vibration.

[0028] The particle damping device 20 and the active vibration isolation device 10 are distributed at intervals. The particle damping device 20 is mainly used for high-frequency vibration reduction, while the active vibration isolation device 10 is mainly used for low-frequency vibration reduction. Utilizing two different vibration reduction mechanisms results in better vibration reduction. Each particle damping device 20 is independent of the others, with no mutual influence or interference; if one fails, the others can still function normally. The particle damping devices 20 are arranged at an angle to the upper connecting plate 1, enabling multi-degree-of-freedom vibration isolation. Each active vibration isolation device 10 is also independent of the others, with no mutual influence or interference. Each connecting rod 3 can be independently controlled; if one fails, the others can still function normally. The connecting rod 3 is also arranged at an angle to the upper connecting plate 1, achieving multi-degree-of-freedom vibration isolation.

[0029] The particle damping device 20 and the active vibration isolation device 10 are both evenly distributed relative to the periphery of the lower connecting plate 8. The even distribution facilitates the independent operation of each particle damping device 20 and active vibration isolation device 10, resulting in a uniform mass distribution of the entire vibration isolator, which is convenient for connection with the flywheel.

[0030] The upper connecting plate 1 and the lower connecting plate 8 are parallel to each other and both have installation interfaces. The upper connecting plate 1 is connected to the flywheel, and the lower connecting plate 8 is connected to the honeycomb panel. The vibration isolator has a uniform mass distribution and is easy to install, which helps to save satellite resources. The vibration isolator can be used independently or in combination. It can achieve multi-degree-of-freedom vibration isolation when used independently, and the vibration isolation effect is even better when used in combination by designing a combined installation platform.

[0031] The above examples are intended to help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make various changes and modifications without departing from the concept of the present invention, and these all fall within the scope of protection of the present invention.

Claims

1. A satellite flywheel composite vibration isolator, characterized in that, The system includes a particle damping device (20), an active vibration isolation device (10), an upper connecting plate (1), a lower connecting plate (8), and a control system; wherein, the particle damping device (20) includes a first damping spring (2), a damping cavity (6), a second damping spring (7), and a particle group (9); one end of the first damping spring (2) is connected to the upper connecting plate (1), and the other end is connected to the damping cavity (6), the other end of the damping cavity (6) is connected to the second damping spring (7), and the other end of the second damping spring (7) is connected to the lower connecting plate (8), the first damping spring (2) and the second damping spring (7) have different stiffnesses; the active vibration isolation device (10) The system includes a connecting rod (3), a piezoelectric sensor (4), and a piezoelectric actuator (5); the control system is connected to the piezoelectric sensor (4) and the piezoelectric actuator (5); one end of the connecting rod (3) is connected to the upper connecting plate (1), and the other end is connected to the lower connecting plate (8). The connecting rod (3) is a bent rod, with the piezoelectric sensor (4) installed on the upper part of the bent part and the piezoelectric actuator (5) installed on the lower part; the damping cavity (6) is a cylindrical cavity made of metal silicone rubber; the damping cavity adopts a flexible design, with two-stage springs providing pressure. The damping cavity compresses the particle group, causing the particle group to move, adapting to the weightless environment of space. The particle group collides and rubs under pressure, and also collides and rubs against the damping cavity wall to consume vibration energy.

2. The satellite flywheel composite vibration isolator according to claim 1, characterized in that, The particle group (9) consists of several round particles, and the particle material is metal or non-metal.

3. A satellite flywheel composite vibration isolator according to claim 1, characterized in that, The piezoelectric sensor (4) and the piezoelectric actuator (5) are made of piezoelectric material PVDF.

4. A satellite flywheel composite vibration isolator according to claim 1, characterized in that, The first damping spring (2), the second damping spring (7), and the connecting rod (3) are all arranged obliquely, forming an angle with the axis of the connecting plate (1) on the vibration isolator.

5. A satellite flywheel composite vibration isolator according to claim 1, characterized in that, The particle damping device (20) and the active vibration isolation device (10) are distributed at intervals and are evenly distributed relative to the periphery of the lower connecting plate (8).

6. A satellite flywheel composite vibration isolator according to claim 1, characterized in that, The upper connecting plate (1) is parallel to the lower connecting plate (8). Both the upper connecting plate (1) and the lower connecting plate (8) have mounting interfaces. The satellite flywheel composite vibration isolator can be used independently or in combination.

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