Satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources and vibration isolation frequency adjustment method thereof

Abstract

The present application relates to a kind of satellite adaptive micro-vibration suppression system and its vibration isolation frequency adjustment method for multi-sensitive load and multi-disturbance source, it is related to aerospace technology field.The system includes: satellite platform and the laser communication load vibration isolation system, optical camera vibration isolation system, flywheel vibration isolation system and central machine installed on the satellite platform;The system further includes: SADA vibration isolation system and solar wing connected on satellite platform by SADA vibration isolation system.The present application has the advantages of small size, light weight, vibration isolation frequency adjustable, relatively small energy consumption.By adjusting the vibration isolation frequency of different parts of the system, the sensitive load and the disturbance source of the whole satellite can meet the dynamic response requirements of the launch segment, and at the same time, the whole satellite can also meet the micro-vibration suppression requirements of the sensitive load in the on-orbit stage.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources and a vibration isolation frequency adjustment method thereof. BACKGROUND

[0002] With the continuous development of aerospace technology, the performance indicators of spacecraft are also continuously improved. For example, the resolution of Earth observation satellites is getting higher and higher. For example, the LANDSAT-1 satellite launched in 1972 has a resolution of 80m; the SPOT-1 satellite launched in 1986 has a resolution of 10m; and the WORLDVIEW-1 satellite launched in 2007 has a resolution of 0.5m. With the continuous improvement of resolution, the stability of the satellite platform is required to be higher and higher for optical remote sensing satellites. During the on-orbit operation of the optical remote sensing satellite, there are many disturbance sources, such as reaction flywheels, control moment gyroscopes, refrigerators, SADAs, etc. During imaging, these disturbance sources will cause the viewing axis of the sensitive load to vibrate, thereby deteriorating the imaging quality. Therefore, the disturbance sources on the satellite must be suppressed.

[0003] A typical micro-vibration suppression device includes a disturbance source isolator and an effective load isolator.

[0004] The disturbance source isolator includes a reaction flywheel, a momentum wheel, a CMG isolator, etc., and is usually installed between a single machine and a satellite body, such as the D-Strut momentum wheel isolator used by the Hubble telescope. Since the isolator has a low frequency, it is easy to cause fluctuations in the torque output by the flywheel, momentum wheel, and CMG, affecting the attitude stability of the whole satellite, so the isolation frequency generally cannot be too low.

[0005] The effective load isolator is installed between the sensitive load and the satellite body, and the frequency of such an isolator is generally low. It is usually locked during the launch phase, such as the improved D-Strut isolator used by the Tacsat-2 satellite, which is used to connect the optical load and the service cabin.

[0006] The isolation frequency of the above-mentioned micro-vibration suppression device is not adjustable or the adjustment range is limited, which brings three problems. First, it cannot meet the high stiffness requirement of the launch phase and the low frequency requirement of the on-orbit phase. Second, when there are multiple sensitive loads and multiple disturbance sources on the whole satellite, dynamic coupling may occur between them, affecting the normal operation of the sensitive load. Third, over time, the performance of the disturbance source will degrade due to friction and other factors, and the disturbance force generated will also increase, reducing the isolation efficiency of the isolator and affecting the normal operation of the sensitive load at the end of its life. SUMMARY

[0007] The present application aims to solve the technical problems in the prior art, and provides a satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple vibration sources and a vibration isolation frequency adjustment method thereof.

[0008] To solve the above technical problems, the technical scheme of the present application is as follows:

[0009] A satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple vibration sources comprises a satellite platform and a laser communication load vibration isolation system, an optical camera vibration isolation system, a flywheel vibration isolation system and a central machine installed on the satellite platform.

[0010] It also comprises a SADA vibration isolation system and a solar wing connected to the satellite platform through the SADA vibration isolation system.

[0011] Among them:

[0012] The optical camera vibration isolation system comprises an optical camera, a first acceleration sensor and a second acceleration sensor; the optical camera is installed on the satellite platform through a plurality of camera isolators; the first acceleration sensor and the second acceleration sensor are backups of each other, used to monitor the dynamic response at the camera and feed back the collected acceleration signals to the central machine.

[0013] The laser communication load vibration isolation system comprises a laser, a third acceleration sensor and a fourth acceleration sensor; the laser is installed on the satellite platform through a plurality of laser isolators; the third acceleration sensor and the fourth acceleration sensor are backups of each other, used to monitor the dynamic response at the laser communication load and feed back the collected acceleration signals to the central machine.

[0014] The flywheel vibration isolation system comprises a flywheel integrated support, an X-direction flywheel, a Y-direction flywheel and a Z-direction flywheel; the X-direction flywheel is installed on the flywheel integrated support through a plurality of X-direction flywheel isolators; the Y-direction flywheel is installed on the flywheel integrated support through a plurality of Y-direction flywheel isolators; the Z-direction flywheel is installed on the flywheel integrated support through a plurality of Z-direction flywheel isolators (307); the flywheel integrated support is installed on the satellite platform through a plurality of flywheel integrated support isolators (308).

[0015] The SADA vibration isolation system comprises a SADA; the SADA is installed on the satellite platform through four SADA isolators.

[0016] In the above technical scheme, the materials of the laser isolator, the camera isolator, the X-direction flywheel isolator, the Y-direction flywheel isolator, the Z-direction flywheel isolator and the flywheel integrated support isolator are respectively viscoelastic damping material, shape memory alloy or shape memory polymer material.

[0017] In the above technical scheme, the number of camera isolators is 8.

[0018] In the above technical solution, the number of laser vibration isolators is 8.

[0019] In the above technical solution, the number of X-direction flywheel vibration isolators is 4; the number of Y-direction flywheel vibration isolators is 4; the number of Z-direction flywheel vibration isolators is 4; and the number of flywheel integrated support vibration isolators is 4.

[0020] A vibration isolation frequency adjustment method of a satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources according to the above, comprising the following steps:

[0021] The frequency range of the vibration isolators in the satellite launch state and the in-orbit state under different service modes is derived according to the structural dynamics model, and the corresponding information of the frequency and temperature is stored on the central machine;

[0022] When the satellite is in the launch phase, the central machine controls the temperature of the camera vibration isolator, the X-direction flywheel vibration isolator, the Y-direction flywheel vibration isolator, the Z-direction flywheel vibration isolator, the flywheel integrated support vibration isolator and the SADA vibration isolator, so that the frequency of the camera vibration isolator, the X-direction flywheel vibration isolator, the Y-direction flywheel vibration isolator, the Z-direction flywheel vibration isolator, the flywheel integrated support vibration isolator and the SADA vibration isolator changes to the optimal frequency range derived in the launch phase, so that the responses at the flywheel and the camera meet the dynamic response requirements of the launch phase.

[0023] When the satellite is in the in-orbit phase, the first acceleration sensor, the second acceleration sensor, the third acceleration sensor and the fourth acceleration sensor collect the dynamic response at the camera, and compare it with the target acceleration a to obtain a difference Δa, and the central machine automatically controls the temperature of the camera vibration isolator, the X-direction flywheel vibration isolator, the Y-direction flywheel vibration isolator, the Z-direction flywheel vibration isolator, the flywheel integrated support vibration isolator and the SADA vibration isolator according to the difference Δa and the in-orbit state under different service modes, so that the frequency of the camera vibration isolator, the X-direction flywheel vibration isolator, the Y-direction flywheel vibration isolator, the Z-direction flywheel vibration isolator, the flywheel integrated support vibration isolator and the SADA vibration isolator changes to the optimal frequency range derived in the in-orbit phase, thereby meeting the micro-vibration suppression requirements of the camera.

[0024] The present application has the following beneficial effects:

[0025] The satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources has the advantages of small volume, light weight, adjustable vibration isolation frequency, and small energy consumption. BRIEF DESCRIPTION OF DRAWINGS

[0026] The application will be further described in detail below in combination with the drawings and specific embodiments.

[0027] Figure 1 A satellite diagram with multiple sensitive loads and multiple disturbance sources installed;

[0028] Figure 2 A satellite diagram only considering a flywheel and a camera;

[0029] Figure 3 A disturbance transmission rate curve diagram;

[0030] Figure 4 A structure diagram of the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources of the application;

[0031] Figure 5 A structure diagram of an optical camera vibration isolation system;

[0032] Figure 6 A structure diagram of a laser communication load vibration isolation system;

[0033] Figure 7 A structure diagram of a flywheel vibration isolation system;

[0034] Figure 8 A structure diagram of an SADA vibration isolation system;

[0035] Figure 9 A structure diagram of a variable vibration isolation frequency vibration isolator;

[0036] Figure 10 A flow diagram of the vibration isolation frequency adjustment method of the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources of the application;

[0037] Figure 11 An internal structure diagram of the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources of the application.

[0038] The reference signs in the figures are as follows:

[0039] 1 - satellite platform, 2 - optical camera vibration isolation system;

[0040] 201 - optical camera, 202 - camera vibration isolator, 203 - first acceleration sensor, 204 - second acceleration sensor;

[0041] 3 - flywheel vibration isolation system, 301 - flywheel integrated support, 302 - X-direction flywheel, 303 - X-direction flywheel vibration isolator, 304 - Y-direction flywheel, 305 - Y-direction flywheel vibration isolator, 306 - Z-direction flywheel, 307 - Z-direction flywheel vibration isolator, 308 - flywheel integrated support vibration isolator, 4 - central computer;

[0042] 5 - SADA vibration isolation system, 501 - SADA, 502 - SADA vibration isolator, 6 - laser communication load vibration isolation system;

[0043] 601 - laser, 602 - laser vibration isolator, 603 - third acceleration sensor, 604 - fourth acceleration sensor, 7 - solar wing. DETAILED DESCRIPTION

[0044] The inventive idea of the present application is that the present application proposes a satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources. The system can take into account the mechanical conditions of the satellite in the launch phase and in the on-orbit phase, so that the sensitive loads and the disturbance sources of the whole satellite meet the dynamic response requirements in the launch phase, and the whole satellite meets the working requirements of the sensitive loads in the on-orbit phase.

[0045] The micro-vibration suppression system comprises multiple sensitive load subsystems and multiple disturbance source subsystems. Each sensitive load and disturbance source subsystem is provided with a vibration isolator that can change with temperature.

[0046] The dynamic equations of the satellite in the launch phase and in the on-orbit phase are established. The influence of the frequency of each vibration isolator on the response at the sensitive loads and the disturbance sources when the satellite is in the launch phase is derived, and the optimal frequency range of each vibration isolator in the launch phase is obtained. The influence of the frequency of each vibration isolator on the working of the sensitive loads when the satellite is in the on-orbit phase is derived, and the optimal frequency range of each vibration isolator in different business modes (flywheel, SADA rotation speed) in the on-orbit phase is obtained. The correspondence between the optimal frequency range and the temperature of the vibration isolator is stored in the central computer on the satellite.

[0047] Two acceleration sensors are provided on each sensitive load, which are backup to each other, for monitoring the dynamic response at each sensitive load, and feeding back the collected acceleration signals to the central computer.

[0048] When the satellite is in the launching stage, the central machine controls the temperature of each vibration isolator, changes the frequency of each vibration isolator to the deduced optimal frequency interval in the launching stage, so that the dynamic response of the sensitive load and the disturbance source meets the response requirement in the launching stage.

[0049] When the satellite is in the on-orbit stage, the acceleration sensor collects the dynamic response of each sensitive load, and automatically controls the temperature of each vibration isolator according to the response size, changes the frequency of each vibration isolator to the deduced optimal frequency interval in the on-orbit stage, so as to meet the micro-vibration suppression requirement of the sensitive load.

[0050] The application will be described in detail below with reference to the accompanying drawings.

[0051] When the satellite is equipped with multiple sensitive loads and multiple disturbance sources, the system diagram is as shown in Figure 1 m0, m s1 ,..., m sn , m p1 ,..., m pm are the masses of the satellite platform 1, the disturbance source s1,..., the disturbance source sn, the sensitive load p1,..., the sensitive load pm, respectively, k0, k s1 ,..., k sn , k p1 ,..., k pm are the stiffness coefficients of the satellite platform 1, the disturbance source s1,..., the disturbance source sn, the sensitive load p1,..., the sensitive load pm, respectively, c0, c s1 ,..., c sn , c p1 ,..., c pm are the viscous damping coefficients of the satellite platform 1, the disturbance source s1,..., the disturbance source sn, the sensitive load p1,..., the sensitive load pm, respectively, F1,..., F n are the disturbance forces generated by the disturbance sources.

[0052] When the sensitive load only considers the optical camera, and the disturbance source only considers the flywheel, the satellite diagram is as shown in Figure 2 The motion differential equation of the double vibration isolation system is established as:

[0053]

[0054] The transfer rate of the disturbance force F is obtained by Laplace transformation on the above formula:

[0055]

[0056] In the formula, X3(s) is the Laplace transformation of x3, and F(s) is the Laplace transformation of F.

[0057] For the convenience of expression, the following dimensionless parameters are defined:

[0058]

[0059] where ω1, ω2and ω3are the frequencies of the flywheel, satellite platform 1 and camera subsystem respectively, which can be expressed as equation (4); ζ1, ζ2and ζ3are the viscous damping factors of the flywheel, satellite platform 1 and camera subsystem respectively, which can be expressed as equation (5).

[0060]

[0061] The force transmissibility curves when considering different frequency ratios are shown in Figure 3 . Wherein, γ1= γ2= 5 can be regarded as no damper for the flywheel and camera; γ1= 0.1, γ2= 5 can be regarded as a damper installed at the flywheel but no damper at the camera; γ1= 5, γ2= 0.1 can be regarded as a damper installed at the camera but no damper at the flywheel; γ1= γ2= 0.1 can be regarded as a damper installed at the flywheel and camera. It can be known from Figure 3 that the double vibration isolation system of the flywheel and camera has better damping effect than the system without isolation or single vibration isolation. Similarly, when the sensitive load is other load and the disturbance source is other single machine, the same conclusion can be obtained.

[0062] As shown in Figure 4 and 11 , an optical remote sensing satellite, ignoring the single machine without requirement for micro-vibration, includes: a satellite platform 1, an optical camera vibration isolation system 2, a flywheel vibration isolation system 3, a central machine 4, an SADA vibration isolation system 5, a laser communication load vibration isolation system 6 and a solar wing 7. The laser communication load vibration isolation system 6, the optical camera vibration isolation system 2, the flywheel vibration isolation system 3 and the central machine 4 are respectively installed on the satellite platform 1; the solar wing 7 is connected to the satellite platform 1 through the SADA vibration isolation system 5. Figure 11 In , in order to show the flywheel vibration isolation system 3 and the central machine 4, the SADA vibration isolation system 5, the laser communication load vibration isolation system 6 and the solar wing 7 are not shown.

[0063] As shown in Figure 5 , the optical camera vibration isolation system 2 includes: an optical camera 201, a camera damper 202, a first acceleration sensor 203 and a second acceleration sensor 204. The optical camera 201 is installed on the satellite platform 1 through the eight camera dampers 202. The first acceleration sensor 203 and the second acceleration sensor 204 are backup for each other, used to monitor the dynamic response at the camera, and feed back the collected acceleration signals to the central machine 4.

[0064] As shown in Figure 6As shown, the laser communication payload vibration isolation system 6 includes: a laser 601, laser vibration isolators 602, a third accelerometer 603, and a fourth accelerometer 604. The laser 601 is mounted on the satellite platform 1 via eight laser vibration isolators 602. The third accelerometer 603 and the fourth accelerometer 604 serve as backups for each other, used to monitor the dynamic response at the laser communication payload and feed back the acquired acceleration signals to the central unit 4.

[0065] like Figure 7 As shown, the flywheel vibration isolation system 3 includes: a flywheel integrated bracket 301, an X-axis flywheel 302, an X-axis flywheel isolator 303, a Y-axis flywheel 304, a Y-axis flywheel isolator 305, a Z-axis flywheel 306, a Z-axis flywheel isolator 307, and a flywheel integrated bracket isolator 308. The X-axis flywheel 302 is mounted on the flywheel integrated bracket 301 via four X-axis flywheel isolators 303; the Y-axis flywheel 304 is mounted on the flywheel integrated bracket 301 via four Y-axis flywheel isolators 305; the Z-axis flywheel 306 is mounted on the flywheel integrated bracket 301 via four Z-axis flywheel isolators 307; and the flywheel integrated bracket 301 is mounted on the satellite platform 1 via four flywheel integrated bracket isolators 308.

[0066] like Figure 8 As shown, the SADA vibration isolation system 5 includes: SADA 501 and SADA vibration isolators 502. SADA 501 is mounted on the satellite platform 1 via four SADA vibration isolators 502.

[0067] like Figure 9 The diagram shows a variable-frequency vibration isolator used in the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources according to the present invention. This isolator can be made of materials with adjustable stiffness, such as viscoelastic damping materials, shape memory alloys, and shape memory polymers. The laser vibration isolator 602, camera vibration isolator 202, X-axis flywheel vibration isolator 303, Y-axis flywheel vibration isolator 305, Z-axis flywheel vibration isolator 307, and flywheel integrated bracket vibration isolator 308 in this invention all adopt this structural form.

[0068] like Figure 10 As shown, the vibration isolation frequency adjustment method of the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources of the present invention includes the following steps:

[0069] Based on the structural dynamics model, the frequency range of the vibration isolator under different operating modes (flywheel, SADA speed) in the satellite launch state and on-orbit state is derived, and the corresponding information of frequency and temperature is stored on the central computer.

[0070] When the satellite is in the launch phase, the central computer 4 controls the temperature of each vibration isolator, changes the frequency of each vibration isolator to the deduced optimal frequency interval in the launch phase, so that the response at the flywheel and the camera meets the dynamic response requirements in the launch phase.

[0071] When the satellite is in the on-orbit phase, the acceleration sensor collects the dynamic response at the camera and compares it with the target acceleration a to obtain a difference Δa; the central computer 4 automatically controls the temperature of each vibration isolator according to the difference Δa and different on-orbit state business modes (flywheel, SADA rotating speed) to change the frequency of each vibration isolator to the deduced optimal frequency interval in the on-orbit phase, so as to meet the micro-vibration suppression requirements of the camera.

[0072] The satellite adaptive micro-vibration suppression system of the present application for multiple sensitive loads and multiple disturbance sources has the advantages of small volume, light weight, adjustable vibration isolation frequency, and small energy consumption. By adjusting the vibration isolation frequencies of different parts of the system, the sensitive loads and disturbance sources of the whole satellite can meet the dynamic response requirements in the launch phase, and at the same time, the whole satellite can also meet the micro-vibration suppression requirements of the sensitive loads in the on-orbit phase. In addition, by adjusting the frequencies of different vibration isolators, the optimal frequency interval can be obtained, so that the influence of the disturbance sources on the sensitive loads is minimized. When the disturbance forces generated by the disturbance sources change, or as time goes by, the performance of the disturbance sources degrades, the micro-vibration suppression system can automatically adjust the frequencies of different vibration isolators, thereby ensuring the normal operation of the sensitive loads.

[0073] Obviously, the above embodiments are only examples for the purpose of clarity, and are not limiting of the embodiments. Based on the above description, other different forms of changes or variations can be made by those of ordinary skill in the art. Here, it is not necessary and impossible to exhaust all the embodiments. The obvious changes or variations derived therefrom are still within the protection scope of the present application.

Claims

1. A method for adjusting the vibration isolation frequency of a satellite adaptive micro-vibration suppression system oriented towards multiple sensitive loads and multiple disturbance sources, characterized in that, Includes the following steps: Among them, the satellite adaptive micro-vibration suppression system for multiple sensitive loads and multiple disturbance sources includes: a satellite platform (1) and a laser communication load vibration isolation system (6), an optical camera vibration isolation system (2), a flywheel vibration isolation system (3) and a central machine (4) installed on the satellite platform (1). It also includes: the SADA vibration isolation system (5) and the solar array (7) connected to the satellite platform (1) via the SADA vibration isolation system (5); The optical camera vibration isolation system (2) includes: an optical camera (201), which is mounted on the satellite platform (1) via multiple camera vibration isolators (202); The laser communication load vibration isolation system (6) includes: a laser (601), a third accelerometer (603), and a fourth accelerometer (604); the laser (601) is mounted on the satellite platform (1) by multiple laser vibration isolators (602); The flywheel vibration isolation system (3) includes: a flywheel integrated bracket (301), an X-axis flywheel (302), a Y-axis flywheel (304), and a Z-axis flywheel (306); the X-axis flywheel (302) is mounted on the flywheel integrated bracket (301) by multiple X-axis flywheel isolators (303); the Y-axis flywheel (304) is mounted on the flywheel integrated bracket (301) by multiple Y-axis flywheel isolators (305); the Z-axis flywheel (306) is mounted on the flywheel integrated bracket (301) by multiple Z-axis flywheel isolators (307); and the flywheel integrated bracket (301) is mounted on the satellite platform (1) by multiple flywheel integrated bracket isolators (308). The SADA vibration isolation system (5) includes: SADA (501); SADA (501) is mounted on the satellite platform (1) via 4 SADA vibration isolators (502); The frequency range of the vibration isolator under different business modes of satellite launch and on-orbit status is derived based on the structural dynamics model, and the corresponding information of frequency and temperature is stored on the central computer (4). When the satellite is in the launch phase, the central unit (4) controls the temperature of the camera isolator (202), X-axis flywheel isolator (303), Y-axis flywheel isolator (305), Z-axis flywheel isolator (307), flywheel integrated bracket isolator (308), and SADA isolator (502) to change the frequency of the camera isolator (202), X-axis flywheel isolator (303), Y-axis flywheel isolator (305), Z-axis flywheel isolator (307), flywheel integrated bracket isolator (308), and SADA isolator (502) to the optimal frequency range of the launch phase, so that the response at the flywheel and camera meets the dynamic response requirements of the launch phase; When the satellite is in orbit, the first accelerometer (203), the second accelerometer (204), the third accelerometer (603), and the fourth accelerometer (604) collect the dynamic response at the camera and compare it with the target acceleration a to obtain the difference Δa. The central unit (4) automatically controls the temperature of the camera vibration isolator (202), the X-axis flywheel vibration isolator (303), the Y-axis flywheel vibration isolator (305), the Z-axis flywheel vibration isolator (307), the flywheel integrated bracket vibration isolator (308), and the SADA vibration isolator (502) according to the difference Δa and the different business modes of the in-orbit state. This causes the frequency of the camera vibration isolator (202), the X-axis flywheel vibration isolator (303), the Y-axis flywheel vibration isolator (305), the Z-axis flywheel vibration isolator (307), the flywheel integrated bracket vibration isolator (308), and the SADA vibration isolator (502) to change to the optimal frequency range derived during the in-orbit segment, thereby meeting the micro-vibration suppression requirements of the camera.

2. The vibration isolation frequency adjustment method according to claim 1, characterized in that, The optical camera vibration isolation system (2) also includes: a first acceleration sensor (203) and a second acceleration sensor (204); the first acceleration sensor (203) and the second acceleration sensor (204) are backups of each other, used to monitor the dynamic response at the camera and feed back the collected acceleration signal to the central unit (4); The third accelerometer (603) and the fourth accelerometer (604) serve as backups for each other, and are used to monitor the dynamic response at the laser communication payload and feed back the collected acceleration signals to the central unit (4).

3. The vibration isolation frequency adjustment method according to claim 1 is characterized in that, The materials of the laser vibration isolator (602), camera vibration isolator (202), X-axis flywheel vibration isolator (303), Y-axis flywheel vibration isolator (305), Z-axis flywheel vibration isolator (307) and flywheel integrated bracket vibration isolator (308) are respectively: viscoelastic damping material, shape memory alloy or shape memory polymer material.

4. The vibration isolation frequency adjustment method according to claim 1, characterized in that, The number of camera vibration isolators (202) is 8.

5. The vibration isolation frequency adjustment method according to claim 1, characterized in that, The number of laser vibration isolators (602) is 8.

6. The vibration isolation frequency adjustment method according to claim 1, characterized in that, The number of X-direction flywheel vibration isolators (303) is 4; The number of Y-direction flywheel vibration isolators (305) is 4; The number of Z-direction flywheel vibration isolators (307) is 4; The number of flywheel integrated bracket vibration isolators (308) is 4.

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