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Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite

A technology for payloads and vibration isolators, applied in the direction of inertial effect shock absorbers, aerospace vehicle guides, etc. Deviation and other problems, to achieve the effects of not being affected by the space environment, reliable performance, and no leakage problems

Active Publication Date: 2012-06-06
TSINGHUA UNIV +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For ordinary vibrations, the impact of this gap on the vibration isolation performance is negligible, but the magnitude of vibration on the satellite platform is very small, and its amplitude is several microns, and the gap of the spherical joint will seriously affect the isolation of the vibration isolation system. Vibration performance, including making the natural frequency of the vibration isolation system deviate from the design value, making the damper unable to achieve the proper damping effect, and may cause additional collisions and impacts

Method used

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  • Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite
  • Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite
  • Multiple-degree-of-freedom vibration isolator and multiple-degree-of-freedom vibration isolating system for effective load and satellite

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Experimental program
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Effect test

Embodiment approach

[0021] Such as figure 1 As shown, the vibration isolator consists of a shell 1, an upper end cover 3 of the shell, a lower end cover 6 of the shell, a metal network material member 2, a moving guide rod 4, a fine-tuning spring 5, a flexible hinge 4-1 of the moving guide rod, and a flexible lower end cover. Hinge 6-1 composition.

[0022] The housing 1 is cylindrical, and the upper and lower ends are respectively fixedly connected with the upper end cover 3 of the housing and the lower end cover 6 of the housing;

[0023] The fine-tuning spring 5 is placed inside the housing 1, and its bottom end is fixedly connected with the lower end cover 6 of the housing;

[0024] The metal network material component 2 is a hollow cylinder, placed inside the housing 1, placed on the fine-tuning spring 5, and the outer periphery is fixedly connected to the inner wall of the housing 1;

[0025] The upper end cover 3 of the housing has a round hole, and the guide rod 4 penetrates through the...

Embodiment approach 1

[0031] Such as figure 2 As shown, the embodiment of the vibration isolation system is composed of several vertically installed vibration isolators 8 provided by the present invention installed between the existing mounts of the payload 9 and the corresponding satellite 7 supporting structures, the vibration isolators The quantity is based on the number of existing mounts for the payload. The upper and lower ends of the vibration isolator are respectively connected to the payload and the satellite platform through the flexible hinge 4-1 of the motion guide rod and the flexible hinge 6-1 of the lower end cover. For example, when the payload has 4 mounts, a vibration isolator can be placed between each mount and the satellite structure to achieve vibration isolation. The advantage of a vibration isolation system constructed in this way is that changes to existing payloads and satellite structures can be minimized.

[0032] According to the requirement of the payload for the is...

Embodiment approach 2

[0034] Such as image 3 As shown, the embodiment of the vibration isolation system is composed of six obliquely installed vibration isolators 8 provided by the present invention installed between the payload 9 and the satellite 7 . The six vibration isolators are divided into three groups, and each group consists of two vibration isolators to form an "eight" shape. Three sets of vibration isolators are evenly distributed on a circle and support the payload together. The upper and lower ends of the vibration isolator are respectively connected to the payload and the satellite platform through the flexible hinge 4-1 of the motion guide rod and the flexible hinge 6-1 of the lower end cover. The vibration isolation system constructed in this way has the advantage that each vibration isolator can work approximately in the state of axial tension and compression, and the lateral stiffness of the single-piece vibration isolator is not high, reducing the parameters of the single-piece...

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PUM

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Abstract

The invention belongs to the field of mechanical vibration isolation and particularly relates to a multiple-degree-of-freedom vibration isolator and a multiple-degree-of-freedom vibration isolating system for an effective load and a satellite. The multiple-degree-of-freedom vibration isolator provided by the invention consists of a casing, a motion guide rod, a metal wire network material member,flexible hinges, a fine tuning spring, an upper casing end cover and a lower casing end cover and has the advantages of compact structure, reliable performance, long service life and the like. The vibration isolating system consisting of the vibration isolator arranged according to a certain geometry configuration is arranged between the effective load and the satellite and can be used for isolating the vibration transmitted to the effective load from each direction of a satellite platform; and the vibration isolator is connected with the effective load and the satellite through the flexible hinges, and thus a gap, collision and the like are avoided.

Description

technical field [0001] The invention belongs to the field of mechanical vibration isolation, and in particular relates to a satellite payload multi-degree-of-freedom vibration isolator and a system. Background technique [0002] In recent years, with the development of aerospace technology, the resolution of earth observation and astronomical observation satellites is getting higher and higher. An important issue that follows is that the vibration generated by moving parts such as the attitude control flywheel and the tracking and scanning mechanism on the satellite platform has an increasing impact on the working quality of the payload. Although these vibrations are small in magnitude, they will blur the high-resolution images taken by the space camera and cannot achieve the expected working performance. The methods to solve this problem include vibration isolation of the vibration source and vibration isolation of the payload. However, since there are many vibration sour...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16F7/10B64G1/38
Inventor 郑钢铁关新王光远梁鲁曹东晶王伟刚王军唐绍凡陈祥
Owner TSINGHUA UNIV
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