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Maglev nonlinear vibration isolator of satellite sensitive load and design method

A technology of sensitive load and design method, applied in the direction of shock absorber, magnetic spring, mechanical equipment, etc., can solve the problem of inappropriate vibration isolation, and achieve the effect of simple structure, good manufacturability and stable magnetic field

Inactive Publication Date: 2015-09-02
SHANGHAI SATELLITE ENG INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

But this invention is not applicable to the vibration isolation of low frequency large stiffness and high frequency small stiffness

Method used

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  • Maglev nonlinear vibration isolator of satellite sensitive load and design method
  • Maglev nonlinear vibration isolator of satellite sensitive load and design method
  • Maglev nonlinear vibration isolator of satellite sensitive load and design method

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Embodiment Construction

[0037] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0038] In this embodiment, the design method of the magnetic levitation nonlinear vibration isolator for the satellite sensitive load provided by the present invention includes the following steps:

[0039] Step 1: When the two magnets face each other with the same pole, the repulsive force increases when they are close to each other, and decreases when they are far away. The mutual repulsion force of the two magnets is

[0040] F = π ...

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Abstract

The invention provides a maglev nonlinear vibration isolator of satellite sensitive load. The maglev nonlinear vibration isolator comprises an output rod, an outer package, a first magnetic body, a second magnetic body and a third magnetic body, the first magnetic body, the second magnetic body and the third magnetic body are all arranged on the inner side of the outer package, the first magnetic body is fixed at the upper end of the outer package, the third magnetic body is fixed at the lower end of the outer package, and the second magnetic body is arranged between the first magnetic body and the third magnetic body and is opposite to the same in a same-polarity manner. The invention further provides a corresponding system and method. A mode that the magnetic bodies are serially connected is adopted, and the magnetic bodies are coaxial and move axially, so that deflection of angles of the magnetic bodies is avoided; a magnetic field is stable, so that vibration at other frequency can be avoided. The maglev nonlinear vibration isolator is nonlinear in rigidity.

Description

technical field [0001] The invention relates to the technical field of vibration isolation of satellite loads, in particular to a magnetic levitation nonlinear vibration isolator and a design method for satellite sensitive loads. Background technique [0002] With the development of aerospace technology, the performance and accuracy of imaging payloads and high-resolution optical payloads continue to improve, and the high-precision and high-stability payloads carried by satellites have higher and higher requirements for the stability of satellite platforms. The impact can no longer be ignored, and vibration isolation measures must be taken to ensure the normal operation of the satellite payload. [0003] The main vibrations of spacecraft are roughly divided into two categories: one is the frequency range of 30-250 Hz or more, which is characterized by a small excitation amplitude, called high-frequency small-amplitude vibration; the second type of vibration frequency is gene...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F16F6/00
CPCF16F6/00F16F2222/06
Inventor 钟鸣申军烽周徐斌刘兴天石新宇
Owner SHANGHAI SATELLITE ENG INST
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