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A method for improving spacecraft attitude control performance and vibration isolation platform

A vibration isolation platform and attitude control technology, which is applied in attitude control, aerospace vehicle guidance devices, etc., can solve the problems of low natural frequency of vibration isolation platform, large resonance peak value, and high frequency vibration of vibration isolation platform.

Active Publication Date: 2016-08-10
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

For traditional spring-damper vibration isolation components, if the stiffness of the spring is too small, the natural frequency of the vibration isolation platform will be low, and the desired vibration isolation effect may not be achieved; if the stiffness is too large, the vibration isolation platform itself will It is easy to generate high-frequency vibration during work, and a large resonance peak will be generated in the case of high-frequency disturbance; the damping ratio of a single material in nature is usually less than 1, and traditional dampers will have the defect of slow attenuation in practical applications

Method used

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  • A method for improving spacecraft attitude control performance and vibration isolation platform
  • A method for improving spacecraft attitude control performance and vibration isolation platform
  • A method for improving spacecraft attitude control performance and vibration isolation platform

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Embodiment Construction

[0074] like figure 1 As shown, a vibration isolation platform for improving the attitude control performance of a spacecraft includes: an upper platform 1, a lower platform 3, and a strut 2 connecting the upper platform and the lower platform. like image 3 As shown, the middle section of the strut includes a positive stiffness part 5 and a negative stiffness part 6 . Positive stiffness means that the direction of the restoring force after the object is deformed is opposite to the direction of deformation, and is generally composed of elastically deformable materials. In this case, a metal rubber rod is used to realize it; negative stiffness refers to the direction of the restoring force and the direction of deformation of the object after deformation. Similarly, the principle of leverage is generally used so that the deformation direction of the deformation element is opposite to the deformation direction of the positive stiffness part. For example, the negative stiffness pa...

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Abstract

The invention relates to a method and a vibration isolation platform for improving spacecraft attitude control performance, in particular to a method for improving the imaging quality of optical loads by using a positive and negative stiffness technology and the vibration isolation platform, and belongs to the field of high-frequency vibration control. The vibration isolation platform comprises an upper platform, a lower platform and a supporting rod connected with the upper platform and the lower platform. The positive and negative stiffness technology is adopted for the supporting rod, and according to the technology, a very high damping ratio can be reached under the condition of common damping material, so that energy is consumed rapidly, and the purpose of improving the imaging quality of the optical loads is achieved.

Description

technical field [0001] The invention relates to a method for improving the attitude control performance of a spacecraft and a vibration isolation platform for realizing the method, in particular to a method for improving the attitude control performance of a spacecraft using positive and negative stiffness technology and a vibration isolation platform for realizing the method, belonging to the high-tech Frequency vibration control field. Background technique [0002] At present, the main vibrating components on spacecraft are actuators with high-speed rotors such as flywheels or control moment gyroscopes. Their vibration is mainly caused by the static and dynamic unbalance of the high-speed rotor and the installation error of the mechanical bearing, and the resulting vibration will directly affect the imaging quality of the optical load. Combined use of a design method for flywheel attitude control system of flexible aircraft (Geng Yunhai, Cui Hutao, Cui Haiying, Yang Di. D...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24B64G1/38G05D1/08
Inventor 郭子熙张尧汤亮关新陈亦东张景瑞翟光
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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