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Dynamic Design of Vibration Isolation and Attenuation System for Small Spacecrafts

Author: ZhangYeWei
Tutor: FangBo
School: Harbin Institute of Technology
Course: General and Fundamental Mechanics
Keywords: small satellite whole-spacecraft vibration isolation local vibration attenuation vibration transmissibility dynamic design
CLC: V423.4
Type: Master's thesis
Year: 2009
Downloads: 138
Quote: 1
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Abstract


The vibration environment of the spacecraft during launching is much worse than that when during its orbital movement. The whole-spacecraft vibration isolation technology and the spacecraft local vibration attenuation can improve the dynamic environment of the spacecraft. The whole-spacecraft vibration isolation can isolate the vibration loads transferred to the satellite, while the local vibration attenuation can satisfy the demand of some sensitive elements of the satellite. The dynamic design problems of the whole-spacecraft vibration isolation and the spacecraft local vibration attenuation are studied in this dissertation.The fundamental theory of the spacecraft vibration isolation and attenuation is discussed first. The whole-spacecraft vibration isolation technology for small satellite is studied. The natural frequencies and the modal damping ratios of the isolation system are analyzed. The vibration transmissibility of the isolation system is calculated. The dynamic design and the structural design of the system are completed.The real modals and complex modals of the isolation system are analyzed and the dynamic parameters of the system are obtained. The whole-spacecraft vibration isolation for small satellite is designed. By comparing the dynamic modals of the satellite with and without the isolation system, we found that the first order longitudinal natural frequency and the first order transverse natural frequency are both decreased. Based on some special points of the satellite, the frequency response analysis is conducted and the simulation results show that the isolation can restrain the vibration of the whole satellite. The method of this paper can isolate the vibration both in longitudinal and transverse directions.The problem of the local vibration control for small satellite is studied at last. Two strategies, adding dynamic vibration absorber or constrained damping layers, are used to attenuate the local vibration. The simulation results indicate that the two designs are both good for the vibration attenuation, and they can be applied to the spacecraft vibration attenuation practically.

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Rocket, the spacecraft structure (overall ) > Spacecraft design and construction of > Satellite
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