Whole-Spacecraft Isolation Platform With Its Dynamics And Performance Based On Electromagnetic Vibration Isolator

The satellite will suffer random excitation induced by rocket motor, the steady-state aerodynamic loadings and shock loads along with the stage separation, etc. Thus, it is necessary to investigate the vibration isolation approach for protecting the satellite in launch period. For the successful launching of a spacecraft, whole-spacecraft vibration isolation is widely applied to the satellite launching process for preventing the spacecraft from being damaged. In the beginning of the 1990 s, whole-spacecraft was first put forward. The main purpose is to build a new whole-spacecraft isolation platform to replace the traditional adapter whose stiffness is very large, or installed the vibration isolation platform between adapter and satellite. All the work is aimed to reduce the dynamic responses and ensure the successful launch of satellite. A novel whole-spacecraft isolation device is designed for the vibration isolation of the satellite. The follows are main contents and results of this paper.The working principle of electromagnetic vibration isolator is studied. The principle of the electromagnetic actuator is employed to the design of the single degree of freedom electromagnetic vibration isolation device. The active electromagnetic actuator can be used as a passive damper when short circuit of the coil. Electromagnetic actuator is manufactured and the experiment is taken on this prototype, the passive and active isolation performances of the Electromagnetic vibration isolator are tested in the experiment.A vibration isolation device based on stroke amplification principle is introduced during the design of the whole-spacecraft isolation platform. The principle of the amplification is studied for the device, and the dynamic responses have been carried on the device. The isolation performance is theoretically verified.The novel whole-spacecraft isolation device is designed with small space usage and light weight. The architecture and features of the system are introduced. The finite element method was employed to establish the dynamical model of the flexible spacecraft equipped with the isolation device. The natural characteristics of the system was analyzed, the natural frequencies and mode shapes were acquired.The dynamical responses are obtained numerically for the flexible spacecraft with and without the vibration isolators, respectively. The simulation results show that the novel whole-spacecraft vibration isolator, which can reduce the amplitude of vibration response of the spacecraft significantly, is valid for vibration suppression of the spacecraft. Isolation performance influenced by the damper orientation is discussed. Several configuration of suspension about dampers was raised. After comparing and analyzing of these different configurations, the final configuration is proposed.