The Design Of The Flexible Antenna Low-fre- Quency Vibration Isolation System And Dynamic Analysis

Satellite in orbit, because its environment is very complex, when disturbed from outside light pressure, temperature, gravity, etc. will cause the flexible antenna low frequency vibration. Meanwhile, the satellite body and the interior of eccentric attitude adjustment can cause low-frequency vibration. In order to avoid mutual coupling between the two low-frequency vibration, need to design a good performance of low frequency vibration isolator to meet the requirements. Although the metal spring isolator has a good low-frequency vibration isolation characteristics, but because of its small and not very good damping suppress resonance peaks; rubber isolator although having a large hysteresis damping characteristics, but its low-frequency vibration isolation performance poor; Study of a rubber article made of metal and a composite spring isolator, and to solve the two-way nature of the low-frequency flexible vibration isolation between the satellite body.Firstly, the mechanical model of rubber and metal spring, drawn spring deformation and aspect ratio curve and metal rubber constitutive equation, whereby the structure of the design parameters of vibration isolator. Patran and Nastran based software platform, the establishment of a three-dimensional model of a metal spring vibration rubber and finite element model to analyze each mode of vibration isolators, got isolator top 26 natural frequency and main vibration mode. Feasibility analysis by applying time-domain white noise excitation isolator response generated to verify the isolator.Then use Patran software, including the establishment of satellite body, a metal spring vibration rubber, flexible antenna and cable networks, satellite solar panels whole 3D models and multi-body dynamics model. Based MSC.Nastran software analyzes the whole star each mode, to get the first 26 natural frequencies and mode shapes master the entire star system. By applying a unit pulse excitation in three directions X. Y. Z, simulation analysis of the frequency domain response and there is no vibration isolator connected rigidly connected to the flexible antenna to the top node, and the entire star system response. Calculation of the flexible antenna to the top node in the isolation rate of three directions, the results showed that:isolator of 2.344Hz,3.32Hz,4Hz,6.6Hz. four resonance frequencies have good vibration isolation performance. Among them, the best isolation effect z direction, the vibration transfer rate compared with non-rigid connection isolators were reduced by 65%,86.53% 62.5%(2.344Hz),99.91%?99.56%?99.93%(3.32Hz),85.12%.89.27%,89.13%(4Hz), 90.72%?93.17%?30.83%(6.6Hz). x to the second, the vibration transmission rate decreased 11.48%?66.73%?0.078%(2.344Hz),66.88%?99.41%?99.32%(3.32Hz)?56.55%? 66.47%?65.54%(4Hz),79.29%?94.55%?94.07%(6.6Hz). y to less effective vibration isolation and vibration transmission rate increase was observed at 2.344Hz and 4Hz, the reason is that the y direction perpendicular to the solar wings, was severely affected solar wings vibration during vibration, However, the maximum vibration peak of 0.52,1.00 and incentive peak is still relatively large attenuation, therefore, the overall design of the isolator isolation effect good.