| 摘要 |
Excitations from engines of the launch vehicles and the aerodynamics of flight produce large vibrations which are very detrimental to spacecraft during launch. Whole-spacecraft vibration isolation systems that greatly reduce the transmitted structure-borne vibrations to the spacecraft are disclosed. The disclosed devices, when combined together into an isolation system, provide vibration isolation for the complete spacecraft and are the only connection between the spacecraft and the launch vehicle. Devices that provide isolation in the axial (thrust) direction are disclosed. These devices consist of an arrangement of damped metallic flexures and machined springs, which provide relative flexibility in the desired direction. Passive damping is provided by compressing and shearing viscoelastic materials.
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