Abstract: To satisfy the requirements of whole-spacecraft isolation, a new semi-active isolation platform is presented using a magneto-rheological (MR) damper as the semi-active actuator. A sleeve anti-shaking structure is designed to increase the transverse and bending stiffness. The finite element (FE) model of the platform is presented, followed by a study of the response of the isolation system to base excitation. Then, the detailed FE model of the whole-spacecraft isolation system is presented, and the impact of the new platform on the dynamic characteristics of the rocket is studied. The results show that the new platform is able to satisfy the requirements of whole-spacecraft isolation. Its isolation performance is affected by the dynamic characteristics of the rocket, but the influence is comparatively small when there exists high connecting stiffness between the rocket and the payload. When replacing the adopter with the new platform, the dynamic characteristics of the rocket show little change from firing to the first separation of the rocket and spacecraft.

Key words: whole-spacecraft isolation, isolation platform, anti-shaking structure, random response analysis, rocket-spacecraft coupling