Abstract
This paper describes the development of a control system and associated technology for a microgravity isolation mount (MGIM)-a device to isolate sensitive scientific payloads on orbiting spacecraft from ambient vibration. The construction of the MGIM, and the specifications which it must satisfy, are briefly described; the control system which achieves this is described in more detail. A model for the MGIM is derived which includes the effect of asymmetric distribution of the payload mass. It is shown that this induces angular motion of the payload and violation of the tolerable microgravity level, unless counteracting control forces are produced. The technology required to support the concept is also described and the results of vibration tests conducted on a full-scale laboratory version of the MGIM are presented.
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