Thermal Design and Model Correlation of a Microgravity Vibration Isolation System for an International Space Station Facility

This paper describes the thermal design, analysis and test of a Microgravity Vibration Isolation System (MVIS) that will ensure the active isolation of the European Space Agency’s Fluid Science Laboratory (FSL) payload from vibration induced by the International Space Station (ISS) structure. The FSL is equipped with optical and electronic devices that are very sensitive to vibration, thermal distortion, temperature change and Electro Magnetic Interference (EMI). The MVIS has to provide a vibration attenuation of −40dB within the range of 0.1–100Hz without inducing thermal or electromagnetic interferences.

The sensitive FSL instruments are mounted in a floating structure called the Facility Core Element (FCE), whereas the rest of the FSL electronics, mechanics and cooling systems are fixed to the International Standard Payload Rack (ISPR). In order to minimize the FCE accelerations, the MVIS is composed of accelerometers, position sensors and magnets (attached to the FCE) that interact with coils controlled by the EU mounted on the ISPR.

The paper summarises the MVIS thermal design with respect to the FSL and MVIS performance and safety/durability requirements. It will also presents the MVIS thermal balance test results as well as the approach used to correlate the thermal model. Furthermore, the paper will describe the method used to calibrate the EU airflow of the FSL avionic air loop during the system integration and test campaign.