15th SYMPOSIUM ON SMALL SATELLITE MISSIONS (B4) Generic Technologies for Nano/Pico Platforms (6B)

摘要

On the road of the development of our first satellite, the NEE-01 PEGASUS, we encountered the need ofdeveloping a heat dissipation and transfer system to components that will need such heat in order to avoidfreezing while the satellite was in the eclipse part of its orbit.Many materials and many designs were tested in order to achieve the best thermal transfer rates asindicated by the specifications derived from extensive testing and from the manufacturing specifications ofour target components until we achieved the best results using multi walled carbon nanotube sheets tomanufacture a thermal transfer bus that met our needs.Such thermal transfer system will allow the spacecraft to route the internally generated heat, as well as anyheat coming from outside that our MLI allows to penetrate the external hull to be efficiently sink to ourfour battery arrays which we are using as thermal dissipation masses. In order ensure the survival of ourCOTS electronics longer than any other previous missions that have used this approach we designed aminiature version of a Multi Layer Insulation system, the requirements were to fend off up to 60% ofincoming heat, to protect the electronics against alpha and beta particles, to shield them from plasmadischarges and to attenuate most of X and gamma radiations. The result was the SEAM/NEMEA SpaceEnvironment Attenuation Manifold, a multi stage MLI capable of blocking alpha, beta, X and Gammaradiation and to block up 67% of incoming heat, while retaining internal heat over eclipse phase, NEMEAcan also attenuate and even neutralize EMP and Plasma discharge events.