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Microsystems in Spacecraft Thermal Control 193

FIGURE 9.1 Microfabricated array of 300 500 mm louver array. The area below the
louvers has been removed using deep reactive ion etch (DRIE). The right picture shows
some of the louvers open, exposing the high emissivity surface below the substrate. (Cour-
tesy: JHU/APL.)

Closed Partially open Open

0.0 0.2 0.4 0.6 0.8 1.0
FIGURE 9.2 IR emissivity of the MEMS louver array with the louvers closed, partially open,
and open. (Courtesy: JHU/APL.)

technologies for future space missions whose primary objective will be to make
multiple simultaneous measurements of the harsh space environment near the
boundary of Earth’s protective magnetic field known as the magnetosphere. The
goal of NMP is to validate new technologies that will enable the reduction of
weight, size, and cost for future missions. ST5, the fourth deep space mission in
the NMP is designed and managed by NASA/GSFC and will validate four
‘‘enabling’’ technologies. Beside standard passive thermal control, these satellites
will carry two VEC experiments, one of them based on a MEMS technology
developed together by NASA/GSFC and JHU/APL. 12,13 These VEC experiments
are technology demonstrations and are not part of the thermal control system itself,
but rather independent experiments. ST5 is scheduled to launch in February of
2006. Given the limited time for prototype development, in part due to the turn-
around time in MEMS fabrication, development and the need for a reliable flight

© 2006 by Taylor & Francis Group, LLC