Technical Paper
Orbital Thermal Analyses of “Rigidization-on-Command” (ROC) Materials for Inflatable Spacecraft
2001-07-09
2001-01-2220
This study addressed the space environment for typical orbits, development of UV curing cationic epoxy resin systems, mechanical properties of UV cured composites, and fabrication of demonstration tubes using the photocurable resin technology. Transient thermal analyses were run on a candidate tube configuration to determine the power required for internal UV lamps to initiate cure (15.50 W/m2) and the temperature range of the thermal processing windows.
