This Phase I proposal is submitted to verify the materials and process engineering of the space environment stable, multifunctional Plasma Sprayable conductive thermal control material system (TCMS) that can be applied to space hardware and can enables the hardware to carry higher leakage current through co doping process engineering for the high electrical conductivity. An innovative space environmental stable TCMS concepts are suggested through AMSENG IRamp;D work for the multifunctional, low (alpha;S/epsilon;T) material systems that can meet these aggressive goals in cost effective, reliable manner especially to meet the needs identified in solicitation for: the coating to be robust in nature. It is anticipated that the coating be non contaminating and is not a trap for the contamination, and be cleanable; as well as its adhesion need to meet the requirement of the orbital conditions along with the need of no particle generation during the life time of the space hardware. The suggested efforts emphasize Plasma Sprayable Materials developments for the two material systems: the first one considers the Co Doping of the BaTiO3 - PBT-50trade; and processing of coating using plasma deposition. The second material system also plans to consider Co Doping using Nano Metallic inclusions in neutral and reducing atmosphere for the Li:GAOtrade;. These innovative approaches can provide the material technology solutions, which can allow higher leakage currents that may also help to defend against the natural solar storm events and provide the needed robustness. The past work and the IRamp;D suggests that the envisioned derived material systems can provide the needed reliable amp; validated TCMS in typical space environments of (LEO), (GEO) amp; beyond with the robustness that can define cleanability and no particle generation. The reliability goal for the robust conductive TCMS is to have a design life of gt; 10 years in LEO and gt; 15 years in GEO, with the hardware demonstration during phase II.nbsp;
