&lt;p&gt;The proposed research will develop novel enabling thermal management technology addressing subsystem (on-board processing and electronics thermal management) as well as spacecraft level design. The proposed validated prototype system would achieve the following engineering advantages:(1) EHD/capillary-driven thermal management system with low mass/volume and power consumption which limits the total power dissipation required of the thermal subsystem; (2) high heat transfer coefficient mechanism using thin film evaporation to maximize the heat rejection temperature and reduce the required radiator area; (3) self-regulating and smart fluid management to permit heat rejection from an arbitrary surface to the lowest available temperature sink.&lt;/p&gt;&lt;p&gt;The current state of? the art for electronics thermal control, wherein thermal control hardware is remotely ?integrated and requires relatively massive, voluminous and power consuming resources?as well as large temperature differences to? serve as the driving potential transferring? dissipated heat. &amp;nbsp;These characteristics impede ?the goal of capable, efficient, and?miniaturized on-board processing systems. Furthermore, processing capability is limited by thermal control considerations, such as the amount of heat rejected, the heat flux along the path of heat rejection, and the temperature difference between? the electronics components and the thermal sink. Thus, technologists seek to integrate the thermal management? solution directly into the chip layout, substrate structure,?and/or package design. This will substantially? boost the cooling performance, while introducing? significant reduction in the package size, and requiring? much smaller overall system temperature driving potential:?a 3-D integrated solution that is lighter, more compact, and?capable of greater heat transport. In addition, a? two-phase device would provide thermal uniformity, reducing thermal stresses and thus enhancing overall?component reliability.&lt;/p&gt;&lt;p&gt;Functionally, this ?concept will reduce the thermal resistance? between the chip and the radiator, raising? the heat rejection temperature with little cost? in power consumption. The net effect is to ?increase the available temperature for heat rejection, presenting the spacecraft with the advantages of increased power levels and/or reduced radiator mass and volume. The prototype TMS hardware will consist of an integrated heat sink chip embedded hybrid EHD/capillary-driven fluid management device that would ensure liquid supply and system self- regulation at the evaporative surfaces.&lt;/p&gt;