Chip-Integrated, Hybrid EHD/Capillary-Driven Thermal Management System is a two year that will leverage independently attained yet related prototype hardware advances for electronics thermal management into a ground breaking hybrid thermal control system for spacecraft applications.
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:
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. 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. 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.
Cross-cutting technology enables spacecraft system and subsystem miniaturization through tight thermal control. Embedded thermal control subsystems can improve electronics component reliability by reducing mechanical stresses and related hardware failure. The target technology application is CubeSat Missions; however, any technology advances are likely to be applicable to virtually any spacecraft mission.
Cross-cutting technology enables spacecraft system and subsystem miniaturization through tight thermal control. Embedded thermal control subsystems can improve electronics component reliability by reducing mechanical stresses and related hardware failure.
|Organizations Performing Work||Role||Type||Location|
|Goddard Space Flight Center (GSFC)||Lead Organization||NASA Center||Greenbelt, MD|
|University of Maryland, College Park||Supporting Organization||Academic|
|Worcester Polytechnic Institute||Supporting Organization||Academic||Worcester, MA|