TCV controlled LHPs can also be used in commercial and military satellites where the radiator sink conditions change, and there is a need to maintain the electronics within a narrow temperature band. The variable thermal link passively maintains the electronics temperature during cold sink conditions, such as during an eclipse. ACT produces LHPs for these satellites, and plans to use the technology developed in this program in its commercial product line. A second application is cooling of commercial and military aircraft components, specifically for UAVs. While operating at high altitudes during daytime, the LHP can reject the thermal load to the aircraft skin or forced convection sink. At cold night, the LHP passively shuts down, limiting the heat loss and maintaining the electronics temperature. One application for the TCV controlled LHP is thermal management for Lunar Landers and Rovers. An example is the Warm Electronics Box (WEB) and batteries for the NASA Anchor Node Mission for the International Lunar Network (ILN). The ILN could be powered by either solar or a radioisotope power system. The WEB and batteries face the same thermal challenges that require a variable thermal link to allow heat removal during daytime and heat preservation during nighttime. The integration of a TCV eliminates the electrical power consumption required to shut down a conventional LHP. Every 1 W of electricity saved translates to a mass saving of roughly 5kg for a solar powered system. Current Mars rover designs use a mechanically pumped single-phase fluid loop for thermal management. The proposed TCV controlled LHP could replace the mechanically pumped loop system with a complete passive system.