Quest has studied commercial applications of our Integrated MLI insulation. Terrestrial non-NASA applications of Load Responsive MLI (LRMLI) are much greater since LRMLI operates efficiently in-atmosphere with an integrated vacuum shell. We have had discussions with dewar and appliance (refrigerator/freezer) manufacturers, who have shown good interest in this early stage insulation technology. Hydrogen powered aircraft are currently in design, with a critical aspect cryotank storage of LH2. Ball Aerospace conducted a trade study of insulations for a High Altitude Long Endurance aircraft, and found LRMLI to be by far the best insulation with lower mass and significantly lower heat leak than SOFI or MLI with heavy vacuum shell. Extremely efficient thermal insulation would have use in commercial cryogenic applications such as cryogenic vessels and pipes in scientific and industrial applications. A major use is insulating LN2, LHe and LOX dewars for research and industrial uses. Other potential applications include large commercial tanks, industrial boilers and industrial hot and cold process equipment, refrigerated trucks and trailers, insulated tank, container and rail cars, liquid hydrogen fueled cars, appliances such as refrigerators and freezers, hot water heaters, mobile containers to keep foods hot or cold, marine refrigeration, potentially even house insulation. Load Responsive MLI (LRMLI) could provide dramatically improved thermal insulation for cryopropellant storage, especially during in-atmosphere launch and ascent. MLI has been identified as a high risk component for EDS and Altair vehicles. EDS requires minimal cryopropellant boiloff during launch and LEO operation. Altair also requires minimal losses during LEO and extended Lunar surface operations, and is difficult to top off prior to launch. Current thermal insulation designs use MLI, or SOFI/MLI combinations, and require purge systems to reduce losses and condensation in-atmosphere. Recent IRAD studies by Ball Aerospace indicate the total heat addition to the cryotank due to high heat leak of the purged and venting MLI is significant - up to 36% of heat leak for a 30 day mission. LRMLI could provide thermal insulation and integrated vacuum shell to insulate cryogenic systems on space instruments, satellites, spacecraft cabins and lunar surface habitats. LRMLI could provide micrometeorite protection. LRMLI should provide a high performance thermal insulation with adjustable thickness, mass and thermal conductance to fit mission requirements. It will provide inherent control of layer dimension and spacing, and should provide more predictable performance with less labor intensive assembly. It may be able to provide substantially longer term cryogenic storage, helping enable longer term manned space flights.