Integrated Cryogenic Propellant Liquefaction System (I-CPLS)

Mainstream is developing an Integrated Cryogenic Propellant Liquefaction System (I-CPLS), with a projected mass of 192 kg, including heat rejection and contaminant mitigation, and power consumption of 10.3 kW when operating in a 225 K environment. Our lunar based I-CPLS liquifies oxygen (O2) (3.3 kg/h) and hydrogen (H2) (0.4 kg/h) simultaneously singular cooling system. In Phase I, Mainstream optimized the I-CPLS based on a representative lunar environment and developed refined component designs. The optimized I-CPLS is 3.8 % under the solicitation mass target and 31.3 % under the solicitation power target. The power system remains the dominant mass for this system. As a result of the lower power use, the power system is 31.3 % under the target for both solar and fission power systems. The net benefit of the I-CPLS is a total mass (liquefaction system plus power system) that is 1,492 kg (-28.4 %) or 670 kg (-23.7 %) under the solicitation total system target for solar and fission power systems, respectively, for a 225 K lunar environment. Additionally, the I-CPLS currently complies with the solicitation mass target. However, for each additional kilogram of I-CPLS mass allowed for reducing the rejection temperature reduces the total mass by has a 9.9 kg and 4.5 kg, for solar and fission power, respectively. In Phase II, Mainstream will completing flight-ready demonstration of key components of the I-CPLS which represent the greatest reduction in system risk. NASA is currently seeking an integrated refrigeration cycle for combining H2 and O2 liquefaction on the lunar surface. Production rates of liquid O2 and liquid H2 of at least 3.3 kg/h and 0.4 kg/h, respectively, are desired with a minimal weight and power consumption.  The proposed lunar-based Integrated Cryogenic Propellant Liquefaction System (I-CPLS) leverages an integrated cycle that liquifies O2 and H2 using a single cooling stream based on a modified Linde cycle. The I-CPLS system enables a significant reduction total mass (power plus liquefaction system) relative to the program targets. This will enable generation and fueling of launch vehicles on lunar surface. Additionally, the I-CPLS currently complies with the solicitation mass and power targets. However, for each additional kilogram of I-CPLS mass allowed for reducing the rejection temperature reduces the total mass by has a 9.9 kg and 4.5 kg, for solar and fission power, respectively. The objective of the proposed innovation (Phase I through Phase III) is to develop a weight and power optimized integrated liquefaction system for hydrogen and oxygen. In Phase I, we demonstrated the I-CPLS system achieved a 31.3% reduction in the power system size (10.3 kW) relative to the target (15.0 kW) while meeting the liquefaction system mass target (192 kg). Additionally, we determined the I-CPLS system is capable of removing reasonable levels of contaminants to the PPT level or less.  In Phase II we will design, fabricate, and demonstrate the low-pressure screw compressor which is a key enabling technology for mass reduction. To meet these objectives, we will refine the design conditions in cooperation with NASA, complete a full compressor design and fabrication package, fabricate and demonstrate the compressor. Finally, we will use the experimental results to refine the system level model to ensure the full system meets the program targets.

The I-CPLS is targeted at improvement in the cryogenic propellant liquefaction state of the art, in particular system weight reduction. This fills a need for ultra-lightweight and low power liquefaction system designs for lunar and Martian vehicle refueling systems. The I-CPLS is targeted at improvement in the cryogenic propellant liquefaction state of the art, in particular system weight reduction. This fills a need for ultra-lightweight and low power liquefaction system designs for lunar and Martian vehicle refueling systems.

This is early/mid-stage (TRL 3) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.