Multi-VCHP (Variable Condenser Heat Pipe) Radiator

Advanced Cooling Technologies, Inc (ACT) will develop a high turndown ratio, freeze tolerant and passive Variable Heat Rejection Radiator for Planetary Surface and Space Habitats based on multiple Non-Integrated Hot Reservoir Variable Conductance Heat Pipes (HR-VCHPs). Habitat waste heat is acquired by a single-phase loop (SPL) using a benign fluid and further transferred to a series of these VCHPs charged with ammonia (or propylene depending on freezing and toxicity requirements) and argon (or neon, again, depending on the freezing requirements) that in turn transfer the heat (with self-adjusting resistance) to the radiators for ultimate rejection. In addition, the HR-VCHPs, that mainly consist of aluminum extrusions, will be flexible/deployable because of stainless steel bellows inserted as adiabatic sections that act as thermal barriers during survival. To develop the proposed system ACT will leverage concepts developed during several previous SBIR programs. One of them is the high reliability Non-Integrated HR-VCHP as the key component that was recently developed by ACT and successfully tested (both thermal control and reliability) on Peregrine 1 Lander in microgravity. This success elevated its TRL to 8. The primary Phase I objective is to demonstrate the feasibility of the concept by analysis, modeling, design and experimental validation. ACT will develop a four-HR-VCHP radiator prototype that will cool a single-phase pumped loop. One of the VCHPs will be flexible to demonstrate deployability. In addition, a preliminary design of a single-phase pumped loop to VCHP evaporator heat exchanger will be developed. The main objective in Phase II will be to demonstrate a full-scale Passive Non-integrated HR-VCHP Radiator system by designing, building and testing a full-scale proof of concept system elevating the TRL to 6. ACT will conduct a series of trade studies for different configurations potentially drifting away from the base-line design obtained in Phase I.

The immediate NASA application of this technology is the Artemis program as well as future human exploration vehicles, designed for planetary surface and/or deep space missions. These missions require thermal control systems capable of operating at fractions of their design heat load in the cold environment of both planetary surface and deep space. In addition, this technology could be used as passive thermal control system for any spacecraft designed to operate in deep space. Future commercial space stations, planetary habitats and pressurized rovers are among potential beneficiaries of the proposed technology. The proposed system could also cool the cold ends of planetary (FSP-like) and space (JETSON-like) nuclear power systems. The concept is commercially attractive, as it builds upon proven technologies and offers high-reliability, scalability, low mass, no control power, high turndown ratio and minimum survival power.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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.