Low-Cost and Light-Weight Transpiration-Cooled Thrust Chambers

The proposed effort aims to evaluate the feasibility of using transpiration-cooled Titanium as the primary material in small-scale thrust chambers for in-space chemical propulsion applications in the 25-5,000lbf thrust class. This approach would allow for bipropellant thrust chambers that are almost 10-times lighter and significantly less expensive than current state-of-the-art radiatively-cooled refractory metal (e.g. Iridium / Rhenium) systems. In addition, since they are actively cooled, the proposed approach will allow for higher chamber pressures, thereby providing further reductions in thruster size and mass for performance improvement.

Potential non-NASA applications are expected to include maneuvering or orbit transfer thrusters for DoD spacecraft (particularly those for low-cost and responsive access to space). Further non-governmental applications could include lightweight apogee-kick motors for commercial satellites as well as use by integrators of small space propulsion systems for commercial missions and small-scale reusable vehicle developers.

NASA applications for the proposed systems are expected to include maneuvering or orbit transfer in science and exploration missions, RCS thrusters for in-space maneuvering, first stage and upper stage propulsion for nano-sat launch vehicles, and planetary lander ascent / descent engines.

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.

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