Additively Manufactured Bimetallic Combustion Chambers for Small Launch Vehicles

ASRC Federal Astronautics is pleased to present this Phase II-E proposal to expand the development of low cost, additively manufactured combustion chambers to include two new structural jacket materials: HR-1, a NASA-developed Fe/Ni superalloy with excellent hydrogen embrittlement resistance; and Scalmalloy, an Airbus-developed high-strength aluminum alloy tailored for modern additive manufacturing. Our current Phase II chamber design uses Inconel 625 to form the structural jacket, a material that is not well-suited for methane- and hydrogen-fueled combustors expected to be used by Lunar and Martian mission descent and ascent stage propulsion systems.

Lunar ascent propulsion Lunar descent propulsion Lunar gateway propulsion Mars Ascent Vehicle (MAV) propulsion Mars descent stage propulsion Small launch vehicle main propulsion

MDA upper stage target propulsion Commercial space nanolaunch vehicle propulsion

This is early/mid-stage (TRL 6) — 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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