Lander Technology: LOX/CH4 Engine

Hotfire testing of a MSFC-developed 4500-lbf thrust regeneratively cooled LOX/CH₄ engine with additively-manufactured thrust chamber. Testing of the 4500-lbf thruster demonstrated methane-based regenerative cooling, verify performance, and anchor thermal models. The design can be scaled and fabricated for higher thrust levels (e.g. 100 kN / 22 klbf class engine). A parallel effort is underway with a 1000 lbf LOX/CH4 thruster with both additively-manufactured thrust chamber and injector.

This technology has potential application to human and robotic missions to the Moon and Mars. The benefits include enabling the development of space propulsion systems that use non-toxic ("green") propellants, potentially producible from space resources. Liquid oxygen/methane (LOX/CH₄) engines feature high performance including high specific impulse (Isp), and are being produced using new, lower-cost additive manufacturing techniques (3-D printing). These qualities improve the operability, affordability, and sustainability of space systems.

This is early/mid-stage (TRL 4) — 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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