An Affordable, Hybrid-Electric Propulsion Architecture for Small Transfer Stages

QAM is pleased to present this proposal to demonstrate feasibility of an affordable O2/CH4 propulsion system architecture that is well suited for a small transfer stage that enables reliable ride share opportunities for cubesat development teams around the world. The uncomplicated multi-start architecture derives its affordability through a reliance upon the use of proven thruster technology and alternative fuel technology borrowed from the automotive industry. Namely, it uses a hybrid electric power cycle for both motive and electrical power, as well as low pressure (~500 psi) gas adsorption propellant tanks. As a result, the proposed architecture—called “HERA” (hybrid electric rocket assembly)—boasts high performance, (at least 340-sec delivered vacuum Isp) and much better propellant fraction than scaling laws predict (generally speaking, stage dry mass and achievable propellant fraction are directly proportional).

Small transfer stage propulsion Lunar and planetary lander ascent and descent propulsion

Missile defense divert and attitude control systems Payload bus propulsion

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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