SBIR Phase I: Liquid Oxygen (LOX) - Methane Engine for Small Satellite Launch Vehicles

Rocket Propulsion Systems Llc, Kent WA

Investigators

Abstract

The broader impact/commercial potential of this Small Business Innovation Research (SBIR) Phase I project is to significantly lower the capital barriers for new enterprises to participate as small satellite launchers and service providers, by offering high-performance rocket engines produced at the $100 K cost point. On the production side, this change would lead to a restructuring of space launch and satellite sector supply chains from the current high cost/low volume to a low-cost/high volume configuration as in the aircraft or automotive industries. Such a change could also provide a significant increase in high paying aerospace engineering and manufacturing jobs. On the customer end, once the small satellites reach the orbit, they could expand capabilities for military and civilian services in space, from surveillance and weather monitoring to completely new industries such as agricultural earth observation and climate change monitoring, or when combined into large constellations, provide wireless and mobile internet service globally to underserved populations. This Small Business Innovation Research (SBIR) Phase I project will boost the development of American-made, high-performance, reliable, high thrust-to-weight and low maintenance liquid rocket engines of 1.5-metric-ton thrust for small 50-180 kg satellite launch vehicles to 700 km Low Earth Orbit (LEO), using low-cost liquid oxygen (LOX) / methane (or liquified natural gas) propellants. A two-stage rocket would be propelled by a cluster of six such engines on its 1st stage, and a single vacuum-version of this engine on its upper stage. The small satellite business has been growing exponentially in the last few years, with the launch demand far outpacing supply. The annual demand/supply launch gap is expected to be in the 200-700 satellite range by 2026. The primary objectives of Phase I are to design and build the preburner and thrust chamber assembly and to design the turbopump assembly. The results from Phase I will provide data on the initial engine weight, manufacturability, production cost, and define the pace, risk posture, and resource needs for engine development. This award reflects NSF's statutory mission and has been deemed worthy of support through evaluation using the Foundation's intellectual merit and broader impacts review criteria.