Abstract
The LE111 thruster utilizes hydrazine and MON3 as fuel and oxidizer, and produces a thrust of 111 N at nominal operating conditions with an Isp of up to 328 s. The thruster is throttleable through the use of separate fuel and oxidizer metering valves and is able to transition to a hydrazine monopropellant mode at any point during its operation. Completed qualification testing has demonstrated a versatile operating box that includes chamber pressure - mixture ratio excursions, heated propellants up to 341K, and gaseous helium ingestion through propellant flow paths. Overall, the thruster has achieved 15,455 s of accumulated on-time and a maximum continuous burn time of 6,000 s. The thruster achieves its exceptional performance through a novel micro-coaxial gas-gas injection scheme and an innovative regeneratively cooled combustion chamber, which uses the oxidizer as the working fluid. This paper describes the thruster’s capabilities and performance recorded during the completed qualification testing, and briefly outlines the design.
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