Session
Technical Poster Session 10: Propulsion
Location
Utah State University, Logan, UT
Abstract
Ball Aerospace (Ball) and the Electric Propulsion Laboratory, Inc. (EPL) are in partnership to develop a high specific impulse electric propulsion system. The propulsion system is based on EPL’s Magneto-gradient Electrostatic Plasma 650-Watt (MEP 650) engine technology. The goal of the MEP 650 project is to develop a flight-like, engineering model (EM) MEP 650 system that can meet future Ball Small Satellite (SmallSat) mission requirements. These requirements are met by an engine that operates at a discharge power of 650 W in self-heating mode, attains a specific impulse of 1,500 seconds, a thrust of 29 mN, and processes about 7.0 kg of xenon propellant at full power.
To support the project efforts, two laboratory engines (EM1 and EM2), a power conditioning unit (PCS), a xenon flow system (XFS) and a MEP command, control, and telemetry (MCCT) unit have been built and tested. Laboratory engine EM1 is dedicated to endurance testing and has completed a 947-hour endurance test at 684 W, at an average discharge voltage of 258 volts. The EM2 engine is dedicated to support continued performance optimization and plasma plume investigations. EPL has completed the MEP system component design, structural and thermal testing, fabrication, and have extensively tested all components, including full system level “end-to -end” performance testing. Characterization of the EM2 engine has been conducted for discharge power levels up to 1 kW (any power level beyond 700 W requires the use of facility power supplies). The results to-date have exceeded the Ball (SmallSat) mission requirements and indicate a total MEP 650 engine efficiency of 35.5%, thrust of 30 mN, and specific impulse of 1,581 seconds at a discharge power of 650 W in self-heating mode. The MEP 650 system has completed all testing identified to achieve a Technology Readiness Level (TRL) 6.
Development Project Overview for MEP Engine Propulsion System for Small Satellites
Utah State University, Logan, UT
Ball Aerospace (Ball) and the Electric Propulsion Laboratory, Inc. (EPL) are in partnership to develop a high specific impulse electric propulsion system. The propulsion system is based on EPL’s Magneto-gradient Electrostatic Plasma 650-Watt (MEP 650) engine technology. The goal of the MEP 650 project is to develop a flight-like, engineering model (EM) MEP 650 system that can meet future Ball Small Satellite (SmallSat) mission requirements. These requirements are met by an engine that operates at a discharge power of 650 W in self-heating mode, attains a specific impulse of 1,500 seconds, a thrust of 29 mN, and processes about 7.0 kg of xenon propellant at full power.
To support the project efforts, two laboratory engines (EM1 and EM2), a power conditioning unit (PCS), a xenon flow system (XFS) and a MEP command, control, and telemetry (MCCT) unit have been built and tested. Laboratory engine EM1 is dedicated to endurance testing and has completed a 947-hour endurance test at 684 W, at an average discharge voltage of 258 volts. The EM2 engine is dedicated to support continued performance optimization and plasma plume investigations. EPL has completed the MEP system component design, structural and thermal testing, fabrication, and have extensively tested all components, including full system level “end-to -end” performance testing. Characterization of the EM2 engine has been conducted for discharge power levels up to 1 kW (any power level beyond 700 W requires the use of facility power supplies). The results to-date have exceeded the Ball (SmallSat) mission requirements and indicate a total MEP 650 engine efficiency of 35.5%, thrust of 30 mN, and specific impulse of 1,581 seconds at a discharge power of 650 W in self-heating mode. The MEP 650 system has completed all testing identified to achieve a Technology Readiness Level (TRL) 6.
