NASA GRC Cathode Development: Challenges and Future Work
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Jon Mackey↗
Engineering topics
Tim Gray
Publications and source records attributed to Tim Gray.
Effects of Environmental Exposure on Barium Oxide Cathode Operation
Hollow cathode assemblies (HCA) are typically designed around a cylindrical emitter for the electron source. Barium oxide (BaO) emitters are one type of emitter commonly used, which consists of a porous tungsten matrix impregnated with a mixture of barium oxide, calcium oxide, and alumina. Barium oxide emitters are susceptible to poisoning by a variety of substances, including oxygen, water vapor, carbon dioxide, and air. Poisoning can occur both during operation and exposure during storage. Water vapor is the primary contaminant of concern with ground exposure, and has been historically controlled by appropriate storage and handling procedures. Over the past several years, NASA Glenn Research Center (GRC)has been testing BaO cathodes to observe the effects on cathode operation after extended environmental exposures
electric propulsion↗
PPE Electric Propulsion Advancing to CDR: 12kW String
String level testing is a vital part of electric propulsion development. With the Power and Propulsion Element (PPE) spacecraft flying two new models of Hall Thrusters, this work is even more critical. PPE will have both 6kW and 12kW thruster strings onboard, all powered by Maxar power processing units (PPU). Both strings have recently undergone end-to-end string level hot fire testing to verify the ability of all components to work together. This entails operating the thruster with the Xenon Flow Controller (XFC) and PPUs under both nominal and off-nominal conditions to stress the system and determine weak points. Such testing has long been a standard Maxar practice since our first 1.5kW electric propulsion system in 2004. This paper will focus on Phase 1 of the 12kW testing recently completed at NASA Glenn. The primary conclusion of the test effort was that the 12kW string operated nominally and that the PPU and XFC could operate the thruster within specifications.
Electric propulsion↗
Technology Demonstration Mission Solar Electric Propulsion Annual Review
The Solar Electric Propulsion (SEP) project is developing and qualifying an advanced 12 kW Electric Propulsion (EP) thruster to the Power and Propulsion Element (PPE) requirements, which are applicable to human/robotic exploration and commercial spaceflight missions.
Clayton Kachele↗
Technology Demonstration Mission Solar Electric Propulsion Annual Review
The Solar Electric Propulsion (SEP) project is developing and qualifying an advanced 12 kW Electric Propulsion (EP) thruster to the Power and Propulsion Element (PPE) requirements, which are applicable to human/robotic exploration and commercial spaceflight missions.
Clayton Kachele↗
NASA Progress on the Development and Qualification of a 12-kW Hall-Effect, Solar Electric Propulsion Thruster
The National Aeronautics and Space Administration (NASA) continues to evolve the human exploration approach for beyond low-Earth orbit and in a manner involving international, academic, and industry partners. The center of this approach is NASA’s Gateway program that will establish a permanent human presence in lunar orbit for human cislunar science, operations, and lunar surface access to eventually land the next American astronauts on the south pole of the Moon. In support of the effort, NASA’s Space Technology Mission Directorate (STMD) began a project to increase the state of the art for the Hall-Effect Solar Electric Propulsion (SEP) technology. The resulting Advanced Electric Propulsion System (AEPS) project has developed a 12 kW Hall-effect thruster in support of the Gateway program. The project is managed by the NASA Glenn Research Center (GRC), supported by the NASA Jet Propulsion Laboratory (JPL) with development, qualification & flight hardware all supplied by L3 Harris Aerojet Rocketdyne (AR). Development of the 12-kW Hall thruster electric propulsion system began with maturation of the Hall Effect Rocket with Magnetic Shielding (HERMeS) Technology Demonstration Units (TDUs). The technology development was then transitioned to AR via the AEPS contract, which built and tested two Engineering Test Unit (ETU) thrusters and multiple critical components. The project transitioned to the production of the three flight thrusters and entered qualification testing at the component and thruster levels.
Electric Propulsion↗