Erosion Rate Measurements for DART Spacecraft Ion Propulsion System

The Double Asteroid Redirection Test (DART) spacecraft was developed to provide the first measurement for orbital deflection of an asteroid upon intentional impact. NEXT ion engine is part mission, on its maiden voyage. As pre-launch risk reduction, erosion characteristics extraction grid system were evaluated using laser measurements sputtered molybdenum atoms over envelope potential throttle conditions mission. Erosion rate dependence propellant flow as well relative density and directionality sputter from center edge measured. Sputtered found have average radial velocity directed toward perimeter increasing with distance. contribution source facility background gas other sources accelerator current examined influence several operating parameters. Facility operation more than a wall-mounted pressure gauge typical assumptions about ingestion would indicate. Far-field flux estimated full angular range based near-field results relying quartz crystal microbalance data at one location fix absolute numbers everywhere. substantially deepen knowledge understanding complex process lifetime, failure via normal life limiter. Study are also relevant thruster–spacecraft integration issues such deposition solar cells surfaces.