Far Field Plume Distribution and Divergence for NEXT: DART Mission

Abstract

In support of the Double Asteroid Redirection Test (DART) mission, laboratory measurements were made on the NEXT ion engine, which will be used for the spacecraft's inspace propulsion [1]. This study revisits a small range of mission-specific 2.7A throttle levels to understand the effect of in-flight flow rate variability, investigate intermediate throttle conditions, and improve measurement methodology. This paper specifically examines the farfield plume divergence and backflow ion flux distribution of the NEXT, while a companion paper examines the charge state distributions.

NEXT Ion Propulsion System Risk-Mitigation Tests in Support of the Double Asteroid Redirection Test (DART) Mission

“…The results of the Phase 1 diagnostic tests are presented in Refs. [10][11], and will be referenced as necessary within this document.…”