Ion Engine Systems Testing.
Abstract
Life testing of two 6750-second, specific impulse, advanced microthruster system flight models is reported. The systems included advanced design, zero-gravity feed systems, thermionic filament neutralizers, solid-state-control logic and power conditioning, stepped thrust vectoring, and thrust-level control. The first system was tested for 3481 hours primarily at 15 micropounds thrust with scheduled off periods, operation at 5 and 10 micropounds, and thrust vectoring. High accelerator electrode drain current, the sole malfunction, made operation marginal near the end of the test. The thruster was then modified by the addition of a variable-temperature accelerator electrode and was used as a diagnostic tool to investigate drain currents. The second system was operated for 452 hours primarily at 5 and 20 micropounds with off periods, at 10 and 15 micropounds, and thrust vectored. Occurrence of high drain currents precluded further systems testing; the system was modified and was used as a diagnostic tool for the investigation of the high drains. A third thruster subsystem was fabricated for experimental purposes. It was operated with a polished copper experimental accelerator and an aluminum accelerator. Results of diagnostic experiments are reported. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1970
- Accession Number
- AD0865350
Entities
People
- Edmund L. James
- Steven J. Goldner
Organizations
- Xerox