Pulsed Inductive Thruster Development (Advanced Electric Propulsion Technology - High Thrust). Volume 2. Supplement.
Abstract
This report describes the results of an experimental investigation of the operation and efficiency of a large impulsive plasma thruster. The thruster uses a one-meter diameter flat spiral coil through which current is pulsed from a 4000 Joule capacitor bank using a spark gap switch. The plasma is driven through inductive coupling rather than with electrodes so as to avoid erosion and energy loss mechanisms that might be undesirable for spacecraft uses. The object of this work was to verify the results of the final report, (AFRPL-TR-80-67, to which this is a supplement), and establish more data on thruster efficiency as a function of specific impulse. The original final report indicated the thruster's efficiency was 45% at 1570 sec Isp. This supplement confirms those figures and reports additional performance figure of 50% at 1590 sec Isp, 62% at 1960 Isp, and 67% at 2250 sec Isp. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1982
- Accession Number
- ADA117797
Entities
People
- C. L. Dailey
- R. H. Lovberg