Pulsed Electromagnetic Thruster.
Abstract
A pulsed inductive plasma thruster has been developed and its performance investigated experimentally. The thruster uses a 20 cm diameter coil through which current is pulsed by discharging a capacitor through a spark gap. Gaseous propellant is injected by a fast acting valve having a total open time of 200 microseconds. The mass utilization factor for this injector was 70 percent. The efficiencies determined by a thrust balance were lower than anticipated because of a large resistive dissipation. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1971
- Accession Number
- AD0735721
Entities
People
- C. L. Dailey
Organizations
- TRW Inc.