LABORATORY TESTING OF THE SPACE-CHARGE-SHEATH ELECTRIC THRUSTOR.
Abstract
Recent experimental results obtained with a laboratory model of the space-charge-sheath thrustor are reported. The principal feature of this thrustor is the electrostatic acceleration of ions in a space-charge sheath formed on the ionizer. Operating conditions were a specific impulse of 2700 to 5500 sec, a magnetic field strength of 800 to 2500 G, an accelerating gap of 1 to 3 mm, an ionizer surface if 13.8 sq cm, a cesium vapor pressure of 5 to 40 mm Hg, and an ion-beam current density of 4 to 14 mA/sq cm. The resulting ion-beam was surprisingly well collimated, with an estimated half-angle of 1.5 deg. Under best operating conditions, the electron drain current to the anode (ionizer) was 31% of the total current. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 31, 1969
- Accession Number
- AD0692736
Entities
People
- Rudolf X. Meyer
Organizations
- The Aerospace Corporation