Accession Number:

AD0734316

Title:

The RAE 10 cm Hollow Cathode Mercury Thruster.

Descriptive Note:

Technical rept.,

Corporate Author:

ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)

Personal Author(s):

Report Date:

1971-06-01

Pagination or Media Count:

26.0

Abstract:

The performance of the RAE 10 cm electron bombardment mercury ion engine is discussed. Results are given which show how, at 80 utilisation efficiency, the discharge losses are reduced from 540 eVion to 260 eVion by increasing the grid open area ratio from 50 to 75. The effect of mass flow rate and magnetic field strength on performance is also shown. Thermal time constants and the effect of hollow cathode flow rate on discharge potential are given and their implications are discussed in connection with engine control. Author

Subject Categories:

  • Electric and Ion Propulsion

Distribution Statement:

APPROVED FOR PUBLIC RELEASE