The RAE 10 cm Hollow Cathode Mercury Thruster.
ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)
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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
- Electric and Ion Propulsion