Integration of a flight prototype power conditioner with a 20-cm ion thruster
Oxide hollow cathode ion thruster power conditioner, evaluating electrical efficiency, weight, reliability integration and testing
Benson, G. C.↗
Engineering topics
Muldoon, W. J.
Publications and source records attributed to Muldoon, W. J..
Multi-phase, 2-kilowatt, high-voltage, regulated power supply.
Development of a flight configured experimental power supply delivering 2 kw of conditioned power represents a concentrated effort at advancing the state-of-the-art in high voltage power supplies for space application. The power supply described herein was designed for use with the Jet Propulsion Laboratory (JPL) 20 cm Mercury Ion Thruster. However, its modularized design philosophy allows adaptation to various high voltage, high power requirements. Areas of principal concern are design of power and control circuits, performance parameters, packaging, efficiency, and weight.
Garth, D. R.↗
Functional and physical design of a flight prototype ion engine power conditioner
Space compatible flight prototype ion engine power conditioning system design for Hg thrustor using oxide cathode
Benson, G. C.↗
Application of integrated circuits in ion thruster power conditioning
Integrated circuits for control and telemetry functions in oxide cathode ion thrustor power conditioning system operating from solar panel
Benson, G. C.↗
Electric thruster power conditioner Quarterly technical report, 1 Jul. - 30 Sep. 1968
Electric thruster power conditioner and support equipment
Muldoon, W. J.↗
Development and testing of a lightweight flight prototype ion engine system.
Lightweight flight prototype mercury ion engine system development and testing
ION ENGINE↗
The development and testing of a lightweight flight prototype ion engine system.
Lightweight flight prototype mercury ion engine system development and testing
ION ENGINE↗