by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English
|Statement||John A. Hamley ... [et al.].|
|Series||NASA technical memorandum -- 106486., NASA technical memorandum -- 106486.|
|Contributions||Hamley, John A., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Development of a Power Electronics Unit for the Space Station Plasma Contactor Iohn A. Hamley, Gerald M. Hill, and Michael J. Patterson National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Joseph Saggio, Jr. and Fred Terdan Analex Corporation Aerospace Parkway Brook Park, Ohio Justin D. Mansell. Get this from a library! Development of a power electronics unit for the space station plasma contactor. [John A Hamley; United States. National Aeronautics and Space Administration.;]. NASA LeRC Work Package 4 initiated the development of a plasma contactor system comprised of a Power Electronics Unit (PEU), an Expellant Management Unit (EMU), a command and data interface, and a Plasma Contactor Unit (PCU). A breadboard PEU was designed and fabricated. The plasma contactor subsystems include the plasma contactor unit, a power electronics unit, and an expellant management unit. Under this pre-flight development .
Plasma contactors have been baselined for the Space Station (SS) to control the electrical potentials of surfaces to eliminate/mitigate damaging interactions with the space environment. The system represents a dual-use technology which is a direct outgrowth of the NASA electric propulsion program and, in particular, the technology development effort on ion thrustor . Plasma Contactor The space station arrays operate at volts dc. When the arrays are producing power, the station structure will also tend to float to a voltage close to the array voltage. Under these conditions, the space station could be subjected to problems like arcing from its surface to the surrounding environment, or arcing to an. Integration issues of a plasma contactor Power Electronics Unit A hollow cathode-based plasma contactor is baselined on International Space Station Alpha (ISSA) for spacecraft charge control. The plasma contactor system consists of a hollow cathode assembly (HCA), a power electronics unit (PEU), and an expellant management unit (EMU). On the Operational Status of the ISS Plasma Contactor Hollow Cathodes The Plasma Contactor Unit (PCU) was developed by the Rocketdyne division of The Boeing Company to control charging of the International Space Station (ISS). Each PCU contains a Hollow Cathode Assembly (HCA), which emits the charge control electrons.
The plasma contactor subsystems include the plasma contactor unit, a power electronics unit, and an expellant management unit. Under this program these will all be brought to breadboard and engineering model development status. The plasma contactor unit acts as an electrical ground rod to connect the Space Station structure to the local environment and harmlessly dissipate the structure charges. NASA Glenn engineers designed, manufactured and tested the hollow cathode assembly, which is the critical component of the plasma contactor unit. The International Space Station (ISS) requires a plasma test article was a development unit hollow cathode the ISS plasma contactor power electronics. therefore selected as the design approach for the station plasma contactor system. 4 In addition to the plasma source, referred to here as a hollow cathode assembly or HCA, the plasma contactor system includes two other subsystems. These are the power electronics unit and the xenon gas feed system. The Rocketdyne Division of Boeing North.