3 edition of Hollow cathode heater development for the space station plasma contactor found in the catalog.
Hollow cathode heater development for the space station plasma contactor
Published
1993
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC], [Springfield, Va
.
Written in English
Edition Notes
| Statement | George C. Soulas. |
| Series | NASA contractor report -- 191131., NASA contractor report -- NASA CR-191131. |
| Contributions | United States. National Aeronautics and Space Administration. |
| The Physical Object | |
|---|---|
| Format | Microform |
| Pagination | 1 v. |
| ID Numbers | |
| Open Library | OL14700604M |
Ignition-Cycle Investigation of a LaB6 Hollow Cathode for 3–5-Kilowatt Hall Thruster Patterson M. J. and Dalton P. J., “ Operational Status of the International Space Station Plasma Contactor Hollow Cathode Assemblies from July to May ,” 49th Joint Propulsion Conference “ Low Current Heaterless Hollow Cathode Cited by: 5. [6] Guo, N., "Research of hollow Cathode for Ion thruster," Ph.D Dissertation, China Academy of Space Technology, Lanzhou, (In Chinese) [7] Soulas, G.C., "Status of Hollow Cathode Heater Development for the Space Station Plasma Contactor," AIAA , June Cited by: 1.
Electric thrusters are finding increasing usage worldwide in spacecraft applications. Significant progress has been made in recent years in the modeling and performance of thermionic hollow cathodes used in flight thrusters, such as Hall and ion thrusters, or other types of plasma sources, such as for technological plasmas. The recent progress is surveyed in this paper through the discussion. Plasma contactors are devices used on spacecraft in order to prevent accumulation of electrostatic charge through the expulsion of plasma (often Xenon).. An electrical contactor is an electrically controlled switch which closes a power or high voltage electrical circuit.A plasma contactor changes the electrically insulating vacuum into a conductor by providing movable electrons and positive.
The cathode heater impedance was assumed to be in a range similar to those utilized on U.S. hollow cathodes, such as the Solar Electric Propulsion System (SEPS) 30 cm ion engine, 7 and the Space Station Freedom (SSF) Plasma Contactor. A hollow cathode plasma contactor has been baselined as a charge control device for the Space Station (SS) to prevent deleterious interactions of coated structural components with the ambient plasma.
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A hollow cathode-based plasma contactor has been selected for use on the Space Station. During the operation of the plasma contactor, the hollow cathode heater will endure approximately thermal cycles.
Since a hollow cathode heater failure would result in a plasma contactor failure, a hollow cathode heater development program was establishedFile Size: KB. A hollow cathode-based plasma contactor has been selected for use on the Space Station. During the operation of the plasma contactor, the hollow cathode heater will endure approximately thermal cycles.
Since a hollow cathode heater failure would result in a plasma contactor failure, a hollow cathode heater development program was established to produce a reliable heater design.
Get this from a library. Hollow cathode heater development for the space station plasma contactor. [George C Soulas; United States. National Aeronautics and Space Administration.]. A hollow cathode-based plasma contactor has a later program, using larger diameter cathodes, re-been baselined for use on Space Station to reduce vealed that the alumina insulation was prone to station charging.' The hollow cathode utilized by the cracking after.
Development efforts for the plasma contactor include optimizing the design and configuration of the contactor, validating its required lifetime, and characterizing the contactor plume and.
Implementation of a hollow cathode plasma contactor for charge control on the Space Station has required validation of long-life hollow cathodes. A test series of hollow cathodes and hollow cathode plasma contactors was initiated as part of the plasma contactor development program.
An File Size: 7MB. Since Octobertwo plasma contactors have been providing charge control on the International Space Station (ISS). At the heart of each of the two plasma contactors is a hollow cathode assembly (HCA) that produces the contacting xenon pla.
The HCA is the result of 9 years of design and testing at the NASA Glenn Research Size: KB. Hollow cathode plasma contactors were baselined for Space Station Freedom (SSF) to control the electrical potentials of surfaces to eliminate/mitigate damaging interactions with the space environment.
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 HCAs were designed and fabricated at NASA’s Glenn Research Center (GRC).Cited by: 8. A hollow cathode plasma source is well suited for this application and was therefore selected as the design approach for the station plasma contactor system, s Active emission to the space plasma of electron current at least matching the net electron current collected on the station solar arrays (referred to as "ciamping" mode) is required for only a small portion of the station orbital Size: 1MB.
This banner text can have markup. web; books; video; audio; software; images; Toggle navigation. Heaterless Hollow Cathodes (HHC) are a subclass of hollow cathodes that do not require a heater for cathode ignition [6].
In this type of cathodes the heating process is by plasma discharge. The plasma contactor subsystems include a hollow cathode assembly, a power electronics unit, and an expellant management unit.
Under a pre-flight development program these subsystems are. Abstract Since Octobertwo plasma contactors have been providing charge control on the International Space Station (ISS). At the heart of each of the two plasma contactors is a hollow cathode. On the Operational Status of the ISS Plasma Contactor Hollow Cathodes [Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers.
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). A hollow cathode-based plasma contactor has been selected for use on the Space Station.
During the operation of the plasma contactor, the hollow cathode heater will endure approximately thermal cycles. Since a hollow cathode heater failure would result in a plasma contactor failure, a hollow cathode heater development program was established to produce a reliable heater.
Soulas, “ Status of hollow cathode heater development for the space station plasma contactor,” in Proceedings of the 30th Joint Propulsion Conference (JPC), Indianapolis, IN, 27–29 June Google Scholar; : Dan Lev, Gal Alon, Leonid Appel.
Get this from a library. Status of hollow cathode heater development for the space station plasma contactor. [George C Soulas; United States. National Aeronautics and Space Administration.]. This photo is of the Hollow Cathode Assembly, which is installed in the plasma contactor that will protect the structure of the space station.
Image credit: NASA The PCU acts as an electrical ground rod to connect the space station structure to the local environment and. A hollow cathode plasma contactor has been baselined as a charge control device for the Space Station (SS) to prevent deleterious interactions of Cited by: 4.
High-Current Hollow Cathode Development *† Christian B. Carpenter QSS Group, Inc. MS Brookpark Rd. Cleveland, OH [email protected] Michael J. Patterson NASA Glenn Research Center MS Brookpark Rd. Cleveland, Ohio IEPC NASA Glenn Research Center is currently developing high power cathodes for a variety of electric propulsion .development7.
The cathode, denoted Rafael Heaterless Hollow Cathode (RHHC)(see Figure 1), is designed to operate at the low current regime ( A) and couple with low power Hall Thrusters ( W). The cathode was designed following a rigorous mechanical and thermal design process and is made of a combination of.between the hollow cathode and the ambient plasma, two complete plasma contactor systems will be present allowing electrons to be emitted from the hollow on the space station at all times with one operational cathode into the ambient plasma, thereby discharging unit and one backup unit.
In the event of a failure, the the spacecraft.
