2 edition of 8-cm ion thruster characterization found in the catalog.
8-cm ion thruster characterization
by National Aeronautics and Space Administration, Lewis Research Center in Cleveland, Ohio
Written in English
|Other titles||Eight ion thruster characterization.|
|Statement||F.J. Wessel ... [et al.]|
|Series||NASA-CR -- 180819., NASA contractor report -- NASA CR-180819.|
|Contributions||Wessel, Frank J., Lewis Research Center.|
|The Physical Object|
NASA’s New Ion Thruster Breaks Records, Could Take Humans to Mars Capable of record-breaking speeds and highly efficient, the X3 Hall thruster is our best bet yet for a trip to the red planet. NSTAR Ion Thruster: The NASA Solar Technology Application Readiness (NSTAR) program provided a single string, primary IPS to the Deep Space 1 spacecraft. The cm ion thruster operates over a kW to kW input power range providing thrust from 19 mN to 92 mN.
The combined thruster and PPU mass of thruster, which is shown in Fig. 2, had performance goals of 50% efficiency at kW, which represented a two-fold increase over state-of-the-art. Download: Download full-size image; Fig. 2. NASA 8-cm ion by: 2. April 6, The ion propulsion system on Deep Space 1 is the culmination of over 50 years of development on electric engine systems in ed on Oct. 24, , Deep Space 1 will be the first spacecraft to actually use ion propulsion to reach another planetary body.
A real ion thruster used on satellites. While it may sound like something that Captain Kirk asks Sulu to set to maximum, an ion thruster is not science fiction but actually a working technology. NTR # , , “Low Power Hall Thruster with internal Cathode” Books and Book Chapters. D.M. Goebel and I. Katz, Fundamentals of Electric Propulsion Ion and Hall Thrusters.
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8-CM ION THRUSTER CHARACTERIZATION F.J. Wessel, D.J. Hancock,C.R. Dulgeroff, and W.S. Williamson Hughes Research Laboratories 1 Malibu Canyon Road Malibu, CA October NAS Supplementary Final Report March through February ;MasA-cR-l) A1 8-a ION THRUSTER lOlO6.
High Power Ecr Ion Thruster Discharge Characterization [John E. Foster, Nasa Technical Reports Server (Ntrs), Et Al] on *FREE* shipping on qualifying offers.
Electron cyclotron resonance (ECR) based ion thrusters with carbon based ion optics can potentially satisfy lifetime requirements for long duration missions (approximately 10 years) because grid erosion and cathode insert Cited by: 4. The 8-CM ion thruster characterization.
By F. Wessel and W. Williamson. Abstract. The performance capabilities of the 8 cm diameter mercury ion thruster were increased by modifying the thruster operating parameters and component hardware. The initial performance levels, representative of the Hughes/NASA Lewis Research Center Ion Author: F.
Wessel and W. Williamson. The performance capabilities of the 8 cm diameter mercury ion thruster were increased by modifying the thruster operating parameters and component hardware. The initial performance levels, representative of the Hughes/NASA Lewis Research Center Ion Auxiliary Propulsion Subsystem (IAPS) thruster, were raised from the baseline values of thrust, T = 5 mN, and specific impulse, I sub sp = 2,s.
An 8-cm ion thruster characterization. By D. Hancock, W. Williamson, F. Wessel and C. Dulgeroff. Abstract. The performance of the Ion Auxiliary Propulsion System (IAPS) thruster was increased to thrust T = 32 mN, specific impulse I sub sp = s, and thrust-to-power ratio T/P = 33 mN/kW.
This performance was obtained by. Development of 8 cm ion thruster technology which was conducted in support of the Ion Auxiliary Propulsion System (IAPS) 8-cm ion thruster characterization book contract (Contract NAS) is discussed. The work included characterization of thruster performance, stability, and control; a study of the effects of cathode aging; environmental qualification testing; and cyclic lifetesting of especially critical thruster.
asteroid using ECR ion thrusters (ref. 15). A revival in microwave research began at NASA GRC in This work culimated in the testing and eventual beam extraction from a 40 cm ion source. The focus of this effort was to develop a medium power thruster similar to the NEXT engine.
Discharge characterization results from that study. The neutralizer of a high-power ion thruster was characterized over a range of flow rates at the nominal thruster operating condition of A of ion beam current at a beam voltage of V.
Near. The ion thruster then processes the propellant and power to propel the spacecraft. The first ion thrusters did not last very long, but the ion thruster on Deep Space 1 exceeded expectations and was used more t hours during a period of over 2 years.
The ion thrusters being developed now are being designed to operate for 7 to 10 years. The satellites are designed to control costs. For example, each will maneuver with Hall-effect thrusters—ion thrusters in which propellant is accelerated by an electric field. The conventional fuel for such a thruster is xenon, which offers high performance.
The Starlink satellites, however, will use a different noble gas: krypton. This development effort has led to the fabrication and preliminary performance assessment of an 8 cm prototype xenon ion thruster operating over an input power envelope of kW. Ion engine grids: Function, main parameters, issues, configurations, geometries, materials and fabrication methods Chinese Journal of Aeronautics, Vol.
31, No. 8 Ferromagnetic enhanced inductively coupled plasma cathode for thruster ion neutralizationCited by: Throughout most of the twentieth century, electric propulsion was considered the technology of the future.
Now, the future has arrived. This important new book explains the fundamentals of electric propulsion for spacecraft and describes in detail the physics and characteristics of the two major electric thrusters in use today, ion and Hall thrusters.
The authors provide an introduction to Cited by: Fundamentals of Electric Propulsion: Ion and Hall Thrusters March The research described in this publication was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration.
Reference herein to any specific commercial product, process, or service. COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.
One such system is an ion thruster. A propulsion system with no moving parts, it has a high reliability and incredible efficiency. Counterbalancing those benefits is a very low actual thrust – I once read, at least as of years ago, that ion thruster force was comparable to a holding an 8 ½ X 11 piece of paper in your : NITZAKHON.
An ion thruster produces a flow of air even though it has no moving parts. A version of this seemingly impossible device is used on a larger scale to propel deep space probes for NASA.
The advantage to this system over others is that you need only an electrical source to power the device and it has no moving parts so it is almost : Alexander Reifsnyder. Description. This book provides an insight into the state-of-the-art in electric propulsion. An attempt is made to portray the technology in a logical fashion, starting with mission requirements.
Technology of the two dominant electric propulsion devices from basic physics through flight hardware is described. How to add Ion Propulsion to Star Wars TIE Fighter Model - Duration: Rimstar views. Homemade ion thruster using 30kV Voss machine. Buy High Power Ecr Ion Thruster Discharge Characterization by John E.
Foster, Nasa Technical Reports Server (Ntrs), Et Al (ISBN: ) from Amazon's Book Store. Everyday low prices and free delivery on eligible orders. ion propulsion system on DS1: 1. Adequate engine life—Prior to the NSTAR project, no ion engine intended for primary propulsion had ever been successfully operated for its full design life.
2. Guidance, navigation and control (GN&C) of a solar-electric propulsion (SEP) spacecraft—The low-thrust nature of SEP, together with large solar File Size: 2MB. Non-intrusive characterization of the singly ionized xenon velocity in Hall thruster plume using laser induced fluorescence (LIF) is critical for constructing a complete picture of plume plasma, deeply understanding the ion dynamics in the plume, and providing validation data for Cited by: 1.
A very brief introduction to Ion Thrusters. This feature is not available right now. Please try again later.