High power ion thruster performance by Vincent K. Rawlin

Cover of: High power ion thruster performance | Vincent K. Rawlin

Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .

Written in English

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  • Space vehicles -- Electric propulsion systems.,
  • Space vehicles -- Propulsion systems.

Edition Notes

Book details

StatementVincent K. Rawlin and Michael J. Patterson.
SeriesNASA technical memorandum -- 100127.
ContributionsPatterson, Michael J., 1955-, United States. National Aeronautics and Space Administration.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL14662253M

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P is the electrical power used by the thruster in W, and; I sp is the specific impulse in seconds. The ion thruster is not the most promising type of electrically powered spacecraft propulsion, but it is the most successful in practice to date.

An ion drive would require two days to. of a high power, high specific impulse propulsion system. Initial analyses show that high power gridded ion thrusters could satisfy JIMO mission requirements.

A NASA GRC-led team is developing a large area, high specific impulse, nominally 25 kW ion thruster to satisfy both the performance and the lifetime requirements for this proposed mission.

Note: Citations are based on reference High power ion thruster performance book. However, formatting rules can vary widely between applications and fields of interest or study.

The specific requirements or preferences of your reviewing publisher, classroom teacher, institution or organization should be applied. The High Power Electric Propulsion (HiPEP) Ion Thruster [John E. Foster, NASA Technical Reports Server (NTRS), et al.] on wrcch2016.com *FREE* shipping on qualifying offers.

Practical implementation of the proposed Jupiter Icy Moon Orbiter (JIMO) mission, which would require a total delta V of approximately 38 km/sCited by: The control computer controls and monitors system performance. 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 than 16, hours during a.

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.5/5(1).

Carl Book, Mitchell Walker, “Effect of Anode Temperature on Hall Effect Thruster Performance,” Journal of Propulsion and Power, Volume 26, Number 5, September-Octoberpp. 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. Jul 30,  · Dan M. Goebel, PhD, is a Senior Research Scientist in the Advanced Propulsion Technology Group at JPL in Pasadena, California.

Since joining JPL inhe has worked on the development of high-efficiency ion thrusters, advanced long life cathodes and grids, and electric-thruster life models for deep space missions. A pulsed inductive thruster (PIT) is a form of ion thruster, The PIT has obtained relatively high performance in the laboratory environment, but it still requires additional advancements in switching technology and energy storage before becoming practical for high-power in-space applications, with the need for a nuclear-based onboard power.

Overview of Advanced Electromagnetic Propulsion Development at NASA Glenn Research Center NASA/TM— work on the high power pulsed thruster test facility and preliminary performance data for a quasi-steady baseline Overview of.

Dan M. Goebel received a B.S. in physics, an M.S. in electrical engineering, and a Ph.D. in applied plasma physics from the University of California, Los Angeles, inand respectively.

Next Ion Thruster Performance Dispersion Analyses [Nasa Technical Reports Server (Ntrs)] on wrcch2016.com *FREE* shipping on qualifying offers. The NEXT ion thruster is a low specific mass, high performance thruster with a nominal throttling range of High power ion thruster performance book 7 kW.

Numerous engineering model and one prototype model thrusters have been manufactured and tested. Performance Evaluation of the T6 Ion Engine After hours of operation in the high power mode, the thruster operation was changed to the 2 kW low power station-keeping mode and continued in.

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. chamber to maximize the mass utilization efficiency of the thruster. High ion examine “two-stage” ion optics performance [20] for very high voltage, high Isp applications.

dimension within the range the optics can tolerate for high-power operation with minimal grid interception. It should be noted that grids fabricated from the. To ensure the successful operation of a thruster using inductively-coupled plasmas (e.g.

radio-frequency ion thrusters (RIT)), a high efficiency and high performance radio-frequency (RF) power. Effect of Anode Temperature on Hall Thruster Performance Wilbur and Brophy showed that the performance of an ion thruster can be improvedthrough an increase in propellant residence time in High-Power Electric Propulsion Laboratory, Department of Aerospace Engineering, Ferst Drive.

A review of the manufacturing and characterization activities at PROEL of a plasma bridge neutralizer for the RIT 10 ion thruster MARCO BIANCONI, GIANFRANCO CIRRI.

A model of ion thruster performance is developed for high flux density cusped magnetic field thruster designs. This model is formulated in terms of the average energy required to produce an ion in the discharge chamber plasma and the fraction of these ions that are extracted to form the beam.

Colorado State University Electric Propulsion & Plasma Engineering (CEPPE) Laboratory. The CEPPE Laboratory researches ion and hall thrusters, plasma propulsion technologies, and spacecraft propulsion systems as well as other applications of plasma technology including hydroxyapatite thin films, erosion and sputtering problems, ion optics, and computational modeling.

A second approach would be to use a moderate-thrust ( lb), modest-performance chemical propulsion thruster at sec I sp, such as liquid oxygen (LOx)/monopropellant hydrazine using a cryocooler to keep the LOx from boiling wrcch2016.comty changes of hundreds of feet per second can be achieved in minutes to hours, depending on the propellant mass available, for platforms of thousands.

High efficiency (above 30%) is typically reached only at high power levels (above kW); consequently, the steady-state version of the MPDT is regarded as a high-power propulsion option. When the thruster is operated below kW, the self-induced magnetic field becomes only marginally sufficient to provide the desired body force, and.

wrcch2016.com - Buy The High Power Electric Propulsion (Hipep) Ion Thruster book online at best prices in India on wrcch2016.com Read The High Power Electric Propulsion (Hipep) Ion Thruster book reviews & author details and more at wrcch2016.com Free delivery on qualified wrcch2016.com: John E Foster.

The Variable Specific Impulse Magnetoplasma Rocket (VASIMR) is an electrothermal thruster under development for possible use in spacecraft wrcch2016.com uses radio waves to ionize and heat an inert propellant, then a magnetic field to accelerate the resulting plasma, generating wrcch2016.com is a plasma propulsion engine, one of several types of spacecraft electric propulsion systems.

Thruster performance determined by impulsive thrust and terminal voltage measurements is found to depend primarily on propellant flow rate and the ratio of electrode radii, but not on thruster size.

Current distributions obtained from magnetic field probes are independent of scale for both thruster designs. Aug 22,  · Application of Ion Thrusters to High-Thrust, High-Specifi c-Impulse Nuclear Electric Missions.

Published Online: High-power xenon ion thrusters. High-thrust and low-power operation of a cm-diameter mercury ion thruster. Aug 26,  · Thruster Design and Performance. The efficiency and specific impulse of a Hall thruster are somewhat less than those of the ion thruster, but, very importantly, the thrust is higher at a given power; also, it requires fewer power supplies than ion thrusters.

High-power electric propulsion (EP). Blue Robotics carries a wide range of parts and supplies for marine robotics including underwater thrusters, enclosures, sensors, cables, connectors, and the BlueROV2 remotely operated underwater vehicle (ROV). Our components are widely used by commercial users, researchers, and explorers.

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Is this the record for the highest power output achieved with an ion thruster. Or is there something higher. Also related, what is the highest Isp achieved by an ion thruster. I know for a fixed power, higher Isp means lower thrust, and that is ultimately limited by acceleration voltage, but still I am curious.

Electric space propulsion is a form of advanced rocket Stuhlinger eventually published a book entitled Ion Propulsion for Space Flight and went on to direct NASA Marshall Space Flight Center's work on arcjet and ion propulsion systems. While he was laying the technical groundwork for ion thruster development between anda number.

This book presents the fundamentals of electric propulsion and explains in detail how the two major electric thrusters in use today, namely ion and Hall thrusters, work. It is the first textbook on this subject to be published in 40 years. Jul 05,  · ISRO's Hall effect ion propulsion discussion thread; 2 Likes.

Print; Pages: ISRO is actively engaged in the development of 75mN SPT to be used in its future high power communication satellites. 75 mN SPT Thrust Nominal mode: 75 mN ± 1 mN measured performance of this thruster package will be measured and compared to the theoretical. Feb 14,  · ion propulsion thruster engine 1.

A Seminar report On ION PROPULSION THRUSTER Submitted for partial fulfillment for award of degree of BACHELOR OF TECHNOLOGY IN Electrical Engineering By piyush Mentor wrcch2016.com Seminar Coordinator Prof.

Varun Kumar Department of Electrical Engineering KAMLA NEHRU INSTITUTE OF TECHNOLOGY, SULTANPUR (U.P.).

Ion thruster explained. An ion thruster or ion drive is a form of electric propulsion used for spacecraft wrcch2016.com creates thrust by accelerating cations by utilizing wrcch2016.com term refers strictly to gridded electrostatic ion thrusters, and is often incorrectly loosely applied to all electric propulsion systems including electromagnetic plasma thrusters.

The vastly improved durability of spacecrafts, coupled with the simultaneous continuous development of thrusters for high power output, has created a strong demand for Hall thrusters (HT) with long service lives. However, erosion of the discharge channel walls by high-energy ions is the most impactful and visible process that limits the lifetime of the thruster.

This process is very sensitive Author: Yongjie Ding, Liqiu Wei, Hong Li, Daren Yu. Dec 24,  · The event marked the first performance test of the Nuclear Electric Xenon Ion System (Nexis) ion engine at the high-efficiency, high-power, and. Tech-X develops a variety of scientific software, including physics simulation software and high-performance computing in the cloud, and provides expert physics simulation consulting services in plasma physics and electromagnetics, including photonic integrated circuits.

These methods also tend to make ion and plasma engines heavy compared to combustion engines, so they are not used for launch from high gravity bodies. Rather they operate where there is already a low-g environment in orbit or away from gravity wells.

The ion and plasma types both involve high energy particles. The distinction is one of density. High efficiency, wide-voltage range, and high-dynamic response have become the most important elements of the space power supply. The electric propulsion (EP) has increasingly become the main configuration of the propulsion platform in spacecraft with ion thruster and stationary plasma thruster as the most used application.About.

The Penn State Department of Aerospace Engineering, established in and the only aerospace engineering department in Pennsylvania, is consistently recognized as one of the top aerospace engineering departments in the nation, and is also an international leader in aerospace education, research, and engagement.Low-thrust Propulsion Technologies, Mission Design, and Application processing unit to a neutralizing cathode to maintain a zero net charge in the plume.

An operational schematic of a gridded-ion engine is shown in figure 1. Fig. 1. Operational schematic of a gridded-ion engine. A Hall thruster is essentially a grid-less ion engine.

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