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Tuesday, July 21, 2020 | History

3 edition of Power electronics development for the SPT-100 thruster found in the catalog.

Power electronics development for the SPT-100 thruster

Power electronics development for the SPT-100 thruster

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  • 22 Currently reading

Published by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, Springfield, Va .
Written in English

    Subjects:
  • Space vehicles -- Electric propulsion systems.

  • Edition Notes

    StatementJohn A. Hamley, Gerald M. Hill, and John M. Sankovic.
    SeriesNASA technical memorandum -- 106488.
    ContributionsHill, Gerald M., Sankovic, John M., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15392145M

    The SPT typically provides 80 mN thrust at an Isp of s and 48% efficiency with an input power of kW. A SPT has been laboratory tested down to W with an Isp of s and efficiency of 21% (Manzella ). At the design point of kW, the SPT operated at an Isp of s and an efficiency of 32%.   Research and Development of Low-Power and High-Power Three-Types Hall Thrusters at Osaka Institute of Technology View Section, Experimental Performance Characterization of a Novel Direct Current Cold Cathode Neutralizer for Electric Thruster Applications.

      Development and Test of the Negative and Positive Ion Thruster PEGASES. View Section, Downstream Flow Analysis of High-Power Helicon Double Gun Thruster with Application to Spacecraft Propulsion Systems. View Section, The Effect of Background Pressure on SPT Hall Thruster Performance. View Section. Starting from that year more then Hall thruster have been used in space[24]. Subsequently Hall engine of different power and size were developed with the introduction of the SPT and SPT .

    The modelling of the Hall thruster SPT is a very important issue in view of the increasing importance of such propulsion devices in space applications. Only kinetic models can investigate the rich variety of physical mechanisms involved in the Hall discharge and in the plume emitted from the thruster. The development and qualification of a kW Hall thruster propulsion system for GEO satellite applications – status update. Paper presented at the 28th international electric propulsion conference, Toulouse, France, Google ScholarCited by: 4.


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Power electronics development for the SPT-100 thruster Download PDF EPUB FB2

Get this from a library. Power electronics development for the SPT thruster. [John A Hamley; Gerald M Hill; John M Sankovic; United States. National Aeronautics and Space Administration.].

SPT is a Hall-effect ion thruster, part of the SPT-family of stands for Stationary Plasma creates a stream of electrically charged xenon ions accelerated by an electric field and confined by a magnetic field. Thruster is manufactured by Russian OKB Fakel, and was first launched onboard Gals-1 satellite in In Fakel debuted a second generation of the.

The SPTB thruster is the basic design variant of the SPTD. Several tasks were solved during development of the design of the new thruster. In particular, the magnetic system has been optimized to reach the required thrust, specific and life time characteristics of the thruster and to ensure the discharge power operating range.

In spacecraft propulsion, a Hall-effect thruster (HET) is a type of ion thruster in which the propellant is accelerated by an electric field.

Hall-effect thrusters use a magnetic field to limit the electrons' axial motion and then use them to ionize propellant, efficiently accelerate the ions to produce thrust, and neutralize the ions in the -effect thrusters (based on the discovery. Additional, time resolved measurements were taken along the centerline of the thruster (R = 0) and along the discharge channel centerline (R = 5 mm).

SPT Hall Thruster Figure 1 provides an image of the SPT Hall thruster operating, as well as a schematic of the thruster. Existing technological fundamentals and potential development paths.

Every electric propulsion system is based on key components that make the concept work. The most important components are the energy storage device (battery system), 2 the electric machine, the power electronics, and a suitable charging device.

• NASA’s Solar Electric Propulsion Technology Demonstration Mission (SEP TDM) • NASA GRC & JPL High Power Hall Thruster Technolo gy Development • Overview of the NASAMS design and testing • kW Hall thruster design and modeling • kW Hall thruster functional tests • kW thruster planned tests • Summary.

“Very High-Power Hall-Effect Thruster for Exploration”, SITAEL is developing, designing, manufacturing and testing a new 20kW class Hall effect thruster, the HT20k, together with the associated high current hollow cathode, the HC This paper provides the description of the development approach and the status of the Size: KB.

SPT/Bi-prop 12 hrs. by SPT 2 per day by SPT A few seconds by a Bi-prop 2 per day by a Bi-prop Orbit Control Maneuvering of chemical and Hybrid GEO satellites 19 MBSAT: DBS communications satellite for Japan and Korea built by SS/L, The first US-built satellite with SPT T he SPT is a Hall-effect thruster designed and built in Russia by the Experimenta l Design B ureau Fakel which has over 15 years of o n orbit flight heritage on Russian spacecraft with this.

Space Systems/Loral has implemented the SPT Hall effect thruster onto geostationary spacecraft for primary north-south station keeping, allowing substantial reductions in onboard propellant : Martin Tajmar.

Carl Book, Mitchell Walker, “Effect of Anode Temperature on Hall Effect Thruster Performance,” Journal of Propulsion and Power, Vol Number 5, September-Octoberpp.

The W-class ISCTv2 Hall Thruster (HT) has been characterized in terms of far-field plume properties. By means of a Faraday Cup and a Retarding Potential Analyzer, both the ion current density and the ion energy distribution function have been measured over a ∘ circular arc for different operating points.

Measurements are compared to far-field plume characterizations performed. Impulse Two-Stage Hall Thruster with Plasma Lens Focusing. In the following, a review of two-stage HETs, plasma lens focusing, and the use of trim coils is discussed.

The implementation of these concepts in the development of the P is then presented, followed by a brief review of the performance and plume characteristics of the thruster to.

By examining a range of thruster sizes and operating conditions,9,10 11 we are able to make modeling predictions. One of the most important parameters for this study is the curve of thruster power in terms of the specific impulse (I sp).

As specific impulse increases, the discharge voltage will increase as well. The Hall thruster power is Cited by: designs, develops and produces Power Processing Unit (PPU) to supply Hall Effect Thrusters: SPT from Fakel and PPSG from Snecma.

The first qualification model, developed for the 50V bus Stentor program, has supplied during hours an SPT thruster in a vacuum chamber simulating space by: 4. 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. of 1 Newton of thrust at elevated power levels. Development of a Hall thruster capable of operating at seconds at power levels of 50 kilowatts and above requires a thruster design which preserves the physical processes required for efficient ionization and acceleration of the propellant.

Important characteristics for preservation. Together, they make 60% of the industry-wide insurance claims for in-orbit operational defects. The author, a recognized expert in the industry, has written this book to provide reliable information on a variety of subjects to engineers and managers involved in spacecraft power systems design, development, testing, and operation.

Improved Superconducting Magnet System to Reduce Upstream Boundary Power Losses in a Helicon Plasma Thruster. John J. Vitucci and; High-Temperature Sensor and Electronics Packaging Technologies for Distributed Engine Controls.

Numerical Modeling Approaches in Hybrid Rocket Motor Development • Monday, 28 July • hrs. Q&A for spacecraft operators, scientists, engineers, and enthusiasts.

Stack Exchange network consists of Q&A communities including Stack Overflow, the largest, most trusted online community for developers to learn, share their knowledge, and build their careers. Visit Stack Exchange.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 ty changes of hundreds of feet per second can be achieved in minutes to hours, depending on the propellant mass available, for platforms of thousands.Journal of Propulsion and Power; Journal of Spacecraft and Rockets; SPT subsystem development status and plan.

M. Day, N. Maslennikov and; W. Rogers; Cyclic endurance test of a SPT stationary plasma thruster. Charles Garner, John Brophy, James Polk and; Lewis Pless.