3 edition of Low power pulsed MPD thruster system analysis and applications found in the catalog.
Low power pulsed MPD thruster system analysis and applications
|Statement||Roger M. Myers, Matthew Domonkos, and James H. Gilland.|
|Series||NASA contractor report -- 191187., NASA contractor report -- NASA CR-191187.|
|Contributions||Domonkos, Matthew., Gilland, James Hunter., United States. National Aeronautics and Space Administration.|
|The Physical Object|
There are several components in a complete system for your boat; besides the thrusters and tunnels (bow or stern or both) – you will need control cables, main switches – automatic or manual – fuse & fuse- holder, control panel(s) and main power cables, even a radio remote is . American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA
Abstract. European activities in the field of electric propulsion research, primarily under ESA sponsorship, are discussed. Attention is given to German RF ion thrusters using Xe gas propellant, a family of British Xe-propellant Kaufmann thrusters with outputs in the mN range, the results of tests with the Field Emission Electric Propulsion system, Italian MPD thruster-related research. Feasibility study of low power helicon thruster M. Manente a, b, J. Carlssonc, C. Bramantid, e, i a, çlua, na a) CISAS University of Padua Via Venezia 15 Padova Italy b) Georgia Tech Univerity Atlanta, GA c) Txcorp Boulder Colorado USA.
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Required pulsed propulsion system components include a pulsed applied-field MPD thruster, a pulse-forming network, a charge control unit, a cathode heater supply, and high speed valves.
Low Power Pulsed MPD Thruster System Analysis and Applications Roger M. Myers Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio Matthew Domonkos University of New Mexico Albuquerque, New Mexico and James H.
Gilland Sverdrup Technology, Inc. Lewis Research Center Group Brook Park, Ohio Prepared for the Joint Propulsion. Get this from a library. Low power pulsed MPD thruster system analysis and applications. [Roger Metcalf Myers; Matthew Domonkos; James Hunter Gilland; United.
Research at Glenn encompasses a combination of systems analysis, numerical modeling, and high-power experiments that investigate pulsed versions of both self-field and applied-field MPD thrusters.
Testing for these thrusters has demonstrated exhaust velocities ofmeters per second (overmph) and thrust levels of Newtons ( Pulsed MPD Thruster Test Facility The pulsed, high power plasma thruster test facility at the Glenn Research Center consists of a high-energy pulse-forming network, interlocked vacuum chamber, propellant plenum, flexure-based thrust stand, and automated.
MPD thruster performance model suitable for use in system or mission analysis, has been achieved. More important than the accuracy of the model in reproducing experimental results is the fact that.
The PPT system includes a power source, power processing unit (PPU), energy storage unit, and the thruster itself. The power source can be any source of electrical power.
Solar cells are generally used, since the thruster operates at low power levels. The PPU converts the spacecraft power to charge the PPT energy storage unit. The energy.
A laboratory MPD thruster may have a mass/power ratio of order kg/kW, depending on scale. Most of this mass is that of the electric conductors (wiring), especially those of the magnetic coils. If superconducting wires replaced copper, coils and windings mass could be reduced by orders of magnitude [Bruno and Giucci, ; Casali and.
cm ion engine, or for a 10 cm Hall thruster). Applied eld MPD thrusters: Here currents are less strong, so the main part of the B eld is external. Still steady or quasi-steady. Pulsed Plasma Thrusters (PPT): Pulsed Plasma Thrusters (PPT) are very similar in principle to self- eld MPD, but they use a solid propellant (Te on) which is ablatedFile Size: 1MB.
A magnetoplasmadynamic (MPD) thruster (MPDT) is a form of electrically powered spacecraft propulsion which uses the Lorentz force (the force on a charged particle by an electromagnetic field) to generate thrust.
It is sometimes referred to as Lorentz Force Accelerator (LFA) or (mostly in Japan) MPD arcjet. Generally, a gaseous material is ionized and fed into an acceleration chamber, where the. A FRC-MPD thruster was designed so that magnetic circuit of water-cooled MPD thruster can be reused.
Figure 7 shows 3D model and the cross-section of the previous structure of FRC-MPD thruster (structure 1). Parts of FRC-MPD thruster are anticipated increasing temperature, because of without water-cooled. Therefore, most thruster parts.
As NASA's lead center for electric propulsion, the Glenn Research Center has established a MW-class pulsed thruster test facility and is refurbishing a high-power steady-state facility to design, build, and test efficient gas-fed MPD by: Integral and local characteristics of the laboratory model of a low-power plasma thruster operating in a pulsed regime have been experimentally studied.
Rectangular pulses of discharge current with the leading and trailing fronts not exceeding 1 ms have been obtained. At an average supplied electric power of ∼ W, the propulsion efficiency amounted to 35%.Author: A. Bugrova, A. Desyatskov, Yu. Korobkin, A. Lipatov, V. Kharchevnikov. A 1-megawatt system would pulse times per second.
Pulsed inductive thrusters can maintain constant specific impulse and thrust efficiency over a wide range of input power levels by adjusting the pulse rate to maintain a constant discharge energy per pulse. It. Control and Analysis of a JxB Pump Propellant Feed System for the Lithium Lorentz Force Accelerator: Bachelor's Thesis: The role of spot mode transition in the anode fall of pulsed MPD thrusters: 24th International Electric Propulsion Conference Cathode Phenomena in Low-Power Magnetoplasmadynamic Thruster: Journal of Propulsion.
The aim of this thruster topology and design, as with any thruster, is to maximize the efficiency of the thruster, especially with respect to the use of the propellant gas. This design has a particular advantage in that area, as the forces developed on the propellant gas arise from electromagnetic forces, rather than from thermal expansion.
The good: This book covers many diverse aspects of pulsed power technology, including insulation, switching, pulse generators, and diagnostics. Also, it is a decent quick-reference for formulas and material parameters (e.g., bulk breakdown strength of materials).Cited by: mechanism regulating the anode fall of a high-power, mission times between and hours, capa-pulsed, self-field MPD thruster is presented.
Plasma bilities that have yet to be demonstrated in the labo-property data recorded to within one electron Larmor ratory .
Inﬂuence of Tailored Applied Magnetic Fields on High-Power MPD Thruster Current Transport and Onset-Related Phenomena IEPC Presented at the 33rdInternational Electric Propulsion Conference, The George Washington University, Washington, D.C., USA October 6–10, Robert C.
Moeller and James E. Polky. A low-power helicon thruster (LPHT) is an electric propulsion system that utilizes a helicon plasma source with high magnetic field strength to achieve specific impulses of up to s using argon propellant.
The Center of Studies and Activities for Space (CISAS) has created a prototype design, and the Georgia Institute of Technology (GA Tech) has.
The thruster must be mounted in the direction shown on fig 1, both if monted in bow and stern (the hatch must open forwards in the direc-tion of travel).
If the unit is to be used as a bow thruster, find the position furthest for-ward where the unit will fit - allowing for 10cm space around all sides.study, respectively. The thruster was operated with an input power of kW. And, Figure 2 shows the 3D model of the MPD thruster with cusp field used for this study.
The MPD thruster has a magnetic circuit which is formed by iron plates sandwiched SmCo magnets around the anode for application of .Low Power Pulsed MPD Thruster_System Analysis and MANAGERIAL BRIEFING INDUSTRIAL ENGINEERING APPLICATIONS IN MANAGING MDO SOFTWARE DEVELOPMENT