Power electronics for a 1-kilopwatt arcjet thruster
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Power electronics for a 1-kilopwatt arcjet thruster

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

Subjects:

  • Arc-jet rocket engines.

Book details:

Edition Notes

Other titlesPower electronics for a one kilowatt arc jet thruster.
StatementRobert P. Gruber.
SeriesNASA technical memorandum -- 87340.
ContributionsUnited States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL15276718M

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Power electronics for a 1-kilowatt arcjet thruster. The preliminary development and demonstration of new, high efficiency, power electronic concepts for start up and steady state control of dc arcjets is reported. The design comprises a pulse width modulated power converter which is closed loop configured to give fast current control. An Author: R. P. Gruber. Power electronics for a 1-kilowatt arc jet thruster. modulated power converter which is closed loop configured to give fast current control. An inductor, in series with the arcjet, serves the dual role of providing instantaneous current control, as well as a high voltage arc ignition pulse. Tests with arcjets demonstrate that the power Author: R. P. Gruber. Journal of Propulsion and Power; Journal of Spacecraft and Rockets; Journal of Thermophysics and Heat Transfer; Browse All Journals; Browse All Virtual Collections; Books. AIAA Education Series; Library of Flight; Progress in Astronautics and Aeronautics; The Aerospace Press; Browse All Books; Meeting Papers; Standards; Other Publications Cited by: 2. Performance and preliminary life test of a low power hydrazine engineering design model arcjet Aerospace Science and Technology, Vol. 15, No. 7 Modeling Study on the Flow, Heat Transfer and Energy Conversion Characteristics of Low-Power Arc-Heated Hydrogen/Nitrogen Thrusters.

  "Power Electronics for a lkW Arcjet Thruster," AIAA Paper , June Yoshikawa, T., et al.. "Development of a Low Powel Arc jet Thruster - . the power supplies properly to ignite the thruster and transition to steady-state operation. 15,16 The discharge supply is a voltage-regulated power supply connected to.   Thermochemical nonequilibrium modeling of a low-power argon arcjet wind tunnel Journal of Applied Physics, Vol. , No. 5 Modelling Study to Compare the Flow and Heat Transfer Characteristics of Low-Power Hydrogen, Nitrogen and Argon Arc-Heated Thrusters.   Nonequilibrium modeling study on plasma flow features in a low-power nitrogen/hydrogen arcjet thruster 31 March | Plasma Science and Technology, Vol. 19, No. 5 Chemical Nonequilibrium Modeling of Low-Power Nitrogen/Hydrogen Arcjet Thrusters.

An electrically-powered spacecraft propulsion system uses electrical, and possibly also magnetic fields, to change the velocity of a of these kinds of spacecraft propulsion systems work by electrically expelling propellant (reaction mass) at high speed.. Electric thrusters typically use much less propellant than chemical rockets because they have a higher exhaust speed (operate. About Power Electronics Books. We have compiled a list of Best & Standard Reference Books on Power Electronics Subject. An exploration of the state-of-the-art in power conversion techniques and power semiconductor devices, this Books are the bottom-down approach, covering the characteristics of power semiconductor devices first and then the fundamentals of conversion techniques.   Power electronics for a 1-kilowatt arc jet thruster After more than two decades, new space mission requirements have revived interest in arcjet systems. The preliminary development and demonstration of new, high efficiency, power electronic concepts for start up and steady state control of dc arcjets is reported. the low-power DC arcjet thruster performance. In the present study, arc voltage, thrust and other important pa-rameters of arcjet thruster are measured for various mass flow rates of argon, nitrogen, nitrogen/ammonia mixtures simulating hydrazine, while the arc current of the arcjet thruster is fixed constant (i.e. I=10 A), so that the effects.