3 edition of Performance of a miniaturized arcjet found in the catalog.
Performance of a miniaturized arcjet
by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C.], [Springfield, Va
Written in English
|Statement||John M. Sankovic and David T. Jacobson.|
|Series||NASA technical memorandum -- 107062.|
|Contributions||Jacobson, David T., United States. National Aeronautics and Space Administration.|
|The Physical Object|
Several examples are the lifetime fatigue performance of the solder joints (temperature cycle reliability), drop test performance, standoff height, or heat sink compatibility. These elements are important to consider, but are hard to describe generically because of the specific application requirements. Designing for miniaturized packages. Arcjets are definitely the gray area between thermal and magnetically based propulsion, arc heating, is a very interesting option. Here, a spark, or arc, of electricity is sustained between two electrodes. This heating is virtually the same way an arc welder operates. This has the advantage that you aren’t thermally limited by your resistor for.
ArcJet Cutting and Design, Houston, Texas. 78 likes 1 was here. Local Business. Arcjet Systems broken elevator call button. I'm doing the Brotherhood of Steel quest on my pc and everything was working just fine. Once at the bottom of the engine core room I restored power to the system and fought off all the synths. Then the quest indicator marked the elevator call button. It is lit (though the light flashes) but when I.
Performance measurements were obtained and life-limiting mechanisms were identified on a laboratory-model arcjet thruster designed to operate at a nominal power level of W. Books about Joan of Arc the French girl who lead the army against the British. Score A book’s total score is based on multiple factors, including the number of people who have voted for it and how highly those voters ranked the book.
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Performance of a Miniaturized Arcjet John M. Sankovic Lewis Research Center Cleveland, Ohio and David T.
Jacobson The Ohio State University Columbus, Ohio Prepared for the (NASA-TM-I) PERFORMANCE OF A MINIATURIZED ARCJET (NASA. Le~is Research Center) 17 p 31st Joint Propulsion Conference and Exhibit. Performance measurements were obtained and life-limiting mechanisms were identified on a laboratory-model arcjet thruster designed to operate at a nominal power level of W.
The design employed a supersonic-arc-attachment concept and was operated from to W on hydrogen/nitrogen mixtures in ratios simulating fully decomposed hydrazine and Cited by: 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. Effect of Nozzle Temperature on the Performance of a 1 kW H 2 -N 2 Arcjet Thruster 8 September | Plasma Science and Technology, Vol.
12, No. 4 A New Manner for Energy Reintroduction in AJAX. McGraw-Hill Book Company () Google Scholar. G.P. Sutton, Oscar BiblarzRocket propulsion elements (7th ed.), John Wiley & Sons, Inc. () Google Scholar. Sankovic JM, Jacobson DT. Performance of a miniaturized arcjet.
NASA technical memorandum ; Google Scholar. Curran FM, Hardy TL, Hag TW. In: A low-power arcjet. Performance of a miniaturized arcjet [microform] / John M. Sankovic and David T.
Jacobson A study of DC-DC converters with MCT's for arcjet power supplies [microform] / Thomas A. Stuart Numerical modeling of a vortex stabilized arcjet [microform] / Gary E. Pawlas. To sustain the arc in the arcjet, the swirl is thought to be necessary.
This paper conducts a numerical study on various geometry and input conditions. The effect of swirl and wall temperature of a nozzle on the plasma flow, arc behavior, and performance parameter of low power arcjet has been studied.
Sankovic JM, Jacobson DT. Performance of a miniaturized arcjet. NASA technical memorandum ; In: A low-power arcjet cyclic lifetest, JANNAF propulsion conference Book on physics of.
Moreover, Arc jet testing on fully instrumented samples, incorporating in-situ miniaturized heat flux, and temperature and recession sensors, can maximize test utility by enabling active test data (such as time-history of recession) and to aid in the development of an extensive database of in-depth thermal response and surface ablation.
The idea of a miniaturized arcjet thruster is being investigated computationally at the University of Stuttgart in Germany. High efficiency multistage plasma thruster: The high efficiency multistage plasma thruster (HEMPT) is a form of electrical propulsion which has in the past drawn comparisons to gridded Ion Thrusters and Hall thrusters.
Biohm (MBB) (ref. Typical performance of these thrusters is shown in Table IU. At BPD, a low power laboratoryusing hydrazine decomposition products, demonstrated a specific impulse of about s. Acti,'ities at CS foct,s on arcjet modeling, power processor design, and thruster performance parametdes.
At BPD, parametric performance. Tbrust-current characteristics of double-size K-VII-S. MPD arcjet system performance test where H is the permeability and R, Rm, R~ are the radii of anode root, anode mouth and cathode flank, respec- tively (see Fig.
v- The measured plots show a tendency toward j2-de- ~o pendence in the larger range of J values; in the remaining,m, range. The effects of the electrical conductivity and the anode wall temperature on arcjet performance prediction are also discussed.
Experimental tests of the engineering design model arcjet thruster with simulated hydrazine reaction products as propellant were carried out with a mass flow rate range of 20 – 32 mg/s and an arc current range of 8. Power Arcjet Thruster VELARC in Test Facilities at IRS and ESA-ESTEC P. Upadhyay A Operation and Performance of a Fully-Integrated ion Electrospray Propulsion System B.
Kristinsson A An Experimental Study of Thrust Dependence on Magnetic Field in an Electrodeless Inductive Plasma Accelerator A. Tatsuno A An arc-heated thruster, or arcjet thruster, heats propellant with an arc which connects the anode and the cathode crossover a narrow channel, as shown in Fig.
the temperature of an arc column is much higher than typical combustion temperature of chemical propellant, the specific impulse of an arcjet thruster is usually two or three times higher than.
ArcJet Systems (also known simply as ArcJet) was a pre-War company which performed communications and propulsion work for both military and civilian contractors.
Despite a very successful run as a defense contractor, by FebruaryArcJet Systems was financially struggling. CEO Thomas Reinhardt took a risk and began construction of both the propulsion. Power electronics for a miniaturized arcjet (OCoLC) Material Type: Government publication, National government publication, Internet resource: Document Type: Book, Internet Resource: All Authors / Contributors: Luis R Piñero; Glen E Bowers; United States.
National Aeronautics and Space Administration. Arcjet Engine Core. The Engine Core is built around the central testing shaft, containing a fueled jet engine. It is accessed during Call to Arms and is a much, simpler, straightforward path.
The bottom level is accessed using the stairwell, with the primary means of accessing the control room being the elevator. Stable arcjet operations at very low-power levels ranging from 40 to 90 W with a constrictor diameter of – mm were confirmed.
(2) Temperature of molecular nitrogen estimated at the center of the constrictor exit is high, about – K, even under very low-power operation, and rises with increasing arcjet input power. (3).Field-emission electric propulsion (FEEP) is an advanced electrostatic space propulsion concept, a form of ion thruster, that uses liquid metal (usually either caesium, indium or mercury) as a propellant.A FEEP device consists of an emitter and an accelerator electrode.
A potential difference of the order of 10 kV is applied between the two, which generates a strong electric .arcjet systems.
The purpose of this work was to obtain preliminary operating experience with high power hydrogen arcjets, and relate performance with 's data.
APPARATUS While the 30 kW arcjet thruster used in this work is of recent design, its basic arrangement resembles that of a 1 kW arcjet thruster used successfully in a hr life test.