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Tuesday, November 17, 2020 | History

3 edition of Characterization of 8-cm engineering model thruster found in the catalog.

Characterization of 8-cm engineering model thruster

Characterization of 8-cm engineering model thruster

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Published by NASA Lewis Research Center, For sale by the Clearinghouse for Federal Scientific and Technical Information in Cleveland, OH, [Springfield, Va .
Written in English

    Subjects:
  • Ion rockets -- Propellant feed systems

  • Edition Notes

    StatementW.S. Williamson
    SeriesNASA-CR -- 174673, NASA contractor report -- 174673
    ContributionsLewis Research Center, Hughes Aircraft Company. Research Laboratories
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL17978275M

    PROTECTION OF MATERIALS AND STRUCTURES FROM THE SPACE ENVIRONMENT Space Technology Proceedings VOLUME 6 PROTECTION OF MATERIALS AND STRUCTURES FROM THE SPACE ENVIRONMENT ICPMSE-7 Edited by Jacob I. Kleiman Integrity Testing Laboratory Inc. Markham, Toronto, Canada A C.I.P. Catalogue record for this book . Mission concept: The mission consists of two spacecraft, one advanced and highly maneuverable one, called MAIN, and a smaller S/C without a maneuvering capability, called TARGET. The latter one simply follows the trajectory into which it is injected by the launch system.


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Characterization of 8-cm engineering model thruster Download PDF EPUB FB2

Get this from a library. Characterization of 8-cm engineering model thruster. [W S Williamson; Lewis Research Center.; Hughes Aircraft Company.

Research Laboratories.]. Hughes research and development laboratories, by Hughes Aircraft Company (Book) Robert L. Forward papers by Robert L Forward Ion thruster system (8-CM) cyclic endurance test (Book) 1.

30 cm Engineering Model thruster design and qualification tests. Characterization of ion and neutral efflux from a 30 cm mercury ion Characterization of 8-cm engineering model thruster book. Preliminary measurements of plasma fluctuations in an 8.

American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA In program yeartwo tasks were central to the NASA Hall thruster program: 1.) the development of a laboratory Hall thruster capable of providing high thrust at high power; 2.) investigations.

The neutralizer of a high-power ion thruster was characterized over a range of flow rates at the nominal thruster operating condition of A of ion beam current at a beam voltage of V. Near. the values from the computer generated model of Emre Turkoz [16]. Preliminary Design In the preliminary designs of the BURFIT (Bogazici University RF Ion Thruster), the proposed thruster.

Colorado State University Electric Propulsion & Plasma Engineering (CEPPE) Laboratory. The CEPPE Laboratory researches ion and hall thrusters, plasma propulsion technologies, and spacecraft. hybrid model of the interior channel and near fleld region of a laboratory Hall thruster,12 The simulated geometry corresponds to an annular thruster 8 cm in length, cm in width, and with an.

Stanford Hall Thruster, given that extensive experimental data exists for comparison purposes.7,8 The annular channel is approximately 8 cm in length and cm in width.

The computational grid, which. A gas from a high pressure supply tank that expands through a valve and a nozzle produces thrust Cold gas thrusters offer low impulse bits and can operate with contamination free, non toxic propellan t. Electrohydrodynamic thrust is an emerging propulsion mechanism for flying insect-scale robots.

There is a need to both minimize the operating voltage and maximize the output force when designing Cited by: 6. Ion Propulsion and accelerator industrial applications (IPAIA) This workshop will provide a forum for the presentation and discussion on the progress in methods and technologies used for the research.

Full text of "Technical activities Center for Materials Science" See other formats. Analysis of the Ion Thruster – See-Chen Lee Probability of Failure of the Ion Thruster – See-Chen Lee Analysis of the De-Spin Thruster – See-Chen Lee Conclusion –. PRISMA (Prototype Research Instruments and Space Mission technology Advancement) Overview Spacecraft Launch Mission Status Sensor Complement Ground Segment References.

PRISMA is a. The thruster consists of a tungsten cathode cm in diameter and 10 cm long, and a ring anode 10 cm i.d., 19 cm o.d., and 1 cm thick. The outer face of the anode is entirely exposed to the discharge, while.

Uniform metal contacts are critical for advanced thermoelectric devices. The uniformity of the contact resistance for gold, tungsten, and SrRuO 3 electrodes on polycrystalline ternary Bi 2 Te 3-based Cited by: 3. Assurance Technology Coporation: Capabilities 1. Production Facility Tenney Engineering Model 4D3 Thermal Vacuum Chamber Scanning Electron Microscopes Die Bond (x).

@article{osti_, title = {Three-dimensional particle-in-cell simulation on gain saturation effect of microchannel plate}, author = {Wang, Qiangqiang and Yuan, Zheng and Cao, Zhurong and Deng, Bo. Full text of "DTIC ADA A Review of United States Air Force and Department of Defense Aerospace Propulsion Needs" See other formats.

Eighteenth Symposium on Naval Hydrodynamics. Washington, DC: The National Academies Press. doi: / Induced "Warm Spots" The surface wave height and velocity of the water behind a. An ion (/ ˈ aɪ ɒ n,-ən /) is an atom or molecule that has a net electrical the charge of the electron (considered negative by convention) is equal and opposite to that of the proton (considered.

Optical Engineering Ebooks Advanced Search > Dr. Frank Morgan. Professional Staff at Johns Hopkins Univ Applied Physics Lab LLC. SPIE Involvement: Author Publications (12) Proceedings. Journal of Aerospace Technology and Management is a techno-scientific publication serialized, edited, and published by the Institute of Aeronautics and Space (Instituto de Aeronáutica e Espaço-IAE).

Figure 6: Functional block diagram of MAIN and TARGET (image credit: SSC) Launch: The two PRISMA satellites were launched successfully on J by ISC Kosmotras on a Dnepr-1 launch. A medical grade nitrous oxide (N2O) and gaseous oxygen (GOX) “Nytrox” blend is investigated as a volumetrically-efficient replacement for GOX in SmallSat-scale hybrid propulsion.

Inertial electrostatic confinement, or IEC, is a class of fusion power devices that use electric fields to confine the plasma rather than the more common approach using magnetic fields found in magnetic.

The NASA Johnson Space Center propulsion systems group built and operated the thruster in the Mauna Kea field test as part of the lunar “dust to thrust” demonstration.

The thruster used cryogenic oxygen. Calibration and characterization of a low-background chamber in support of hardware-in-the-loop testing and modeling of infrared seekers Richard Tschiegg, Steven Conard, Patrick Thompson, Adriaan Carter. Fig. shows the discharge current composition at the target surface for the discharge with Al target at discharge voltages of V, V, and V calculated by the IRM.

Note that for all discharge Author: Daniel Lundin, Ante Hecimovic, Tiberiu Minea, André Anders, Nils Brenning, Jon Tomas Gudmundsson, Jo. Open Source CubeSat Workshop Open Space Beyond Join us for a three days workshop to see how the open source approach can be applied to CubeSat (and Small Sat) missions with a focus on.

DLA Reverse Engineering Technical Data Packages for Development of Alternate Sources of Supply for DLA Nuclear Enterprise Support Office (NESO) NSN: ; DLA. Filed under: Liquid propellant rocket engines Performance evaluation of a two-stage turbine designed for a ratio of blade speed to jet speed of / (Washington, [D.C.]: National Aeronautics and Space.

EnviSat (Environmental Satellite) Overview Spacecraft Launch Mission Status Sensor Complement Ground Segment References.

EnviSat is an Earth observation mission of ESA (European Space. Figure 5: Block diagram of the OBDH system (image credit: ESA). The satellite command and control system: This system is organized around two OBDH systems (Figure 6), a master SM data-handling. To remedy this deficiency, a catalytic reactor model developed at Exxon Research and Engineering (1) was exercised.

A JP-4/air mixture at conditions indi- cated by the fluid mechanic model were input to. The linearized Euler model is known to be one of the most accurate models for such advanced simulations in that the model can take into account the effects of nonuniform and even unsteady.

Well, it took a while, but our "modern" LVDC assembler () has now been updated to assemble for a PTC target computer. Moreover, the transcription of the PTC ADAPT Self-Test. Conversion of instrument housekeeping items to engineering units Instrument Characterization Special Processing Dataflow Block Diagram Data.

e- satellite as an earth surveillance camera and then study of satellites compared to cameras as like a concept to spy electronics satellite circuit AMNIMARJESLOW GOVERNMENT XI XAM PIN .EPS (Electrical Power Subsystem): A large single-wing solar array (size of 9 m x 5 m = 45 m 2), deployed on the sunlit side of the spacecraft, maximizes both its power generation capability and the cold-space.

Characterization of 8-cm engineering model thruster. NASA Technical Reports Server (NTRS) Williamson, W. S. Development of 8 cm ion thruster technology which was .