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Friday, July 31, 2020 | History

4 edition of Pulsed plasma thruster contamination found in the catalog.

Pulsed plasma thruster contamination

Pulsed plasma thruster contamination

  • 270 Want to read
  • 36 Currently reading

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

  • Contamination,
  • Plumes,
  • Plasma engines,
  • Pulsed jet engines,
  • Exhaust gases

  • Edition Notes

    StatementRoger M. Myers ... [et al.].
    SeriesNASA technical memorandum -- 107328.
    ContributionsMyers, Roger M., United States. National Aeronautics and Space Administration.
    The Physical Object
    Pagination1 v.
    ID Numbers
    Open LibraryOL17838500M

      Because of the advantages of low-cost, low-mass, and high specific impulse, electric propulsion thrusters (EPTs) for spacecraft orbit correction and interplanetary spacecraft acceleration have recently become the front subject and focal point in space propulsion fields [1, 2].As a member of EPTs, pulsed plasma thruster (PPT) has a broad prospect on small satellites for its small, compact, .   Thrusters That Eat Teflon! | Pulsed Plasma Thrusters - Duration: SciShow Space , views. The X3 Ion Thruster Is Here, This Is How It'll Get Us to Mars - Duration:

    Researchers at Purdue University have developed a liquid fed pulsed plasma thruster (LF-PPT) for use in nanosatellites. Contemporary solid/gas phase propellants have been employed with limited success in nanosatellites, stemming from low efficiencies, limited operational lifetime, contamination issues, and complex/bulky injection systems. This thesis gives a detailed design process for a pulsed type thruster. The thrust stand designed in this paper is for a Pulsed Plasma Thruster built by Sun Devil Satellite Laboratory, a student organization at Arizona State University. The thrust stand uses a torsional beam rotating to record displacement. This information, along with impulse-.

      Pulsed plasma thrusters (PPTs) are spacecraft propulsion devices that use plasma accelerated by an electromagnetic field created by a pulsed electrical discharge. The most common PPTs use a solid polymer, usually polytetrafluoroethylene (PTFE), as the propellant. These PPTs are called ablative pulsed plasma thrusters (APPTs). Chapters in Books. Burton, R. L., Rysanek, F., Antonsen, E. A., Wilson, M. J., and Bushman, S. S., "Pulsed Plasma Thruster Performance for Microspacecraft Propulsion.

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Pulsed plasma thruster contamination Download PDF EPUB FB2

A pulsed plasma thruster (PPT), also known as a plasma jet engine, is a form of electric spacecraft propulsion.

PPTs are generally considered the simplest form of electric spacecraft propulsion and were the first form of electric propulsion to be Pulsed plasma thruster contamination book in space, having flown on two Soviet probes (Zond 2 and Zond 3) starting in PPTs are generally flown on spacecraft with a surplus of.

Pulsed plasma thrusters (PPTs) are high-specific-impulse, low-power electric thrusters. Several tests of the EO - 1 thruster were performed at Glenn to demonstrate life capability, characterize contamination of spacecraft surfaces, and verify performance.

EO - 1's PPT is capable of producing a thrust of micro-Newtons ( pounds) and. Pulsed plasma thruster contamination. [Roger Metcalf Myers; Lewis Research Center,; United States.

National Aeronautics and Space Administration,] Electronic books Electronic government information: Additional Physical Format: Microfiche version: Pulsed plasma thruster contamination (OCoLC) Material Type. Pulsed plasma thruster contamination (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Roger Metcalf Myers; United States.

National Aeronautics and Space Administration. Pulsed plasma thruster contamination. Pulsed Plasma Thruster Plume Investigation Using a Current-Mode Quadruple Probe Method 23 May | Journal of Propulsion and Power, Vol.

20, No. 2 Preliminary Design and Analysis of a Directional Micro-Retarding Potential Analyzer for High-density Plumes. contamination study of a micro pulsed plasma thruster.

thesis. ceylan kesenek, 1st lt, tuaf. afit/ga/eny/m department of the air force. air university. air force institute of technology. wright-patterson air force base, ohio.

approved for public release; distribution unlimited. further impacts electrode erosion and contamination, as well as thermal housekeeping requirements. By investigating the e ects of many collective pulses, stress testing data is a direct source for evaluation of discharge models and thruster design.

Pulse-to-pulse variations are averaged and can be observed on a change of trend basis. This book provides an insight into the state-of-the-art in electric propulsion. An attempt is made to portray the technology in a logical fashion, starting with mission requirements.

Technology of the two dominant electric propulsion devices from basic physics through flight hardware is described. “Our system is better able to operate reliably for the entire mission and the liquid propellant we use does not create the contamination risks to the subsystems that we see with current options.” The Purdue team’s work was presented in June at the IEEE Pulsed Power and Plasma Science Conference in Orlando, Florida.

Pulsed Plasma Thruster Contamination. Pulsed Plasma Thrusters (PPT's) are currently baselined for the Air Force Mightysat II.1 flight in and are under consideration for a number of other.

Inefficiencies in a Pulsed Plasma Thruster,” 32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference,July,LakeBuenaVista, [4] Mikellides, P.

and Turchi, P. J., ”Modeling of Late-time Ablation in Teflon Pulsed Plasma Thrusters,”32nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference,July,LakeBuena Vista, PPTs at energy levels which ensures complete ionization and plasma formation for the given injected mass.

Second, the contamination risks associated with liquid propellant PPTs is relatively lower. water is one of the most attractive liquid propellant for pulsed plasma thrusters due to its relatively low 56 contamination risk. Pulsed Plasma Thrusters NASA Facts National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio – FS––11––GRC Introduction Pulsed plasma thrusters (PPTs) are high-specific-impulse, low-power electric thrusters.

Pulsed plasma thrusters are ideal for applications in small spacecraft for attitude. Pulsed plasma thrusters (PPTs) have been widely used in space flight applications due to their low cost and robustness.

Recently, it has been observed that during the operation of a PPT, the plasma plume exhibits an in-plume acceleration phenomenon where the leading-edge ions continue to accelerate in the plume even in the absence of electromagnetic forces.

Download Citation | Vacuum Chamber Construction and Contamination Study of A Micro Pulsed Plasma Thruster | The micro pulsed plasma thruster (micro-PPT) is a simple and versatile electric thruster. Pulsed plasma thruster (PPT) is an attractive micro-thruster for many flight missions.

Compared to other electric propulsion systems, PPT is more compact, lightweight and robust while lower in thrust efficiency. It is very difficult to solve this problem because of lacking of theoretically thorough understanding of the energy transformation.

16 Woronowicz, M.S., "Option 8 Plasma Magnetometer Boom Heating Analysis," S AI- /MSW-3, 28 September 17 Arrington, Lynn A., EO-1 Pulsed Plasma Thruster Test Report for the Contamination/Life Acceptance Test, NASA Glenn Research Center Verification Test Report, 11 September Vacuum Chamber Construction and Contamination Study of a Micro Pulsed Plasma Thruster Jacob H.

Debevec Follow this and additional works at: Part of the Aerospace Engineering Commons Recommended Citation Debevec, Jacob H., "Vacuum Chamber Construction and Contamination Study of a Micro Pulsed Plasma Thruster" (). Thrust and Performance Study of Micro Pulsed Plasma Thrusters [Jeremy J.

Selstrom] on *FREE* shipping on qualifying offers. This research is focused on several areas of the μPPT performance. An important idea studied is the effect of lifetime use on the performance.

The thruster is fired for a simulated lifetime of use to see if there is an impact on the thrust of the thruster. positioned by these thrusters. Introduction Pulsed plasma thrusters (PPTs) are low thrust electric propulsive devices which have a low power requirement, less than Watts, and high specific impulse greater than seconds.

_ PPTs can provide spacecraft attitude adjustments, high-precision positioning, and orbit raising on small satellite.The work presented in this report is an investigation of the plasma flow on a Teflon Pulsed Plasma Thruster (PPT), and the resulting plume.

The long range goal is a theoretical model of the flow, both between and beyond the thruster electrodes, that could aid in the improvement of performance, and also predict the contamination potential of the device.propulsion thrusters.1 This includes magnetoplasmadynamic thrusters for high specific impulse applications.

A type that has kept its potential for applications for over 40 years is the Pulsed Plasma Thruster (PPT), also known as Pulsed Magnetoplasmadynamic Thruster (iMPD).

This thruster combines the advantage of a simple and affordable.