Stationary plasma thruster plume characteristics

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National Aeronautics and Space Administration, National Technical Information Service, distributor , [Washington, DC], [Springfield, Va
Space vehicles -- Propulsion sys
StatementRoger M. Myers and David H. Manzella.
SeriesNASA contractor report -- 194454., NASA contractor report -- NASA CR-194454.
ContributionsManzella, David H., United States. National Aeronautics and Space Administration.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL14707717M

Stationary Plasma Thrusters (SPT's) are being investigated for application to a variety of near-term missions. This paper presents the results of a preliminary study of the thruster plume. Study of Plume Characteristics of a Stationary Plasma Thruster - NASA/ADS Electron density and temperature of the plume are measured by a double Langmuir probe in an experimental chamber.

A numerical model based on both particle-in-cell scheme and direct simulation Monte Carlo hybrid method is developed to simulate the flow field of plume. Plasma Characteristics Measured in the Plume of a Next Multi-Thruster Array [John E. Foster, Nasa Technical Reports Server (Ntrs), Et Al] on *FREE* shipping on qualifying offers.

Plasma properties in the plume produced by a 3+1 NEXT thruster array operating at full power were mapped using a series of planar Langmuir probes. The Langmuir probes were swept across the diameters of Cited by: Stationary Plasma Thrusters (SPT's) are being investigated for application to a variety of near-term missions.

This paper presents the results of a preliminary study of the thruster plume characteristics which are needed to assess spacecraft integration requirements. Stationary Plasma Thrusters (SPT's) are being investigated for application to a variety of near-term missions.

This paper presents the results of a preliminary study of the thruster plume Stationary plasma thruster plume characteristics book which are needed to assess spacecraft integration : David H.

Manzella and Roger M. Myers. Study of Plume Characteristics of a Stationary Plasma Thruster 22 October | Plasma Science and Technology, Vol. 10, No. 5 Far-Field Species Distribution Measurements on the BHT Hall Thruster ClusterCited by: Time-resolved measurement of plasma parameters in the far-field plume of a low-power Hall effect thruster 13 September | Plasma Sources Science and Technology, Vol.

21, No. 5 Stationary electron velocity distribution function in crossed electric and magnetic fields with collisionsCited by: Abstract. The global characteristics of an ATON stationary plasma thruster operating on xenon and krypton are investigated. It is shown that, with krypton, the thrust at the same mass flow rate of the working gas is greater and the efficiency is somewhat lower than those with by: Moreover, the plume plasma property was obtained to evaluate the loss mechanism of the W Hall thruster.

In this paper, the thrust performance and plume characteristics of the W Hall thruster are described, and the magnetic field requirement and performance improvement of low-power Hall thrusters are discussed.

Details Stationary plasma thruster plume characteristics FB2

Experimental apparatusAuthor: Hiroki Watanabe, Shinatora Cho, Kenichi Kubota. Stationary plasma thrusters (SPT, also called closed electron drift thruster of the Morozov type), are ion thrusters with high specific impulse and low thrust.

These features make them suitable for satellite station keeping or orbit by: Stationary Plasma Thruster (SPT) Hall thruster plume calculated using the Electric Propulsion Interactions Code (EPIC) [6,8] is shown in Fig.

As was the case for ion thrusters, the measured secondary ion fluxes were an order of magnitude less than fluxes measured in ground-based chambers, but, again, in good agreement with plume Size: KB. Get this from a library.

Stationary plasma thruster plume characteristics. [Roger M Myers; David H Manzella; United States. National Aeronautics and Space Administration.].

Thrust generated by the XPT was on par with conventional Hall thrusters [stationary plasma thruster (SPT) or thruster with anode layer] at the same power level (~11 mN at W with 25% anode. Pulsed plasma thrusters (PPTs) are a form of electric propulsion for spacecraft [1–5].They were first deployed in orbit on the Zond-2 spacecraft in [] and are highly suitable for small satellites [], especially with the recent discovery of promising alternative propellants [5, 8–10].As suggested by their name, they operate in a pulsed mode triggered by a spark by: 4.

Measurements of important electric thruster plume testing, the dominant collision process is plume parameters, particularly ion current charge exchange between the plume and density, can be significantly effected by the background gas species.

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Force Line Plasma Stream Ionization Zone Debye Layer Stationary Plasma Thruster These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm by: The stationary plasma thruster (SPT) developed behavior and, in spite of an extensive flight history in the former Soviet Union over the past several for the SPT (the 70 designates the exit diameter in decades characteristics in the SPT's plume.

This report. STATIONARY PLASMA THRUSTER PLUME CHARACTERISTICS Roger M. Myers1 and David H. Manzellaz Sverdrup Technology, Inc.

NASA Lewis Research Center Group Brookpark. OH Abstract Stationary Plasma Thrusters (SPTs) are being investigated for application to a. Stationary Plasma Thruster Plume Emissions David H. Manzella Sverdrup Technology Inc. Lewis Research Center Group Brook Park, Ohio The emission spectrum from a xenon plasma prod/g_ by a Stationary Plasma Thruster provided by the Ballistic Missile Defense Organ/ration (BMDO) was measmed Appmximatdy indvid_ Xe/_ Xe//, and Xe HI.

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 : Zhe Zhang, Zun Zhang, Haibin Tang, William Ling, Jiayun Qi, Jinbin Cao.

Pulsed plasma thrusters are ideal for applications in small spacecraft for attitude control, precision spacecraft control, and low-thrust maneuvers. Ablative PPTs using solid propellants provide mission benefits through system simplicity and high specific impulse.

Description Stationary plasma thruster plume characteristics EPUB

These systems exploit the natural properties of plasma to produce thrust and high. thrusters, Hall-effect thrusters (HETs), stationary plasma thrusters (SPTs), and magnetic-layer thrusters are all names for essentially the same device that is characterized by the use of a dielectric insulating wall in the plasma channel, as illustrated in Fig.

7 File Size: 1MB. MCC. model to study the plume of a stationary plasma thruster. The model is based on a fluid description of the electrons ~the electron density follows a Boltzmann distribution.

and a particle description of the ion and neutral transport. Collisions between heavy species are taken into account with a Monte Carlo by: Mass Spectral Measurements in the Plume of an SPT Hall Thruster: King, L.B. and Gallimore, A.D. Journal of Propulsion and Power: Ion Energy Diagnostics in the Plasma Exhaust Plume of a Hall Thruster: King, L.B.

and Gallimore, A.D. Journal of Propulsion and Power. Particle‐in‐Cell Simulation of Stationary Plasma Thruster.

Taccogna. E-mail address: simulation of the plasma‐wall interaction inside the acceleration channel and for ion‐neutral collision into the plume emitted from the thruster.

Results show the axial acceleration mechanism, the secondary electron emission instability, the Cited by: Non-Maxwellian electron energy probability functions in the plume of a SPT Hall thruster G Giono1,2, J T Gudmundsson1,3, N Ivchenko1, S Mazouffre4, K Dannenmayer5, D Loubère6, L Popelier6, M Merino7 and G Olentšenko1 1Department of Space and Plasma Physics, School of Electrical Engineering, KTH-Royal Institute of Technology, Stockholm, Sweden 2Leibniz-Institute of.

Modelling of plasma thruster plumes for spacecraft plume-impingement analysis Nuno Loureiro Under supervision of Prof. Jorge Loureiro Dep. Physics, IST, Lisbon, Portugal Octo Abstract Plasma thruster plume models for two types of electric thrusters are implemented in File Size: 1MB. tral plasma in a hybrid magnetoelectrostatic trap.2 The CHT features a reduced surface-to-volume ratio in comparison to a typical annular Hall thrusters so-called stationary plasma thruster or SPT Ref.

3, making it potentially less subject to channel wall erosion by ion-induced sputtering, and more attractive for scaling down to operate at low File Size: 1MB. thruster with magnetic layer5 ~TML!, thruster with extended acceleration zone,6 and most commonly now stationary plasma thruster ~SPT!.

In another variant of the Hall thruster,7 the channel walls are electrically conducting, bi-ased to the cathode potential and much shorter than the chan-nel width. In this configuration, the electrons retain. COVID Resources.

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The interaction between the plume of Hall thruster and the surface of the SMART-1 spacecraft is investigated by developing a three-dimensional IFE-PIC-MCC code, with the emphasis on the effect of the disturbance force and thermal loading caused by charge exchange ions (CEX) impingement on the surface of the spacecraft.

The parameters such as heat flux and forces of CEX ions which impinge on Cited by: 4.In spacecraft propulsion, a Hall-effect thruster (HET) is a type of ion thruster in which the propellant is accelerated by an electric field. Hall-effect thrusters use a magnetic field to limit the electrons' axial motion and then use them to ionize propellant, efficiently accelerate the ions to produce thrust, and neutralize the ions in the plume.HALL THRUSTER SYSTEMS Stationary Plasma Thruster (SPT) Thruster with Anode Layer (TAL) Performance Characteristics Power: - 3 kW (50 kW) Thrust: mN Specific Impulse: s ( s) Efficiency: % Typical Propellant: Xenon ArgonFile Size: 8MB.