Propellant Losses Because of Particulate Emission in a Pulsed Plasma Thruster

Journal of Propulsion and Power - United States
doi 10.2514/2.5313
Full Text
Abstract

Available in full text

Date
Authors
Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Related search

Internal Langmuir Probe Mapping of a Hall Thruster With Xenon and Krypton Propellant

2006English

A Model for Plasma Ignition of Solid Propellant

2012English

The Ferroelectric Plasma Thruster

English

Plasma Properties Downstream of a Low-Power Hall Thruster

Physics of Plasmas
Condensed Matter Physics
2005English

Research and Development of a High-Power Electrothermal Pulsed Plasma Thruster System Onboard Osaka Institute of Technology 2nd PROITERES Nano-Satellite

2016English

Plasma Instability of Magnetically Enhanced Vacuum Arc Thruster

AIP Advances
NanotechnologyAstronomyPhysicsNanoscience
2019English

Influence of Azimuthally Nonuniform Propellant Flow Rate on Thrust Vector and Discharge Current Oscillation in a Hall Thruster

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN
2009English

“Radiative Losses in Plasma Accelerators”

Journal of Experimental and Theoretical Physics
AstronomyPhysics
2007English

Global Modeling of N2O Discharges: Helicon Plasma Thruster Application

International Journal of Aerospace Engineering
Aerospace Engineering
2013English

Amanote Research

Note-taking for researchers

Follow Amanote

© 2024 Amaplex Software S.P.R.L. All rights reserved.

Privacy PolicyRefund Policy