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Performance Measurements of Electric Solid Propellant in an Ablative Pulsed Electric ThrusterElectric solid propellants are advanced solid chemical rocket propellants that can be controlled (ignited, throttled and extinguished) through the application and removal of an electric current. These propellants may also be used for electric in-space propulsion, specifically in the ablative pulsed plasma thruster. In this paper, we will investigate the performance of an electric solid propellant operating in an ablation-fed pulsed plasma device by use of an inverted pendulum micro-Newton thrust stand. Namely, the impulse-per-pulse and the specific impulse of the device using the electric solid propellant will be reported for test runs of 100 pulses and energy levels of 5, 10, 15 and 20 J. Further, the device will also be tested using the current state-of-the-art pulsed plasma thruster propellant, polytetrafluoroethylene. The performance of each propellant will be compared for each energy level using an identical setup and apparatus. This comparison of performance between propellants in a controlled setting will allow for better understanding of previous experimental observations.
Document ID
20190030421
Acquisition Source
Marshall Space Flight Center
Document Type
Abstract
Authors
Glascock, Matthew S.
(Missouri Univ. of Science and Technology Rolla, MO, United States)
Rovey, Joshua L.
(Illinois Univ. at Urbana-Champaign Urbana, IL, United States)
Polzin, Kurt A.
(NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 4, 2019
Publication Date
August 19, 2019
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
M19-7213
Meeting Information
Meeting: AIAA Propulsion and Energy Forum and Exposition
Location: Indianapolis, IN
Start Date: August 19, 2019
End Date: August 22, 2019
Sponsors: American Institute of Aeronautics and Astronautics (AIAA)
Distribution Limits
Public
Copyright
Public Use Permitted.
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