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Deflagration plasma thrusterThis paper introduces the application of the magnetized plasma deflagration process to space propulsion. The deflagration process has the unique capability of efficiently converting input energy into kinetic energy in the accelerating direction. To illustrate the totally divergent characters of 'snowplow' detonation and deflagration discharges, examples of the differences between deflagration and detonation 'snowplow' discharges are expressed in terms of current densities, temperature, and particle velocities. Magnetic field profiles of the deflagration mode of discharges are measured. Typical attainable plasma characteristics are described in terms of velocity, electron temperature, and density, as well as measurement techniques. Specific impulses measured by piezo-electric probe and pendulum methods are presented. The influence of the transmission line in the discharge circuits on plasma velocity is measured by means of a microwave time-of-flight method. The results for the deflagration thruster are compared with other space thrusters. Further research areas are identified.
Document ID
19840049280
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Cheng, D. Y.
(International Power Technology, Inc. Sunnyvale, CA, United States)
Chang, C. N.
(International Power Technology, Inc. Sunnyvale, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Spacecraft Propulsion And Power
Accession Number
84A32067
Distribution Limits
Public
Copyright
Other

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