NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Magnetic Flux Compression Using Detonation Plasma Armatures and Superconductor Stators: Integrated Propulsion and Power ApplicationsThis presentation discusses the use of magnetic flux compression for space flight applications as a propulsion and other power applications. The qualities of this technology that make it suitable for spaceflight propulsion and power, are that it has high power density, it can give multimegawatt energy bursts, and terawatt power bursts, it can produce the pulse power for low impedance dense plasma devices (e.g., pulse fusion drivers), and it can produce direct thrust. The issues of a metal vs plasma armature are discussed, and the requirements for high energy output, and fast pulse rise time requires a high speed armature. The plasma armature enables repetitive firing capabilities. The issues concerning the high temperature superconductor stator are also discussed. The concept of the radial mode pulse power generator is described. The proposed research strategy combines the use of computational modeling (i.e., magnetohydrodynamic computations, and finite element modeling) and laboratory experiments to create a demonstration device.
Document ID
19990110664
Acquisition Source
Marshall Space Flight Center
Document Type
Reprint (Version printed in journal)
Authors
Litchford, Ron
(NASA Marshall Space Flight Center Huntsville, AL United States)
Robertson, Tony
(NASA Marshall Space Flight Center Huntsville, AL United States)
Hawk, Clark
(Alabama Univ. Huntsville, AL United States)
Turner, Matt
(Alabama Univ. Huntsville, AL United States)
Koelfgen, Syri
(Alabama Univ. Huntsville, AL United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1999
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: Advanced Space Propulsion
Location: Huntsville, AL
Country: United States
Start Date: April 5, 1999
End Date: April 8, 1999
Sponsors: NASA Marshall Space Flight Center, NASA Headquarters, Jet Propulsion Lab., California Inst. of Tech., American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available