One of the authors of this paper is George Miley
-DonW-
http://stinet.dtic.mil/oai/oai?&verb=getRecord&metadataPrefix=html&identifier=ADA446973
Accession Number : ADA446973
Title : Propulsion and Power Generation Capabilities of a Dense Plasma
Focus (DPF) Fusion System for Future Military Aerospace Vehicles (POSTPRINT)
Descriptive Note : Conference Paper
Corporate Author : AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION
DIRECTORATE
Personal Author(s) : Knecht, Sean D. ; Mead, Franklin B. ; Thomas, Robert E.
; Miley, George H. ; Froning, David
Handle / proxy Url : http://handle.dtic.mil/100.2/ADA446973
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Report Date : 06 OCT 2005
Pagination or Media Count : 8
Abstract : The objective of this study was to perform a parametric
evaluation of the performance and interface characteristics of a dense
plasma focus (DPF) fusion system in support of a USAF advanced military
aerospace vehicle concept study.
This vehicle is an aerospace plane that combines clean "aneutronic" dense
plasma focus (DPF) fusion power and propulsion technology, with advanced
"waverider"-like airframe configurations utilizing air-breathing MHD
propulsion and power technology within a reusable single-stage-to-orbit
vehicle.
The applied approach was to evaluate the fusion system details (geometry,
power, T/W, system mass, etc.) of a baseline p-11B DPF propulsion device
with Q = 3.0 and thruster efficiency, eta prop = 90% for a range of thrust,
Isp and capacitor specific energy values.
The baseline details were then kept constant and the values of Q and eta
prop were varied to evaluate excess power generation for communication
systems, pulsed-train plasmoid weapons, ultrahigh-power lasers,
shielding/cloaking devices and gravity or time-distorting devices.
Thrust values were varied between 100 kN and 1,000 kN with Isp of 1,500 s
and 2,000 s, while capacitor specific energy was varied from 1 - 15 kJ/kg. Q
was varied from 3.0 to 6.0, resulting in gigawatts of excess power.
Thruster efficiency was varied from 0.9 to 1.0, resulting in hundreds of
megawatts of excess power. Resulting system masses were on the order of 10's
to 100's of metric tons with thrust-to-weight ratios ranging from 2.1 to
44.1, depending on capacitor specific energy.
Such a high thrust/high Isp system with a high power generation capability
would allow military versatility in sub-orbital space, as early as 2025, and
beyond as early as 2050. This paper presents only the views and
recommendations of the authors themselves and are not necessarily those of
the Air Force.
Descriptors : *AEROSPACEPLANES, MILITARY OPERATIONS, SYMPOSIA, AUSTRALIA,
CAPACITORS, SUBORBITAL TRAJECTORIES, HYBRID PROPULSION, AIR BREATHING
ENGINES(UNCONVENTIONAL), MAGNETOHYDRODYNAMICS, THRUSTERS, PLASMAS(PHYSICS),
ELECTRIC POWER PRODUCTION
Subject Categories : RESEARCH AND EXPIRIMENTAL AIRCRAFT
PLASMA PHYSICS AND MAGNETOHYDRODYNAMICS
Distribution Statement : APPROVED FOR PUBLIC RELEASE
