conceptual design of a z-pinch fusion propulsion systemradams).pdf · decade module ii •500 kj...
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Conceptual Design of a Z-Pinch Fusion
Propulsion System
Advanced Concepts Office
George C. Marshall Space Flight Center
National Aeronautics and Space Administration
Robert Adams, Ph.D.
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Team Members
• Polsgrove T., Fincher, S., Adams, R. – NASA (MSFC)
• Fabisinski, L. - International Space Systems, Inc.
• Maples, C. - Qualis Corporation
• Miernik, J., Statham, G. - ERC, Inc.
• Cassibry, J., Cortez, R., Turner, M. - UAHuntsville
• Santarius, J. - University of Wisconsin
• Percy, T. - SAIC, Inc.
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
3
Z-Pinch Fusion: Background
• Nuclear weapon x-rays are simulated through Z-Pinch
phenomena.
• New developments in multi-keV plasma radiation
sources are progressing to thermonuclear fusion
temperatures*
• Such technology could be applied to develop advanced
thruster designs that promise high thrust/high specific
impulse propulsion
• This project would develop a conceptual design for such
a thruster.
*Velikovich, A. L., R. W. Clark, J. Davis, Y. K. Chong, C. Deeney, C. A. Coverdale, C. L. Ruiz, et al. 2007, Z-pinch plasma neutron sources,
Physics of Plasmas 14, no. 2: 022701. doi:10.1063/1.2435322.
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Operation of a Z Pinch
Cathode
Anode
Hypersonic Nozzle
I
Gas Cylinder
Evacuated Chamber
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High Current Generates Intense
Magnetic Fields
I
B, Magnetic Flux
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Magnetic Fields Compress the
Plasma to X-Ray Temperatures
Ion Motion B
X-rays
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Plasma Instability
• Rayleigh-Taylor is most
deleterious effect
preventing success,
can be overcome with
tailored density profile*
*Velikovich, Cochran, and Davis, Phys. Rev. Let. 77(5) 1996.
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Electrode Erosion
• Coupling electrical energy to plasma– Directly coupled devices lead to erosion
– All susceptible to x-ray radiation and neutron damage
• Potential workarounds– Allow electrodes to erode!
– Consider inductively coupled techniques
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Thruster Concept
Hypersonic NozzlesCathode
Anode
Z-Pinch
D-T Fuel
Secondary Fuel
And Radiation
Shield
MHD Generator
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Z-pinch Design
• Annular nozzles
with Deuterium-
Tritium (D-T) fuel in
the innermost
nozzle
• Lithium mixture
containing Lithium-
6/7 in the outermost
nozzle.
• The D-T fuel and
Lithium-6/7 mixture
acts as a cathode
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Z-pinch modeling
• Treat Z-pinch as Otto cycle
– Process 1-2: Isentropic compression
– Process 2-3: Constant volume heat
addition
– Process 3-4: Isentropic expansion
– Process 4-1: Constant volume heat
rejection
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Engine Performance
• Engine Performance as a function of liner mass
• Design point picked based on mission needs
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Nozzle Performance
• Particle trajectory modeling required to estimate
performance and correctly size nozzle.
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
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0.0%
5.0%
10.0%
15.0%
20.0%
25.0%
30.0%
35.0%
40.0%
45.0%
50.0%
0 20000 40000 60000 80000 100000 120000
Mission Delta-V (m/s)
Paylo
ad
% (
Paylo
ad
Mass /
IM
LE
O)
Mars Round Trip (90 Days One Way)
Mars Round Trip (30 Days One Way)
Jupiter Round Trip
One Way Trip to Mars (180 Days One Way)
One Way Trip to Mars (90 Days One Way)
Traditional Chemical
Propulsion
Z-Pinch Fusion
Propulsion
Missions to Mars, Jupiter, and Beyond can be achieved
with significantly reduced trip times when
compared to state of the art chemical propulsion
90 day transfer
from Earth to
Mars
Missions Enabled
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Mission Analysis
Mars 90 Mars 30 Jupiter 550 AU
Outbound Trip Time (days) 90.2 39.5 456.8 12936
Return Trip Time (days) 87.4 33.1 521.8 n/a
Total Burn Time (days) 5.0 20.2 6.7 11.2
Propellant Burned (mT) 86.3 350.4 115.7 194.4
Equivalent DV (km/s) 27.5 93.2 36.1 57.2
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
Figure 4.1 Mars 90 Day Transfer Trajectories
Mars Orbit
Earth Orbit
Transfer Traj Orbit
Transfer Trajectory
Mars Orbit
Earth Orbit
Transfer Traj Orbit
Transfer Trajectory
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Vehicle Configuration
Subsystem Mass (kg)
Payload 150,000
Structures 54,600
Main Propulsion 95,138
RCS 586
Thermal 77,164
Power 16,480
Avionics 389
Total Dry Mass 394357
30% MGA 73,307
Total Mass 467,664
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Thrust Coil Configuration
• FLiBe protects thrust and seed coils from thermal flux and
other radiation.
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
Seed Field
Superconductor
and LN2
coolant channelKapton
Insulator
Seed Coil
Load
Structure
Radiant Heat
Shield
Seed Field
Coil Housing
Evacuated
Region Molten mixture of lithium fluoride
(LiF) and beryllium fluoride (BeF2)
[FLiBe].
Thrust Coil
Load
Structure
Thrust Coil
Conductor
Diagram intended to illustrate the general
composition of the rings that comprise the nozzle.
Dimensions and aspect ratio to be determined
after detailed structural analysis.
Neutron
protection/cooling
channelZirconium diboride
(ZrB2) ceramic shell
Direction
of Fusion
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Power Management System
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
Recharging for next pulse one of the major
technical challenges for pulsed fusion
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Structural Analysis of Magnetic
Nozzle
• Structural truss can handles stresses from pulsed fusion
indefinitely.
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
• Focal point of
nozzle
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Thermal Management System
• Radiators operate at 300 K, 800 K and 1400 K.
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
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Avionics Suite
National Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office
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DECADE Module II
• 500 kJ pulsed power facility
• Last prototype built before DECADE construction
• Defense Threat Reduction Agency– Nuclear Weapons Effects (NWE)
– Plasma Radiation Sources (PRS)
• Good working order
• Capable of >1 TW instantaneous
power (about 6% of world's
electrical power consumption)
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Pulsed Fusion Facility
• DM2 Utilization Arrangements – L3 Communications, Pulsed Science Division
– Boeing
– Oak Ridge National Labs
• Other fusion collaborations– LANL
– HyperV Corp.
– Univ. of New Mexico
• Expected Capabilities– 500 ns pulse, 2 MA current
– 1 keV, 1025 /m3 plasma state
– Effective dwell time of ~100 nsAerophysics
lab
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Summary
• No showstoppers found for this technology– Preliminary analytical results are promising
– The technology development required for this propulsion system is
achievable on a reasonable timescale given sufficient resources.
• Z-pinch has potential for a number of missions of interest– Reusable vehicle that recaptures in Earth Orbit does round trips to Mars
– Interstellar precursor missions
– Crewed Missions to other solar system targets
• Opportunity to create new facility to explore z-pinch and
other pulsed fusion concepts– Looking for funding to move module to MSFC for installation
– Completed facility would allow proof of principle experiments on pulsed fusion
concepts.
• Our team thanks the NASA Innovative Programs and
Partnerships Program for funding this workNational Aeronautics and Space Administration
George C. Marshall Space Flight Center
ED04/Advanced Concepts Office