637127main tarditi presentation
TRANSCRIPT
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Aneutronic Fusion Spacecraft Architecture
A. G. Tarditi1, G. H. Miley2 and J. H. Scott3
1University of Houston – Clear Lake, Houston, TX 2University of Illinois-Urbana-Champaign, Urbana, IL
3NASA Johnson Space Center, Houston, TX
NIAC 2012 – Spring Meeting, Pasadena, CA
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Aneutronic Fusion Spacecraft Architecture
A. G. Tarditi1, G. H. Miley2 and J. H. Scott3
1University of Houston – Clear Lake, Houston, TX 2University of Illinois-Urbana-Champaign, Urbana, IL
3NASA Johnson Space Center, Houston, TX
NIAC 2012 – Spring Meeting, Pasadena, CA
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• Exploration of a new concept for space propulsion suitable for aneutronic fusion
• Fusion energy-to-thrust direct conversion: turn fusion products kinetic energy into thrust
• Fusion products beam conditioning: specific impulse and thrust compatible with needs practical mission
Summary
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Where all this fits: the Big Picture
Fusion Research
Electric Space
Propulsion
Fusion
Propulsion
Plasma
Propulsion
• “Big time” space travel needs advanced propulsion at the 100-MW level
• This really means electric propulsion • Electric propulsion needs fusion
Advanced Electric Utility Technology
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Introduction - Space Exploration Needs
“Game changers” in the evolution of human transportation
?
?
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Introduction - Space Exploration Needs
• Incremental modifications of
existing space transportation designs can only go so far…
• Aerospace needs new propulsion technologies
?
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• A new propulsion paradigm that enables faster and longer distance space travel is arguably the technology development that could have the largest impact on the overall scope of the NASA mission
• In comparison, every other space technology development would probably look merely incremental
• Investing in R&D on new, advanced space propulsion architectures could have the largest impact on the overall scope of the NASA mission.
Introduction - Priorities
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• Utilization of fusion energy for spacecraft propulsion may be one of the most compelling research directions for the development of the future space program
• Fusion research has reached a high level of scientific and technological maturity through a half-century of remarkable progress
Introduction – Fusion Propulsion
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• Even if a fusion reactor were to be available today, its successful application to space propulsion would be constrained by the requirements of integration with an electric thruster
• Overall system mass and efficiency is ultimately all that matters if a significant step-change in the potentials of space travel is to be achieved
• Key figure of merit: specific mass α [kg/kW]
Introduction – Fusion Propulsion
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• Design a spacecraft architecture that, for a given payload, enables the most capable missions
• Focus on minimal overall system specific mass α (kg/kW)
• Choose highest energy density source (fusion is just second to matter-antimatter annihilation) and…
• …a propulsion scheme with a minimal-mass and highest-efficiency in propellant acceleration
Motivation
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Ideal Space Propulsion
• Utilize fusion products directly for production of thrust
• The most efficient propulsion system will utilize the highest energy density source and the simplest propulsion configuration
Low-Mass Fusion Core
Fusion Products Exhaust
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Fusion Propulsion
? Fusion Reactor Plasma Jet Thrust
Ideal case:
Light fusion core => Fusion Products => Exhaust
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Indirect Fusion Propulsion
Electric power production and plasma generation/acceleration in an indirect fusion propulsion scheme
Plasma Accelerator
Auxiliary Systems
Electric Power
Magnetic Nozzle
Exhaust
Fusion Reactor
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Auxiliary Systems
Fusion Reactor Beam Conditioning
System Exhaust
Fusion Products Beam
Direct Fusion Propulsion
Plasma exhaust production in a direct fusion propulsion scheme
Electric Power
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Mission Design
• For a given mission and given power and initial mass, there is an optimal specific impulse profile that allows the fastest transfer
• In the gravity-free approximation, it can be shown that the optimal specific impulse (Isp) is proportional to the trip time (shorter trips will require more thrust, less Isp) [Moeckel, 1972]
• For “reasonable” travel in the Solar System the optimal Isp is in the 104 s range
W. E. Moeckel, J. Spacecraft, 6 (12), 863 (1972) and NASA-TN D-6968 (1972)
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Aneutronic Fusion
• Fusion products from main aneutronic reactions: – p + 11B => 3 4He +8.7 MeV – 2.9 MeV α-particle ’ speed ≈107 m/s (simplification:
each α-particle is considered having an energy of 2.9 MeV)
• D + 3He => p (14.7 MeV) + α (3.7 MeV) – 3.7 MeV α-particle ’ speed ≈1.3· 107 m/s – 14.7 MeV proton ’ speed ≈ 5.3·107 m/s
• These reactions give a specific impulse in the 106 s range; too high for most practical purposes
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Basic Constraints
• A jet of particles (beam) with velocity v and a mass flow equal to dM/dt (kg/s)
• (Momentum) Thrust Fth=v (dM/dt) • The specific impulse is conventionally expressed in
seconds and defined as Isp=v/g0 , where g0 is the Earth gravity acceleration
• Then, for a given power, to decrease the Isp and increase the thrust at the same time the mass flow needs to be increased
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Old Thinking: “Slush” Plasma Propellant
• The α’s are injected into a denser, cold plasma • After exchanging momentum and energy the
propellant will be faster and warmer
• A magnetic nozzle will redirect (most of) the thermal energy into the direction of thrust
α−beam
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• By injecting the alpha's with a large angle w.r.t. the axis of the magnetic nozzle solenoidal field the longitudinal speed will be reduced.
• The gyro radius for a 2.9 MeV α in a 1 T field is about 0.25 m: to capture the ions the injection has to be non-adiabatic (plasma collisions)
α−beam
Old Thinking: “Slush” Plasma Propellant
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The Proposed Approach: Fusion Energy-to-Thrust Direct
Conversion
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Fusion Energy to Thrust Direct Conversion
TWDEC
Fusion Reactor
Electric Power
Fast Ion Bunch
Exhaust
Ion Beam
Collector
Slow/Dense Ion Source
Fast-to-Slow Bunch
Energy Transfer Fast Ions
Dense Slow Ion Bunch
Neutralizing Electrons
System concept (TWDEC=Travelling Wave Direct Energy Converter)
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Converting Beam Energy into Thrust
Two basic processes operate concurrently: 1. Fast-to-Slow Bunch electrostatic energy exchange
2. Magnetic Piston effect created by fast beam bunches confined into a spiral trajectory
Electric Field
Slow, Dense Bunch Speeds Up Fast Ion Bunch
Slows Down
j
vbunch
Slow, Dense Bunch Speeds Up
Fast Ion Bunch Slows Down
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1) Fast-to-Slow Bunch Energy Exchange
Electric Field
Bunch Formation – (Hollow Electrodes)
Slow Dense Bunch Speeds Up
Fast Ion Bunch Slows Down
Guide Magnetic Field Coil
Fast Ion Bunch
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Fast-Electron, Neutralized Beam Scenario
Slow Dense Bunch Speeds Up
Fast-Electrons (neutralizing, not
recombining)
Fast-electron beam (possibly partially neutralizing) may allow higher densities
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“Magnetic Piston”: an Old Concept
Concept illustration (from W.B. Kunkel, “Plasma Physics in Theory and Applications”, 1966)
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Collimated α−beam
Magnetic Piston: 1) Beam Injection
B
• The gyro-radius for a 2.9 MeV α−particle in a 1 T field is about 0.25 m.
• Bunching can allow for non-adiabatic injection required to capture the ions.
STEP 1. Injecting fusion products with a large angle w.r.t. the
axis of a solenoidal magnetic field: the longitudinal speed will be
reduced and particles follow a spiral orbit
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STEP 2. With a collimated, pencil-beam injection, the
accumulation of ion bunches forms a current ring
2) Formation of Current Layer
j
Traveling Storage Ring”
B
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STEP 3. As more particles are collected the current in the
layer increases that, in turn, increases the magnetic field
3) Magnetic Field Increase
j
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j
Magnetic Piston Pushing Target Ion Bunch
Slow Dense Bunch Speeds Up
vFastBunch
Fast Ion Bunch Slows Down
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Particle-in-Cell Simulation
Testing α-particle bunch expansion in 0.1x1 m “can”
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Near-Term Experimental Plans
• University of Illinois Urbana-Champaign (UIUC) Fusion Studies Lab: experimental campaign on key physics issues: – Utilization of the Helicon Injected Inertial Plasma
Electrostatic Rocket (HIIPER) plasma jet for the generation of a high-density ion “bunched” beam
– Validating the direct energy-to-thrust conversion via fast-slow bunch interaction
– Testing of the TWDEC at higher density: TWDEC stage directly connected to a IEC plasma device.
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UIUC Fusion Studies Lab
IEC Device at UIUC: 50 kV, 50 mA, 1 kW max. 44” diameter spherical stainless steel IEC chamber. Base vacuum <10-6 Torr
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IEC Device at UIUC: plasma from a 2.2 kW Helicon source
UIUC Fusion Studies Lab
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IEC Device at UIUC: IEC plasma with energized grid and formation of plasma jet
UIUC Fusion Studies Lab
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Research Plan F.Y. 2011-2012
1st Quarter Physics process definition at the system-level and evaluation of overall performances.
2nd Quarter Particle-in-Cell computer modeling and simulation of subcomponents
3rd Quarter System-level modeling refinement, in-depth simulation and testing of overall performances and key physics issues
4th Quarter Revised detailed design. Final recommendation for next-step developments.