1012 winglee[1]
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Transcript of 1012 winglee[1]
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MagBeam:
R. Winglee, T. Ziemba, J. Prager, B. Roberson, J Carscadden
• Coherent Beaming of Plasma
• Separation of Power/Fuel from Payload
• Fast, cost-efficient propulsion for multiple missions
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Plasma PropulsionMajor Savings in Mass through higher energy/speed plasma systems
Deep Space 1
Inherently low thrust systems: very low acceleration
Solar electric ~1 × 10-4 m/s/s
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Plasma PropulsionMajor Savings in Mass through higher energy/speed plasma systems
VASIMR
Inherently low thrust systems: very low acceleration
Solar electric ~1 × 10-4 m/s/s
Nuclear electric ~1 × 10-3 m/s/s
Long duration and/or costly dedicated power units for single missions
MagBeam: Focused Beaming of Plasma PowerSeparation of Power and Payload for High Thrust/Low
Propellant Usage
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Beam Propagation
Beam Expansion will reduce the efficiency of any beamed energy system
Nature regularly propagates plasma beams over 10’s km to 10’s of Earth radii
Able to do so by using collective behavior of plasmas
MagBeam uses these same collective processes to minimize beam dispersion
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Importance of MagBeam
Divergent Plasma Stream
Highly Focused Plasma Beam
Benefit 1:By studying focusing techniques obtain Higher Efficiency Plasma Thrusters
Can yield increases by factors of 50% performance
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Importance of MagBeam
Benefit 2:Compact electrodeless thrusters
Able to take high power operation without degradation
Means consider orbital transfers for large systems like Space Station
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Importance of MagBeam
• Modify spacecraft orbits (raise or lower)
Benefit 3:
• Planetary/lunar transfer orbital for multiple payloads
• Reduced cost due to reusable nature of system
Full up system would facilitate human exploration to the Moon, Mars and Beyond
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Plasma Plume
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Confined Plasma Plume
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Implementation of Magnetic Nozzle System
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High Power HeliconNozzle Magnet
Plasma Diagnostics
MagBeam Deflector
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UW: 6ft long x 5ft diameter Vacuum Chamber
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SimulationsMagnets: 30 cm; 5cm resolution
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Simulations
eei
ie
i Penn
n∇−
×+×−= ∑ 1
ene
BJBVE
0=×∇+∂∂ EBt
Evolution of Magnetic Field
Magnets: 30 cm; 5cm resolution
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Simulations
eei
ie
i Penn
n∇−
×+×−= ∑ 1
ene
BJBVE
0=×∇+∂∂ EBt
Evolution of Magnetic Field
Magnets: 30 cm; 5cm resolution
Log Plasma Energy DensityDensity 2 × 1013 cm-3
Bulk Speed: 30 km/s
Thermal Speed: ~ 30 km/s
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Simulations
eei
ie
i Penn
n∇−
×+×−= ∑ 1
ene
BJBVE
0=×∇+∂∂ EBt
Evolution of Magnetic Field
Magnets: 30 cm; 5cm resolution
Log Plasma Energy DensityDensity 2 × 1013 cm-3
Bulk Speed: 30 km/s
Thermal Speed: ~ 30 km/s
Multi-Fluid Equations
γt
0)( =⋅∇+∂∂
ααα ρρ V
αααααα
αρ Pnqdtd
∇−×+= ))(( rBVEV
ααααα PγPγtP
∇⋅−+⋅∇−=∂∂
VV )1()(
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Fix Diagnostic ProbesFix Diagnostic Probes
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No Nozzle Configuration
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High Power Helicon: No Magnetic Nozzle
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Improved Performance with Magnetic Nozzle
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With magnetic Nozzle
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High Power Helicon: With Magnetic Nozzle
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Far Field View of Beamed Plasma
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MagBeam: Hitting the Target
MagBeam Interaction
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MagBeam: Middle of Chamber
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MagBeam: End of Chamber
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MagBeam: Hitting the Target
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(a) MagBeam: Mid Chamber
0
1
2
3
4
5
6
0.00 0.05 0.10 0.15 0.20 0.25 0.30
time (ms)
Volta
ge
From HPH
From MagBeam
(b) MagBeam: End of Chamber
0.0
0.5
1.0
1.5
2.0
2.5
0.0 0.1 0.2 0.3 0.4time (ms)
Den
sity 350 V
200 V100 V
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Power System Requirements
• Fast Discharge Rates (associated with LEO and Geo)
• Best supplied by Batteries/Fuel Cells (recharge between missions)
• Present day capabilities is 400 W hrs/kg (1.5 MJ/kg)
• Expectation in the next decade might be 600 W hrs/kg
• Charging: - Solar Electric
•Space Station presently yields 100 kW using 6% efficiency
• Present day triple junction systems yield nearly 30% efficiency
- Nuclear Electric• Present day capabilities is 20 kg/kW
• Expectation in the next decade 5 kg/kW
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Bootstrapping into SpaceSuborbital + LEO Space Station
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Bootstrapping into Space
10,000 kg payload
5 min interaction time
200,000 kg batteries
300 MW thruster, 2000s Isp
800 kg of propellant
Suborbital + LEO Space Station∆V ~ 3 km/s
VERSUS
20,000 kg chemical rocket
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Suborbital to LEO ∆V ~3 km/s to Geo. Transfer ∆V ~+1.5 km/s
10,000 kg payloadRecharge batteries
Fire again
1,200 kg total propellant
VERSUS
30,000 kg chemical rocket
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To Escape Velocity ∆V ~+3 km/s
10,000 kg payload
30 min interaction time
200,000 kg batteries
Fire Again
2000 kg of propellant
VERSUS
65,000 kg chemical rocket
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Fast Trip to Mars: ∆V ~20 km/s
Longer Acceleration Period: Need to Start with Space Stationat higher Altitude
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Fast Trip to Mars: ∆V ~20 km/s
Rendezvous using geosynchronous-like transfer
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Fast Trip to Mars: ∆V ~20 km/s
10,000 kg payload
4 hr interaction time
3 × 106 kg batteries
300 MW thruster, Isp 4000s
or 1.5 × 106 kg advanced nuclear electric
7,000 kg of propellant
VERSUS
18,000,000 kg chemical rocket
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Mars Station Provides Braking: ∆V ~25 km/s
• ∆V ~ 7 km/s right at surface
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Total Trip Time: 0 Day - Start
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Total Trip Time: 50 Day - Arrive at Mars
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Total Trip Time: 61 Day - Leave Mars
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Total Trip Time: 96 Day - Arrive Eath
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MagBeam:Model/lab results demonstrating performance
Beamed Plasma System Fast MissionsReusable system & eliminates large power units for each new mission cost effective solution for multiple missions
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Roadmap:Phase II –
• Demonstrate beam coherence in expanded UW chamber (to 9 ft)
• Comparative model/lab studies in larger chambers (help from NASA centers to perform studies to 30 ft)
• Demonstrate performance of higher power thrusters and develop scaling laws for large systems
Further work– demonstrate km range using sounding rocket
experiment- orbital demonstration
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Still Finds the Target Even if Deflector Misaligned
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Differential motion between the ions and electrons are generated currents and electric fields such that the magnetic field in which the plasma is born stays with the plasma.
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Magnetic Field is essentially the transmission wire of space for plasma and power