Date post: | 02-Jan-2016 |
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Charge Exchange Containment Cell
Ryan Bosworth,
Doug Claes,
Michael Johnson,
and Trey Quiller
The Exploration and Space Technology (EaST) LabDr. Andrew Ketsdever
Department of Mechanical and Aerospace Engineering
• Motivation• Charge Exchange Process• Charge Exchange Cell– Design Stage– Overview of completed system
• Results
Introduction
• Electronic Propulsion has high mass due to power systems
• $10,000 per pound of payload to LEO using the Atlas and Delta launch systems
• New propulsion called Electrode-less Lorentz Force Thruster or ELF Thruster
Motivation
Charge Exchange
• Creating fast neutral particles to eject from the system• Mainly momentum transfer between particles• No kinetic energy lost• Minimal deviation from trajectory
Neutral Charge Exchange Gas
Ion Beam
Fast Neutrals
Remaining Ions
Vacuum
Designing the Device
• Main goals of design:– Contain a neutral gas in a vacuum environment– Vary neutral gas pressure– Constant neutral gas number density– Easy to machine device
• Went through an extensive design process
Building of Device
Experimental Testing
• Tested our best predicted configuration for best containment
• 200 milli-torr MKS differential pressure transducer
• Flow rates of 1, 5, 10, 15, 20, 25, 40, and 50 sccm
• Record chamber pressure, differential reading, and flow rates
Results
5 10 15 20 25 30 35 40 45 50 550
1
2
3
4
5
6
7
Differential Pressure for Argon
Flowrate(sccm)
CE
GC
Pre
ssu
re (
mT
orr
)
Thank you for your time.