Variable Specific Impulse MagnetoPlasma Rocket
Transit times
- 90 day trip
- Zero Earth & Mars relative velocity
- 60 % net efficiency
Physics of Aft Cell
- Axially Asymmetric Magnetic Field
- Varied to adjust exhaust rate
- Magnetic Field (0.6 Tesla)
- Plasma < 1 Mega Kelvin
- Ions leaving ~ 50,000 m/s
- Ion Cyclotron Resonance Heating
Ion Cyclotron Resonance Heating
- Radio Frequency Heating
- Ions circle around field lines
- ~170 kW
Physics of Central Cell
- Tandem Mirror Magnetic Field (1.2 Tesla)
- Bottles plasma & converts Thermal into Kinetic Energy
- Cassady, Leonard D, et al. "VASIMR Performance Results." Joint Propulsion Conference & Exhibit (2010).
- Chang Diaz, Franklin R., Michael M. Hsu, Ellen Braden, Ivan Johnson, and Tien F. Yang. "Rapid Mars Transits With Exhaust- Modulated Plasma Propulsion." NASA Technical Paper 3539 (1995).
- Chang Diaz, Franklin R. "The VASIMR." Scientific American Nov. 2000: 90-97.
- Ilin, Andrew V , et al. "VASIMR® Human Mission to Mars." Space, Propulsion & Energy Sciences International Forum (2011).
- Longmier, Benjamin W. "VX-200 Magnetoplasma Thruster Performance Results Exceeding Fifty-Percent Thruster Efficiency."JOURNAL OF PROPULSION AND POWER 27.4 (2011).
- Squire, Jared P. "VASIMR® VX-200 Operation at 200 KW and Plume Measurements: Future Plans and an ISS EP Test Platform." IEPC-2011-154 (2011).
- "Technology." Ad Astra Rocket Company. Ad Astra Rocket Company. 18 Apr. 2012. <http://www.adastrarocket.com/aarc/Technology>.
- "Diagnostics Used For The VASIMR VX-200i." YouTube. YouTube, 17 Apr. 2009. Web. 18 Apr. 2012. <http://www.youtube.com/watch?v=o5_b_to4pdk>.
Works Cited
Physics in forward cell
Helicon Antenna
VASIMR
- Helicon Waves
- Radio Freq. EM waves
- Presence of Magnetic Field
- Solid State Build
- 10-50 MHz
- 15-35 kW
- Plasma
- Cold State
- ~60,000 K
- Gaseous Injection
- Neutral Gas through Quartz tube
- Magnetic Field Bottling(0.24 Tesla)
- BSCCO Super-Conducter
- Liquid Nitrogen Cooling
- Helicon Antenna
- Heats & Ionizes
Thrust & Specific Impulse
- Amount of Speed attainable per unit mass of propellant
- Varieties of Fuel (Neon, Argon, Xenon, Nitrogen, Deutrium, Hydrogen, Helium )
- Thermal transition to Kinetic
- Compact Design
- Relatively Fast Transit Times
- Magnetic Shielding from Radiation
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- External Magnetic Field Interactions (Quadrupole mitigation)
- Thermal Heat Management
- Equipment Interference
- Environmental Limitations (10-7 torr)
Benefit & Drawbacks
- 200 kW to antennas
- 10 MW Solar Panel Array
- Fission Nuclear Reactor (Optimistic)
- 68% efficiency
- Specific Power 6 kg/kW
- High Voltage, Low current Antennas
Cost of Power
- 3 cells
- Electrode-less engine
- Utilizes a variety of Modern Physics to produce controlled outbursts
Overall Design and layout
- Using 20th Century physics to create 21st technology
- New faster degree of space travel
- Currently being developed by Ad Astra Company
21st Century Rocket