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Variable Specific Impulse MagnetoPlasma Rocket

QUESTIONS?

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

-

  • 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

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