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5–42880b

Advanced Propulsion Concepts. To National Space Society Huntsville Alabama L5 Society John Cole November 12, 2004. 5–42880b. Contents. The Goals and Objectives of the President’s Vision The Horizons Avenues Chemical Electromagnetic Nuclear Concluding Remarks. 5–42880b.

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5–42880b

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  1. Advanced Propulsion Concepts ToNational Space SocietyHuntsville Alabama L5 Society John Cole November 12, 2004 5–42880b

  2. Contents • The Goals and Objectives of the President’s Vision • The Horizons • Avenues • Chemical • Electromagnetic • Nuclear • Concluding Remarks 5–42880b

  3. The President’s Visionfor U.S. Space Exploration • Goal and Objectives • The fundamental goal of this vision is to advance U.S. scientific, security, and economic interests through a robust space exploration program.In support of this goal, the United States will: • Implement a sustained and affordable human and robotic program to explore the solar system and beyond. • Extend human presence across the solar system, starting with a human return to the Moon by the year 2020, in preparation for human exploration of Mars and other destinations. • Develop the innovative technologies, knowledge, and infrastructures both to explore and to support decisions about the destinations for human exploration. • Promote international and commercial participation in exploration to further U.S. scientific, security, and economic interests. • http://www.nasa.gov/missions/solarsystem/explore_main.html • February 3, 2004 5–42880b

  4. The Horizons • Human missions beyond Jupiter may require: • Velocity changes > 200 km/s. Implies Initial Vehicle Specific Energy ~ 14 GJ/kg. For comparison: a tank of H2 and O2 ~ 10 MJ/kg. • Trip times of less than 2–3 years. • Implies Initial Vehicle Specific power > 3–10 KW/kg. • For comparison: the Delta 4 provides ~ 30 KW/kg. • But Prometheus Jupiter Icy Moons Orbiter (JIMO) provides < 20 Watts/kg. • Payload mass similar to ISS plus an equal propellant mass. • Extraterrestrial assembly, possibly lunar manufacturing. • Many orbit transfer missions. • Many launches from Earth. • Propulsion technologies in the pipe-line can get us started (Atlas V, Delta IV, JIMO). • Clearly, advanced propulsion technologies are needed. • Very little is completely new, relook at overlooked ideas. • Many Avenues Exist; Some May Lead To Solutions. • February 3, 2004 5–42880b

  5. Earth Escape • Earth escape durations: • Of a few days will require> 100 W/kg, total vehicle. • Of a few months will require< 10 W/kg. • 100 MT to escape implies power levels of 1–10 MW. • New solar array technologies of> 300 W/kg (just arrays) should enable vehicles withPsp ~ 20 W/kg andfuel fractions < 0.1. • Prometheus nuclear electric propulsion (NEP) type technology will provide avehicle Psp > 20 W/kg. Assumes constant acceleration perpendicular to the gravity. 5–42880b

  6. Round-trip Planetary Missions Propellant Fraction = 0.632 • Round trips of 2 to 3 years to points beyond Mars imply a large initial Vehicle Specific Power of 3 to 10 KW/kg. • This is well beyond the current capabilities of solid or liquid core reactor concepts. 5–42880b

  7. – + HAN, an ionic liquid Potential Research • Advanced chemical propellants • Focus on high energy density materials (HEDM). • Energy density of chemical propulsion is fundamentally limited but significant potential performance gains do exist. High energy, environmentally benign monopropellants. Metallic Hydrogen Synthesis Solid molecular hydrogen particles (H2 matrix) formed on liquid helium surface (circled area) EnergeticHydrocarbon Fuels Ionic Liquid Monopropellant Recombination Energy Fuels 5–42880b

  8. – + HAN, an ionic liquid High-energy Density Monopropellants The Air Force has formulated several monopropellants that substantially outperform hydrazine and even surpass bipropellants for some applications. NH3OH+ NO3- Novel energetic salts have higher energy densities and reduced vapor toxicities compared with hydrazine. Enabling new missions—smaller vehicles, more payload, higher V, longer useful vehicle lifetime. Cutting costs—monopropellant-based propulsion systems are simpler, smaller, and less costly than bipropellant systems. 5–42880b

  9. Metallic Hydrogen • What is metallic hydrogen? Under intense pressure the hydrogen atoms become so close together that the electrons easily move from atom to atom. • Most solid state theories predict “metastable” state, will remain in the metallic form when the pressure is released up to an unknown critical temperature • Benefits • The estimated specific impulse of metallic hydrogen is 1,700 second. Specific energy ~ 140 MJ/kg. • The density will be much higher than liquid hydrogen. • The performance improvement may reduce costs. • Research Objectives • To find whether metallic hydrogen can be produced. • Then determine if metastable and critical temperature • Can metallic hydrogen be affordably produced, handled, and used? • Metallic Hydrogen enables single-stage-to-Lunar or Mars landing and return! Diamond anvil cell, Silvera 5–42880b

  10. Energetic Combustion Devices • Powdered Metal Combustion Technology • Endoatmospheric Mars propulsion. • Metals/CO2 combustion utilizes in-situ resources. • Ascent stage for Mars sample return mission. • Thermal driver for pulse power MHD generator. • Nonequilibrium Plasma Generator (NPG) concept. • High-power airborne auxiliary power unit (APU). • Adapt existing experimental device to investigate fundamental combustion processes. • Pressurized rig with optical access. • Positive displacement fluidized bed feed system. • Demonstrate prototypical rocket mode operation. Powdered Metals Research Combustor 5–42880b

  11. Potential Research • Electromagnetics and Plasma-based Propulsion • Focus on MW-Class electric thrusters. • Plasma production, control, and containment. • Electromagnetic launch assist. • Components (flightweight and high-power). • Includes beamed energy propulsion. Electric Microthrusters Magnetohydrodynamic Augmented PropulsionExperiment (MAPX) MHD-augmented Thrusters Flightweight Magnets Electromagnetic Launch Assist MW-class Electric ThrustersEnabling for High-power NSI Beamed Energy Propulsion 5–42880b

  12. Horizontal Launch Assist • Weight Savings • Some fuel reduction from initial velocity • For a Horizontal Take-Off, Horizontal Landing (HTHL) vehicle the thrust and engine weight is 60% that for VTHL. • Launch assist can reduce take-off and landing gear to that needed for landing. • 200 m/s launch assist can reduce wing size to that needed for landing empty. • Electromagnetic launch assist has now been developed by the Navy. • Flywheel energy storage technology is mature and improving. • This technology is ready forreconsideration. 5–42880b

  13. Gallium Electromagnetic Thruster • Gallium Electromagnetic Thruster (GEM) • Two-stage pulsed plasma thruster that avoids gas valves and high-current switches and mitigates electrode erosion. • Performance characteristics: • 50–500 kW power level. • 5,000–100,00 sec Isp, variable. • >50% efficiency. 5–42880b

  14. Plasmoid Thruster • Plasmoid ThrusterAn inductive pulsed plasma thruster that repetitively forms and accelerates a compact toroidal (magnetized) plasmoid. • Performance characteristics • 100 kW—1 MW power level. • 5,000—10,000 sec specific impulse. • > 50% efficiency. 5–42880b

  15. Variable Specific Impulse Magnetoplasma Rocket (VASIMR) • Helicon plasma is heated using ion cyclotron resonance heating (ICRH), ejected through magnetic nozzle. • No electrodes or other materials in direct contact with the plasma. • Therefore, potential for very high power density, high reliability, long life. • Multiple propellants: hydrogen, deuterium, helium, nitrogen, argon, xenon, and others. • Scalable beyond 10s of megawatts. • The biggest challenge is energy efficiency at low specific impulse. NASA Johnson Space Center Advanced Space Propulsion Laboratory 5–42880b

  16. Helicon-Electron-Cyclotron-Resonance Acceleration Thruster (HEAT) • Uses antenna and plasma waves instead of electrodes. • Radio waves heat plasma. • Magnetic field accelerates hot plasma. • No electrodes: • Increases operating life. • Allows in situ propellant use in space. Small (10 cm long, 2 cm diameter) helicon source in operation. Glenn Research Center 5–42880b

  17. Jupiter Icy Moons Orbiter 5–42880b

  18. Advanced Nuclear Propulsion • Advanced Nuclear Propulsion • Focus on high specific energy/power concepts. • Highly enabling for human/robotic exploration. • 106 improvement in specific energy over chemical. • Potential for system specific power > 1 kW/kg. (U,Zr,Nb)C Sample High-temperature Fission Fuels Nuclear Isomers (nonfissioning) Aerojet Corp Test Rig LANTR hot fire test (25:1 area ratio) Advanced Fission Systems Antimatter 5–42880b

  19. Simulated ReactorSystem Demonstrations • SAFE-100a Simulation • Prototypical reactor power level. • Vacuum environment. • Insulated core, HX, HP condensers. • Checkout testing ongoing. • Goal is to demonstrate operation of integrated system. SAFE-100a (uninsulated) Automated Test Facility Operations 5–42880b

  20. Pulsed Gas Core ReactorNon-nuclear Test • This schematic of the conceptual design for the PMI-FPS represents the most fully formed concept to date, incorporating all three prior aspects of: • Shockwave generation, shock collision and fission energy release, and magnetic flux compression power generation. • In addition to a new fourth component, a radial compaction of plasma by theta-pinch. INSPPI, Univ. Fla. 5–42880b

  21. Fusion Propulsion 5–42880b

  22. Human Outer Planet Exploration Revolutionary Aerospace Systems Concepts 5–42880b

  23. Antimatter • Annihilation with matter yields187 MJ/microgram. • Compare with combustion, H2/O2at 10 MJ/kilogram. • Penning traps can store > 1014 antiprotons. • Propulsion concepts use antimatter to trigger microfission or fusion. • Example concept is an antimatter sail. 5–42880b

  24. Other Concepts Solar Thermionic http://www.inspacepropulsion.com/tech/aerocapture.htmlAerocapture Myrabo, RPI Microwave Beamed Energy Propulsion www.inspacepropulsion.com/tech/tethers.html MXER Tether http://www.grc.nasa.gov/WWW/bpp/ Emerging Physics 5–42880b

  25. Concluding Comments • Human missions beyond Mars will require propulsion technologies beyond those currently being developed. • Chemical—Specific Energy > 10 MJ/kg. • Nuclear—Specific Power > 10 KW/kg. • Many old concepts that were immature may now be ready for another look. • Research is slow business, but not expensive. • Avenues exist. 5–42880b

  26. Back-up Charts 5–42880b

  27. Reusable Single Stage to Orbit • NOT YET! • SSTO is currently not quite achievable, limited by: • Fuel specific energy. • Mass of wheels, wings, tanks, and engines. • Reusable vehicles are not cost-effective until flight rates> 25 flights/year. • What We Like to Have • Ultimately, frequent flights of an SSTO vehicle are desired. • Reduced fuel fraction enables: • More payload. • Added safety features. • Added operability features. • What is needed • High specific energy fuels (>10 MJ/kg). • Off-board energy, launch assist. • Stages. 5–42880b

  28. Mag-Beam Concept John Carscadden, University of Washington. • A space-based station generates a stream of magnetized ions. • The ions interact with a magnetic sail on a spacecraft to provide propulsion. • NASA Institute for Advanced Concepts Phase I $75,000 contract for a six-month study to validate the concept and identify challenges. 5–42880b

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