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Ion propulsion 1.ppt
- 1. Electric Propulsion forFuture Space Missions Part I Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field
- 2. Introduction • Why electricpropulsion? – Types – Applications • Some history • Future missions and vehicles • A very cool future
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- 4. Why High ExhaustVelocity Is Important
- 5. Chemical & ElectricPropulsion Have Intrinsic Differences
- 6. Solar and NuclearElectric Propulsion Subsystems Power Conditioning Solar Cells Thrust Electric Thruster Propellant Exhaust Sun Thermal-to- Electric Power Conversion Nuclear Reactor
- 7. Electric Propulsion Historical Overview 1903 -- K. E. Tsiolkovsky derived the “Tsiolkovsky” or “Rocket” Equation commonly used to show the benefits of electric propulsion 1906 -- R. Goddard wrote about the possibility of electric rockets 1911 -- K. E. Tsiolkovsky independently wrote about electric rockets 1929 -- World’s first electric thruster demonstrated by V. P. Glushko at the Gas Dynamics Laboratory in Lenningrad 1960 -- First “broad-beam” ion thruster operated in the U.S. at the NASA Lewis (now Glenn) Research Center
- 8. Electric Propulsion Historical Overview 1964 -- First successful sub-orbital demonstration of an ion engine (SERT I) by the U.S. 1964 -- First use of an electric thruster on an interplanetary probe (Zond 2) by the USSR 1970 -- Long duration test of mercury ion thrusters in space (SERT II) by the U.S. 1972 -- First operation of a xenon stationary plasma thruster (SPT-50) in space (Meteor) by the USSR 1993 -- First use of hydrazine arcjets on a commercial communications satellite (Telstar 401) by the U.S.
- 9. The First ElectricThruster • Developed by V. P Glushko at the Gas Dynamics Laboratory in Lenningrad, 1929 - 1933 • Solid and Liquid Conductors Were Vaporized by High Current Discharges in the Plenum Chamber and Expanded Through the Nozzle • Power Provided by 40 kV, 4 mF Capacitors
- 10. Types Of ElectricThrusters • Electrostatic – Ion – Hall • Electrothermal – Arcjet – Resistojet • Electromagnetic – Magneto plasma dynamic (MPD) – Many others
- 11. Types Of ElectricThrusters THRUSTER POWER RANGE SPECIFIC IMPULSE (s) Electrothermal 100s of watts 300 to 400 Resistojets Arcjets Hydrazine kilowatts 500 to 600 Hydrogen 10s of kilowatts 900 to 1200 Ammonia kilowatts to 10s of kilowatts 600 to 800 Electrostatic Gridded Ion Engines watts to 100 kilowatts 2000 to 10,000 Stationary Plasma Thrusters (SPT) 100s of watts to 10’s of kilowatts 1000 to 2500 Thruster with Anode Layer (TAL) 100s of watts to 10’s of kilowatts 1000 to 4000 Electromagnetic Magnetoplasmadynamic (MPD) Pulsed kilowatts (average) 1000 to 4000 Steady-State 100s of kilowatts to megawatts 3000 to 7000 Pulsed Plasma Thruster 10s to 100s of watts (average) 1000 to 1500 Pulsed Inductive Thruster 10s of kilowatts 3000 to 5000 Electron Cyclotron Thruster kilowatts to 10s of kilowatts 2000 to 4000 Many Others
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- 15. Hall Thruster SPT-100 1350 W 1600lbf-s/lbm (Nominal) SPT-70 700 W 1450 lbf-s/lbm (Nominal) SPT-140 4000 W 1700 lbf-s/lbm (Nominal) SPT-50 300 W 1200 lbf-s/lbm (Nominal) Thrusters designed and fabricated by the Design Bureau Fakel, Kaliningrad (Baltic Region), Russia, and offered by International Space Technology, Inc.
- 16. Hall Thruster Magnet Coils DielectricWalls Cathode Power Supply Power Supply Xe Xe Anode Ez Br
- 17. Hydrazine Arcjet Primex AerospaceHydrazine Arcjet: 1.8 kW, 200 mN, 500 lbf-s/lbm
- 18. Arcjet Thruster CATHODE ANODE CURRENT ARC PROPELLANTIN THRUSTER EXHAUST
- 19. Arcjet Thruster Ship Setof Four Olin Aerospace 500 lbf-s/lbm Hydrazine Arcjets and Power Processing Unit
- 20. Magneto Plasma Dynamic(MPD) Thruster Pulsed MPD Thruster Operating on Argon Propellant at Princeton University
- 21. Magneto Plasma Dynamic(MPD) Thruster
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- 25. NASA Glenn ElectricPropulsion Laboratory (EPL)
- 26. NASA Glenn ElectricPropulsion Laboratory (EPL) Contributions • On September 23, 2001, the Deep Space 1 ion thruster set a record of 16,000 hrs. of operation while propelling the spacecraft on its encounter with Comet Borrelly. • In preparation of MErcury Surface, Space ENvironment, GEochemistry and Ranging (MESSENGER) probe mission, VF-6 was used to characterize components under a 10-sun solar insolation environment. • On December 3, 2000, hollow cathodes, which were developed at GRC and tested in VF-5 as part of the Plasma Contactor Unit, began protecting the International Space Station from harmful space plasma voltage potentials.
- 27. NASA Glenn ElectricPropulsion Laboratory (EPL) Contributions • A refractive secondary concentrator (RSC) achieved temperatures of 1455 Kelvin with an 87% throughput in VF-6. • On January 4, 2002, a pulsed plasma thruster on Earth Observing 1 demonstrated a highly fuel efficient method of controlling spacecraft attitude and "pointability." • Conducted first integrated solar dynamic system test from solar input to electrical power in VF-6.
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- 32. Neptune and IonThruster
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- 35. Deep Space 1Thruster / Spacecraft Compatibility Testing
- 36. Deep Space 1Thruster
- 37. • Launch ofDeep Space 1 • Boeing Delta II (7326) Rocket • October 24, 1998
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