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Electric Propulsion for Future Space Missions Part I. Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field. Introduction. Why electric propulsion? Types Applications Some history Future missions and vehicles A very cool future.
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Electric Propulsion for Future Space MissionsPart I Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field
Introduction • Why electric propulsion? • Types • Applications • Some history • Future missions and vehicles • A very cool future
Electric PropulsionHistorical 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
Electric PropulsionHistorical 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.
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 The First Electric Thruster
Types Of Electric Thrusters • Electrostatic • Ion • Hall • Electrothermal • Arcjet • Resistojet • Electromagnetic • Magneto plasma dynamic (MPD) • Many others
Hall Thruster Thrusters designed and fabricated by the Design Bureau Fakel, Kaliningrad (Baltic Region), Russia, and offered by International Space Technology, Inc. SPT-100 1350 W 1600 lbf-s/lbm (Nominal) SPT-140 4000 W 1700 lbf-s/lbm (Nominal) SPT-70 700 W 1450 lbf-s/lbm (Nominal) SPT-50 300 W 1200 lbf-s/lbm (Nominal)
Anode Magnet Coils Xe Dielectric Walls Ez Br Cathode Xe Power Supply Power Supply Hall Thruster
Hydrazine Arcjet Primex Aerospace Hydrazine Arcjet: 1.8 kW, 200 mN, 500 lbf-s/lbm
PROPELLANT IN THRUSTER EXHAUST CATHODE ANODE CURRENT ARC Arcjet Thruster
Arcjet Thruster Ship Set of Four Olin Aerospace 500 lbf-s/lbm Hydrazine Arcjets and Power Processing Unit
Pulsed MPD Thruster Operating on Argon Propellant at Princeton University Magneto Plasma Dynamic (MPD) Thruster
NASA Glenn Electric Propulsion 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.
NASA Glenn Electric Propulsion 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.
Launch of Deep Space 1 • Boeing Delta II (7326) Rocket • October 24, 1998
