electric propulsion for future space missions
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Electric Propulsion for Future Space Missions
Part I
Bryan PalaszewskiDigital 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
Solar Electric Propulsion Module
Why High Exhaust VelocityIs Important
Ve Vs/cCHEMICAL PROPULSION
ELECTRIC PROPULSIONROCKET EQUATION
Mfinal
Minitial= EXP
– ²V s/c
Ve
Isp =Ve
gc
PayloadPropellant
Power Supply
PayloadPropellant
Chemical
Electric
Energy Limited
Power Limited
Propellant Velocity
Total Impulse
Thrust
Time
Chemical
Chemical
Electric
Electric
Chemical & Electric Propulsion Have Intrinsic Differences
Solar and Nuclear Electric Propulsion Subsystems
Power Conditioning
Solar Cells
ThrustElectric Thruster
PropellantExhaust
Sun
Thermal-to-Electric Power
Conversion
Nuclear Reactor
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.
The First Electric Thruster• 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
Types Of Electric Thrusters• Electrostatic
– Ion– Hall
• Electrothermal– Arcjet– Resistojet
• Electromagnetic– Magneto plasma dynamic (MPD)– Many others
Types Of Electric Thrusters
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 800Electrostatic 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 4000Electromagnetic 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
Ion Thruster
Ion Thruster
POSITIVE GRID (AT 1070 V)
NEGATIVE GRID (AT -200 V)
ANODE (AT +1100 V)PROPELLANT FEED
NEUTRALIZER KEEPER (AT +5 V)
MAGNET RINGS - ELECTRONS ARE REMOVED FROM THE DISCHARGE CHAMBER AT THE MAGNETIC FIELD CUSPS
NEUTRALIZER CATHODE (AT -15 V)
KEEPER ELECTRODE (AT +1075 V)
PROPELLANT FEED
MAGNETIC FIELD LINES (USED TO IMPROVE IONIZATION EFFICIENCY)
HOLLOW CATHODE (AT +1070 V) EMITS ELECTRONS INTO THE DISCHARGE CHAMBER
PROPELLANT FEED
IONS ACCELERATED ELECTROSTATICALLY THROUGH A NET VOLTAGE OF 1100 V
PLASMA BRIDGE
ION BEAM (AT THE AMBIENT SPACE
PLASMA POTENTIAL) ( 0 V )
ELECTRONS EMITTED BY AN EXTERNAL CATHODE ARE INJECTED INTO THE ION BEAM FOR NEUTRALIZATION
PLASMA (AT +1100 V)
ION PRODUCTION VOLUME
ELECTRONS IMPACT ATOMS TO CREATE IONS
Ion Thruster Layout
Hall Thruster
SPT-1001350 W
1600 lbf-s/lbm (Nominal)
SPT-70700 W
1450 lbf-s/lbm (Nominal)
SPT-1404000 W
1700 lbf-s/lbm (Nominal)
SPT-50300 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.
Hall Thruster
Magnet Coils
Dielectric Walls
Cathode
Power SupplyPower Supply Xe
Xe
Anode
EzBr
Hydrazine Arcjet
Primex Aerospace Hydrazine Arcjet: 1.8 kW, 200 mN, 500 lbf-s/lbm
Arcjet Thruster
CATHODE
ANODE
CURRENT ARC
PROPELLANT IN
THRUSTER EXHAUST
Arcjet ThrusterShip Set of Four Olin Aerospace 500 lbf-s/lbm Hydrazine Arcjets
and Power Processing Unit
Magneto Plasma Dynamic (MPD) Thruster
Pulsed MPD Thruster Operating on Argon Propellant at Princeton University
Magneto Plasma Dynamic (MPD) Thruster
J x B Propellant
Insulator Backplate
B
J
Anode
Anode
Propellant
Cathode
Current Streamlines
Self-Induced Magnetic Field
PlasmaCL
Pulsed Plasma Thruster
Pulsed Plasma Thruster
Pulsed Plasma Thruster
NASA Glenn Electric Propulsion Laboratory (EPL)
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.
Jupiter
Saturn
Uranus
Neptune
Neptune and Ion Thruster
Pluto
Deep Space 1
Deep Space 1 Thruster / Spacecraft Compatibility Testing
Deep Space 1 Thruster
• Launch of Deep Space 1
• Boeing Delta II (7326) Rocket
• October 24, 1998
DS-1 Trajectory
Autonomous Navigation
Comet Borrelly
Comet Borrelly
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