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Electric Propulsion for Future Space Missions Part I Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field.

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Presentation on theme: "Electric Propulsion for Future Space Missions Part I Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field."— Presentation transcript:

1 Electric Propulsion for Future Space Missions Part I Bryan Palaszewski Digital Learning Network NASA Glenn Research Center at Lewis Field

2 Introduction Why electric propulsion? –Types –Applications Some history Future missions and vehicles A very cool future

3 Solar Electric Propulsion Module

4 Why High Exhaust Velocity Is Important

5 Chemical & Electric Propulsion Have Intrinsic Differences

6 Solar and Nuclear Electric Propulsion Subsystems

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 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

10 Types Of Electric Thrusters Electrostatic –Ion –Hall Electrothermal –Arcjet –Resistojet Electromagnetic –Magneto plasma dynamic (MPD) –Many others

11 Types Of Electric Thrusters

12 Ion Thruster

13

14 Ion Thruster Layout

15 Hall Thruster SPT-100 1350 W 1600 lb f -s/lb m (Nominal) SPT-70 700 W 1450 lb f -s/lb m (Nominal) SPT-140 4000 W 1700 lb f -s/lb m (Nominal) SPT-50 300 W 1200 lb f -s/lb m (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 Dielectric Walls Cathode Power Supply Xe Anode EzEz BrBr

17 Hydrazine Arcjet Primex Aerospace Hydrazine Arcjet: 1.8 kW, 200 mN, 500 lb f -s/lb m

18 Arcjet Thruster CATHODE ANODE CURRENT ARC PROPELLANT IN THRUSTER EXHAUST

19 Arcjet Thruster Ship Set of Four Olin Aerospace 500 lb f -s/lb m 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

22 Pulsed Plasma Thruster

23

24

25 NASA Glenn Electric Propulsion Laboratory (EPL)

26 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.

27 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.

28 Jupiter

29 Saturn

30 Uranus

31 Neptune

32 Neptune and Ion Thruster

33 Pluto

34 Deep Space 1

35 Deep Space 1 Thruster / Spacecraft Compatibility Testing

36 Deep Space 1 Thruster

37 Launch of Deep Space 1 Boeing Delta II (7326) Rocket October 24, 1998

38 DS-1 Trajectory

39 Autonomous Navigation

40 Comet Borrelly

41


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