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Author: Lewis Research Center
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 220
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Book Description
Author: Lewis Research Center
Publisher:
ISBN:
Category : Aeronautical instruments
Languages : en
Pages : 220
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Book Description
Author: Allen E. Fuhs (ed)
Publisher: MIT Press (MA)
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 576
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Book Description
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel. Symposium
Publisher: North Atlantic Treaty Organization Resear Rganization
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 554
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Book Description
Author: Dan M. Goebel
Publisher: John Wiley & Sons
ISBN: 0470436263
Category : Technology & Engineering
Languages : en
Pages : 528
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Book Description
Throughout most of the twentieth century, electric propulsion was considered the technology of the future. Now, the future has arrived. This important new book explains the fundamentals of electric propulsion for spacecraft and describes in detail the physics and characteristics of the two major electric thrusters in use today, ion and Hall thrusters. The authors provide an introduction to plasma physics in order to allow readers to understand the models and derivations used in determining electric thruster performance. They then go on to present detailed explanations of: Thruster principles Ion thruster plasma generators and accelerator grids Hollow cathodes Hall thrusters Ion and Hall thruster plumes Flight ion and Hall thrusters Based largely on research and development performed at the Jet Propulsion Laboratory (JPL) and complemented with scores of tables, figures, homework problems, and references, Fundamentals of Electric Propulsion: Ion and Hall Thrusters is an indispensable textbook for advanced undergraduate and graduate students who are preparing to enter the aerospace industry. It also serves as an equally valuable resource for professional engineers already at work in the field.
Author: Robert Gouland
Publisher:
ISBN: 9780122941504
Category :
Languages : en
Pages : 482
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 152
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Book Description
Author: Jesus Betancourt-Roque
Publisher:
ISBN:
Category : Automatic data collection systems
Languages : en
Pages :
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Book Description
Author: Robert C. Finke
Publisher:
ISBN:
Category : Space simulators
Languages : en
Pages : 44
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Book Description
A facility containing 15- and 25-foot-diameter space-environment tanks and support equipment is described. The facility is designed for testing ion and plasma thrustors, 10 sub -7 spacecraft, and related components at pressures in the 10 torr range. Total pumping capacity in the 10 sub -5 torr range for air has been measured at 250 000 liters per second and for hydrogen at 660 000 liters per second. The pumping systems and 28 000- square- foot liquid-nitrogen- cooled condenser are described. Data are presented on an auxiliary fast pumpdown tank that simulates ambient pressures encountered during a booster launch to 10 sub -6 torr range in approximately 2 minutes. Pertinent information concerning a spin test apparatus and thrustor installation method is also included. An electrical and instrumentation system is described consisting of 2 megawatts of 20-kilovolt direct- current power, a 2000-cable patch board network, a 600-channel thermocouple system, and a 400-channel digital data recorder. An annunciator system is provided to indicate status of operating equipment. Some aspects of safety are considered, including interlocking, personnel protection, and procedures.
Author: Jet Propulsion Laboratory (U.S.)
Publisher:
ISBN:
Category : Jet propulsion
Languages : en
Pages : 20
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722920128
Category :
Languages : en
Pages : 108
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Book Description
Results are presented which show that hollow cathodes can be operated on ammonia but that sustained operation in the high pressures where arcjet thrusters operate (of the order of 1000 Torr) is difficult to achieve. The concept of using contoured, fine wire meshes attached across the screen grid apertures in an ion thruster to effect control of the ion beam divergence is introduced. The concept is compared to conventional (free sheath) ion extraction and is shown to be potentially attractive. The performance related effects of changing the anode and cathode locations and of interchanging hollow cathode and refractory filament electron sources within an 8-cm diameter, argon, ring cusp ion thruster discharge chamber are examined. The effects induced in discharge chamber performance by changes in magnetic field strength and configuration and in propellant flow distribution are also measured. Results are presented in terms of changes in the parameters that describe the effectiveness of primary electron utilization and ion extraction into the beam. The apparatus and instrumentation used to study hollow cathode operation at high electron emission levels (of the order of 100 A) is described. Wilbur, Paul J. Unspecified Center ARC JET ENGINES; ELECTROSTATIC ENGINES; ION PROPULSION; RESEARCH MANAGEMENT; AMMONIA; ARGON; FILAMENTS; HOLLOW CATHODES; ION BEAMS; MAGNETIC FIELDS; OPTICS; REFRACTORY MATERIALS...
