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Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781721197576 Category : Languages : en Pages : 30
Book Description
Solar Electric Propulsion (SEP) when used for station keeping and final orbit insertion has been shown to increase a geostationary satellite's payload when launched by existing expendable launch vehicles. In the case of reusable launch vehicles or expendable launch vehicles where an upper stage is an expensive option, this methodology can be modified by using the existing on-board apogee chemical system to perform a perigee burn and then letting the electric propulsion system complete the transfer to geostationary orbit. The elimination of upper stages using on-board chemical and electric propulsion systems was thus examined for GEO spacecraft. Launch vehicle step-down from an Atlas IIAR to a Delta 7920 (no upper stage) was achieved using expanded on-board chemical tanks, 40 kW payload power for electric propulsion, and a 60 day elliptical to GEO SEP orbit insertion. Optimal combined chemical and electric trajectories were found using SEPSPOT. While Hall and ion thrusters provided launch vehicle step-down and even more payload for longer insertion times, NH3 arcjets had insufficient performance to allow launch vehicle step-down. Degradation levels were only 5% to 7% for launch step-down cases using advanced solar arrays. Results were parameterized to allow comparisons for future reusable launch vehicles. Results showed that for an 8 W/kg initial power/launch mass power density spacecraft, 50% to 100% more payload can be launched using this method. Oleson, Steven Glenn Research Center NASA/TM-1999-209646, NAS 1.15:209646, IEPC-99-185, E-11994
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781721197576 Category : Languages : en Pages : 30
Book Description
Solar Electric Propulsion (SEP) when used for station keeping and final orbit insertion has been shown to increase a geostationary satellite's payload when launched by existing expendable launch vehicles. In the case of reusable launch vehicles or expendable launch vehicles where an upper stage is an expensive option, this methodology can be modified by using the existing on-board apogee chemical system to perform a perigee burn and then letting the electric propulsion system complete the transfer to geostationary orbit. The elimination of upper stages using on-board chemical and electric propulsion systems was thus examined for GEO spacecraft. Launch vehicle step-down from an Atlas IIAR to a Delta 7920 (no upper stage) was achieved using expanded on-board chemical tanks, 40 kW payload power for electric propulsion, and a 60 day elliptical to GEO SEP orbit insertion. Optimal combined chemical and electric trajectories were found using SEPSPOT. While Hall and ion thrusters provided launch vehicle step-down and even more payload for longer insertion times, NH3 arcjets had insufficient performance to allow launch vehicle step-down. Degradation levels were only 5% to 7% for launch step-down cases using advanced solar arrays. Results were parameterized to allow comparisons for future reusable launch vehicles. Results showed that for an 8 W/kg initial power/launch mass power density spacecraft, 50% to 100% more payload can be launched using this method. Oleson, Steven Glenn Research Center NASA/TM-1999-209646, NAS 1.15:209646, IEPC-99-185, E-11994
Author: National Aeronautics and Space Administration (NASA) Publisher: Createspace Independent Publishing Platform ISBN: 9781721193042 Category : Languages : en Pages : 30
Book Description
The sun tower concept of collecting solar energy in space and beaming it down for commercial use will require very affordable in-space as well as earth-to-orbit transportation. Advanced electric propulsion using a 200 kW power and propulsion system added to the sun tower nodes can provide a factor of two reduction in the required number of launch vehicles when compared to in-space cryogenic chemical systems. In addition, the total time required to launch and deliver the complete sun tower system is of the same order of magnitude using high power electric propulsion or cryogenic chemical propulsion: around one year. Advanced electric propulsion can also be used to minimize the stationkeeping propulsion system mass for this unique space platform. 50 to 100 kW class Hall, ion, magnetoplasmadynamic, and pulsed inductive thrusters are compared. High power Hall thruster technology provides the best mix of launches saved and shortest ground to Geosynchronous Earth Orbital Environment (GEO) delivery time of all the systems, including chemical. More detailed studies comparing launch vehicle costs, transfer operations costs, and propulsion system costs and complexities must be made to down-select a technology. The concept of adding electric propulsion to the sun tower nodes was compared to a concept using re-useable electric propulsion tugs for Low Earth Orbital Environment (LEO) to GEO transfer. While the tug concept would reduce the total number of required propulsion systems, more launchers and notably longer LEO to GEO and complete sun tower ground to GEO times would be required. The tugs would also need more complex, longer life propulsion systems and the ability to dock with sun tower nodes. Oleson, Steve Glenn Research Center NASA/TM-1999-209307, E-11833, NAS 1.15:209307, AIAA Paper 99-2872
Author: Frede Blaabjerg Publisher: Academic Press ISBN: 012816168X Category : Technology & Engineering Languages : en Pages : 532
Book Description
Control of Power Electronic Converters, Volume Two gives the theory behind power electronic converter control and discusses the operation, modelling and control of basic converters. The main components of power electronics systems that produce a desired effect (energy conversion, robot motion, etc.) by controlling system variables (voltages and currents) are thoroughly covered. Both small (mobile phones, computer power supplies) and very large systems (trains, wind turbines, high voltage power lines) and their power ranges, from the Watt to the Gigawatt, are presented and explored. Users will find a focused resource on how to apply innovative control techniques for power converters and drives. Discusses different applications and their control Explains the most important controller design methods, both in analog and digital Describes different, but important, applications that can be used in future industrial products Covers voltage source converters in significant detail Demonstrates applications across a much broader context
Author: William C. Strack Publisher: ISBN: Category : Electric propulsion Languages : en Pages : 28
Book Description
Current technology for solar-electric propulsion is used to assess the potential performance advantages of low-thrust propulsion for an out-of-the-ecliptic mission. Simple normal-to-the-orbit thrust steering is assumed with coast subarcs permitted. The electric spacecraft is launched onto an Earth escape trajectory by an Atlas (SLV3C)-Centaur or a Titan IIIC. Comparisons with a similarly launched uprated Burner II stage reveal that significant performance gains are possible using the electric stage with 250- to 475-day flight times.
Author: Fouad Sabry Publisher: One Billion Knowledgeable ISBN: Category : Technology & Engineering Languages : en Pages : 485
Book Description
What Is Plasma Propulsion A SpaceX Starship powered by chemical methylox engines will take up to six months to reach Mars. On Earth, radiation exposure is less than 2.5 milliseiverts per year. On their approach to Mars, colonists will face levels 300 times higher than that. Can we use superconducting advanced plasma propulsion technologies to cut the time down to 30 days? Neutron Star Systems has developed an improved magnetoplasmadynamic thruster system that uses rare earth barium copper oxide high temperature superconducting electromagnets to significantly improve plasma propulsion performance while consuming less electricity. This could be the way of the future for spaceflight propulsion. Technically, there are two types of propulsion systems namely chemical and electric depending on the sources of the fuel. Electrostatic thrusters are used for launching small satellites in low earth orbit which are capable to provide thrust for long time intervals. These thrusters consume less fuel compared to chemical propulsion systems. Therefore for the cost reduction interests, space scientists are interested to develop thrusters based on electric propulsion technology. Can SpaceX use Advanced Plasma Propulsion for Starship? How You Will Benefit (I) Insights, and validations about the following topics: Chapter 1: Plasma Propulsion Engine Chapter 2: Spaceflight Chapter 3: Wingless Electromagnetic Air Vehicle Chapter 4: Electrically Powered Spacecraft Propulsion Chapter 5: Ion thruster Chapter 6: Stellarator Chapter 7: Electric sail Chapter 8: MagBeam Chapter 9: Spacecraft propulsion Chapter 10: Advanced Electric Propulsion System Chapter 11: Anti-gravity Chapter 12: Artificial gravity (II) Answering the public top questions about plasma propulsion. (III) Real world examples for the usage of plasma propulsion in many fields. (IV) 17 appendices to explain, briefly, 266 emerging technology in each industry to have 360-degree full understanding of plasma propulsion' technologies. Who This Book Is For Professionals, undergraduate and graduate students, enthusiasts, hobbyists, and those who want to go beyond basic knowledge or information for any kind of plasma propulsion.
Author: National Aeronautics and Space Administration (NASA)
Author: National Aeronautics and Space Administration (NASA)
Author: Steven Robert Oleson
Author: National Aeronautics and Space Administration (NASA)
Author: 
Author: Frede Blaabjerg
Author: William C. Strack
Author: 
Author: Jesse Allen Linnell
Author: Jet Propulsion Laboratory (U.S.)
Author: Fouad Sabry