DESIGN, FABRICATION, AND TESTING OF A CESIUM ION ROCKET ENGINE.
Design, fabrication, and testing of a cesium ion rocket engine
ION ENGINE↗
SEARCH · Engineering Papers
Results for “Ion Propulsion”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Control and Guidance of Electrically Propelled Spacecraft
Some of the conditions and methods of control and guidance for a nuclear-electric spacecraft are discussed in general terms. The type of spacecraft considered is propelled by an ion motor. The broad aspects of the flight trajectory peculiar to this type of propulsion are examined. Some equipment limitations are reviewed.
NUCLEAR-ELECTRIC PROPULSION↗
Environmental effects on laboratory and in- flight performance of neutralization systems.
Environmental effects influencing experiments with ion thrust beams in small and large chambers and space flight test
ION BEAM↗
Power processing requirements for solar electric propulsion.
The successful integration of a light-weight, high-efficiency power conditioning (PC) unit with an electron bombardment ion thruster using a hollow cathode at JPL has been reported recently. This paper summarizes the presently conceived requirements by which the next generation of PCs should be judged and evaluated. The requirements are formulated in terms of a deep space mission, which implies that the characteristics of the solar source will vary in terms of output power and output voltage. The requirements identified by practical experience during long-term evaluation between 1968-1970 are described and explained.
Macie, T. W.↗
Performance capabilities of the 8-cm Mercury ion thruster
The paper presents an initial characterization of the performance capabilities and constraints of the 8-cm Hg ion thruster system with a view to evaluating its application to large space system propulsion requirements. With minor thruster modifications, the thrust was increased by about a factor of four, while the discharge voltage was reduced from 39 to 22 volts. The thruster was operated over a range of specific impulse of 1950 to 3040 seconds, and a maximum total efficiency of about 54% was attained at a discharge voltage of 24 volts and thruster input power of 0.49 kW.
Mantenieks, M. A.↗
Advanced electric propulsion and space plasma contactor research
A series of experiments performed on an 8 cm dia. ring cusp magnetic field ion thruster are described. The results show the effects of anode and cathode position and size, ring cusp axial location and discharge chamber length on plasma ion energy cost and extracted ion fraction. Thruster performance is shown to be improved substantially when optimum values of these parameters are used. Investigations into the basic plasma phenomena associated with the process of plasma contacting are described. The results show the process of electron collection from a background plasma to a hollow cathode plasma contactor exhibits a higher impedance than the process of electron emission from the hollow cathode. The importance of having cold ions present to facilitate the plasma contacting process is shown. Results of experiments into the behavior of hollow cathodes operating at high interelectrode pressures (up to approx. 100 Torr) on nitrogen and ammonia are presented. They suggest that diffuse emission from the insert of a hollow cathode can be sustained at high interelectrode pressures if the cathode is made of non-conducting material and the cathode internal pressure is reduced by evacuating the cathode interior. A theoretical model of discharge chamber operation developed for inert gas thrusters is extended so it can be used to evaluste the performance of mercury ion thrusters. Predictions of the model are compared to experimental results obtained on two 30 cm dia. thrusters.
Wilbur, P. J.↗
Lunar Get-Away-Special - Exploring the moon with a miniature electrically propelled spacecraft
A spacecraft and mission concept designed to carry out a search for water at the lunar poles is described. The main elements of the concept are solar-electric propulsion, a miniature spacecraft, and a highly focused scientific mission. The major challenges to the spacecraft design were the mass and volume limits of the GAS canister, the incorporation of solar electric propulsion, and the high radiation exposure in the Van Allen belt. The capability of ion drive in carrying out high-performance missions is demonstrated.
Salazar, R. P.↗
High-Power Hall Thruster Technology Evaluated for Primary Propulsion Applications
High-power electric propulsion systems have been shown to be enabling for a number of NASA concepts, including piloted missions to Mars and Earth-orbiting solar electric power generation for terrestrial use (refs. 1 and 2). These types of missions require moderate transfer times and sizable thrust levels, resulting in an optimized propulsion system with greater specific impulse than conventional chemical systems and greater thrust than ion thruster systems. Hall thruster technology will offer a favorable combination of performance, reliability, and lifetime for such applications if input power can be scaled by more than an order of magnitude from the kilowatt level of the current state-of-the-art systems. As a result, the NASA Glenn Research Center conducted strategic technology research and development into high-power Hall thruster technology. During program year 2002, an in-house fabricated thruster, designated the NASA-457M, was experimentally evaluated at input powers up to 72 kW. These tests demonstrated the efficacy of scaling Hall thrusters to high power suitable for a range of future missions. Thrust up to nearly 3 N was measured. Discharge specific impulses ranged from 1750 to 3250 sec, with discharge efficiencies between 46 and 65 percent. This thruster is the highest power, highest thrust Hall thruster ever tested.
Manzella, David H.↗
Annular Ion Engine: Evolutionary Approach to Achieve Revolutionary Capabilities
The Annular Ion Engine concept represents an evolutionary development in gridded ion thruster technology with the potential for delivering revolutionary capabilities.
ion thrusters↗
Electric Vehicle Lithium-Ion Battery Life Cycle Management
There is no question that electric vehicles (EVs), which are key for addressing climate change impacts from the transportation sector, are quickly gaining popularity and availability. With limits and other challenges related to the supply of critical battery minerals, maximizing the use of EV batteries and ensuring recovery of battery minerals is imperative. Therefore, proper end-of-life-cycle management (reuse and recycling) of these batteries must be part of the EV ecosystem from the perspective of both the supply chain and environmental footprint. Second use of batteries for energy storage systems extends the initial life of these resources and provides a buffer until economical material recovery facilities are in place. Although there are multiple pathways to recycling and recovery of materials, new recovery technologies are moving toward commercially available hydrometallurgy and promising direct recycling, which analysis has shown has the lowest overall carbon footprint. Strategically locating these plants close to battery collection further reduces transportation and thus recycling and recovering costs. Proper life cycle management could alleviate future lithium-ion battery materials supply chains for EVs. Governments and other stakeholders around the world have started initiatives and proposed regulations to address the challenges associated with life cycle management of EV lithium batteries. Finally, as manufacturers are increasingly faced with the likelihood of such extensive regulatory requirements, attention should be given to new designs, sales, and service models that can reduce life cycle management costs.
25 ENERGY STORAGE↗
Stacking Multiple Ion Captures in The High Performance Antiproton Trap (HiPAT)
The High performance Antiproton Trap (HiPAT) research project was initiated by the Marshall Space Flight Center's propulsion Research Center to examining the fundamental behavior of low energy antiprotons. Stored antiproton would ultimately be used for experimental demonstration of basic propulsive concepts. Matter-antimatter annihilation produces approximately 10(exp 8) MJ/g nearly 10 orders of magnitude more energy per unit mass than chemical based combustion, hence NASA's interest. To achieve containment, HiPAT utilizes a type of electromagnetic bottle know as a Penning trap positioned within an ultrahigh vacuum test section. Recently, the HiPAT hardware configuration has been enhanced to facilitate the capture of multiple normal matter ion burst. This endeavor is often referred to as "stacking" and used to increasing the number of captured particles. A prior normal matter experimental effort, successfully demonstrated the effectiveness of single burst capture. The stacking process is accomplished by manipulating the electric field generated by the confinement electrodes i.e. adjusting the well potential depth. These potential well values are initially configured to maximize the quantity of captured ions per burst; shallow wells with a depth of 100 volt or less (referenced to the incoming ion beam energy) are typically selected. Once captured, a cooling interval is required to reduce the energy of trapped particles below the lower extent of the "trap door" (or leading electrode) ion emitting potential. This is necessary such that a new burst of hot ions can be introduced while preventing those already inside from escaping. The cooling time is driven by a combination of mechanisms such as synchrotron radiation, background gas scattering, and resistive damping in a time scale on the order of minutes. A potential for reducing this hold period is to actively manipulate the electric field shape, using the power supply control system, to produce a deeper potential well. The trapped ions ride down the morphing well to a lower potential energy, leaving margin to once again cycle the "trap door" capturing a new burst while limiting the number of escaping ions. By adjusting the magnitude and timing of the potential well shaping, subsequent shots from the ion beam can be captured on a time scale shorter then that dictated by the standard inject, capture and cool technique. Currently, experimental tests are under way examining the functionally of this system for stacking multiple ions bursts within the HiPAT system.
Martin, James J.↗
PEGASUS: A multi-megawatt nuclear electric propulsion system
A propulsion system (PEGASUS) consisting of an electric thruster driven by a multimegawatt nuclear power system is proposed for a manned Mars mission. Magnetoplasmadynamic and mercury-ion thrusters are considered, based on a mission profile containing a 510-day burn time (for a mission time of approximately 1000 days). Both thrusters are capable of meeting the mission parameters. Electric propulsion systems have significant advantages over chemical systems, because of high specific impulse, lower propellant requirements, and lower system mass. The power for the PEGASUS system is supplied by a boiling liquid-metal fast reactor. The power system consists of the reactor, reactor shielding, power conditioning subsystems, and heat rejection subsystems. It is capable of providing a maximum of 8.5 megawatts of electrical power of which 6 megawatts is needed for the thruster system, leaving 1.5 megawatts available for inflight mission applications.
Coomes, Edmund P.↗
Ion thrusters and LFAs for outer planet exploration
Given the recent advancements in power generation, waste heat rejection systems and electric propulsion, a reassessment of the benefits of Nuclear Electric Propulsion (NEP) is provided.
advanced electric propulsion mission studies↗
Electric propulsion and its applications to space missions
Consideration is given the NASA, Air Force and European electric propulsion programs, the characteristics of primary electric propulsion systems, nuclear electric orbit transfer vehicles, and such topics in the fundamental processes of electrostatic thrusters as sputtering in mercury ion thrusters, the screen hole plasma sheath of an ion accelerator system, and the modelling of ion beam neutralization and nitrogen chemisorption. Also considered are electrostatic thruster components and systems, electromagnetic thrusters such as MPD and RIT systems, electric rail guns and mass drivers, power sources which include solar and nuclear alternatives, power conversion systems and their cooling apparatus, and the environmental interactions between spacecraft and their electric propulsion systems.
Finke, R. C.↗
Effect of thrustor arcing on ion rocket system design
Electrode arcing effects on ion rocket thrustor system design
THRUSTOR↗
Electronic propulsion systems for long-term space station operations
Attitude and orbit control electric propulsion systems for long term space stations, discussing resistojets and electron bombardment and contact ionization ion thrustors
Stuhlinger, E.↗
Solar cell modules for plasma interaction evaluation
A plasma interaction analysis in support of the solar electric propulsion subsystem examined the effects of a large high voltage solar array interacting with an ion thruster produced plasma. Two solar array test modules consisting of 36 large area wraparound contact solar cells welded to a flexible Kapton integrated circuit substrate were abricated. The modules contained certain features of the effects of insulation, din-holes, and bonding of the cell to the substrate and a ground plane. The possibility of a significant power loss occurring due to the collection of charged particles on the solar array interconnects was the focus of the research.
Source record↗
Hollow cathode startup using a microplasma discharge
Attention is given to a microplasma discharge to initiate a hollow cathode discharge for such applications as plasma flow experiments, the electric propulsion of space vehicles, and as a replacement for filament cathodes in neutral beam injector ion sources. The technique results in a cathode that is easy to start, simple in design, and which does not require external RF exciters, inserts or heating elements. Future applications may include ion beam milling and ion implantation.
Aston, G.↗