183
183
May 6, 2010
05/10
by
Wells, W. H
texts
eye 183
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No Abstract Available
Topic: ION PROPULSION
216
216
Jun 17, 2010
06/10
by
Derfler, H
texts
eye 216
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No Abstract Available
Topics: ION PROPULSION, PLASMA PROPULSION
503
503
Jun 21, 2010
06/10
by
Carrega, F., et al
texts
eye 503
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Silastene coating for pollution reduction in hotshot wind tunnel simulating reentry conditions
Topics: ELECTRODES, ION ENGINES, ION PROPULSION, FOCUSING
285
285
Jun 27, 2010
06/10
by
Fesenkov, V. G
texts
eye 285
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No Abstract Available
Topics: COSMOS SATELLITES, ION PROPULSION, SCIENTIFIC SATELLITES, SPACECRAFT LAUNCHING, U.S.S.R.
273
273
Jun 18, 2010
06/10
by
Ducati, A. C.; Muehlberger, E.; Todd, J. P
texts
eye 273
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Propellants and thrust performance for thermoionic electric thrustor
Topics: ION PROPULSION, PROPELLANTS, THERMOELECTRICITY, THRUST, THRUSTORS, IONIC PROPULSION,...
Electric propulsion for micro- and nano-satellites is an increasingly viable solution for station keeping and end-of-life operations. In particular, microelectromechanical systems (MEMS) electrodes for use in a field ionization electric propulsion thruster are starting to show compelling evidence as a viable plasma generator electrode. This was determined by utilizing a bell jar pressure chamber and a proof-of-concept field ionization electrode characterization fixture complete with an...
Topics: carbon nanotubes, field emission, field ionization, electrostatic ion propulsion, cubesat
This thesis presents the implementation issues of an ion propulsion subsystem (IPS) on a geosynchronous communications satellite. As an example, Ultra High Frequency (UHF) Follow-On class satellite is selected for this study. The issues include: (1) impact of integration of IPS with other subsystems, such as the electrical power subsystem to take care of the heavy demand of power requirements and location of the subsystem with least impact on attitude control and plume impingement on solar...
Topics: Ion rockets, Geostationary satellites., Ion propulsion, geosynchronous satellite, North-South...
153
153
Jul 5, 2010
07/10
by
KADEN, H
texts
eye 153
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THE UNSTABLE VORTEX LAYER BEHIND A WING IS ANALYZED USING CONFORMAL MAPPING TECHNIQUES. A PLANE DISCONTINUITY MODEL IS DEVELOPED AND THE ROLLING-UP PROCESS OF THE SURFACE IS STUDIED. APPLICATIONS TO AIRFOIL WING THEORY ARE GIVEN. A CORRESPONDING FLOW VISUALIZATION EXPERIMENT IN A WATER TANK IS DESCRIBED.
Topics: ELECTRIC GENERATORS, ION PROPULSION, POWER SUPPLIES, CESIUM, ELECTRICAL PROPERTIES, IONIZATION,...
714
714
May 29, 2011
05/11
by
Gnoffo, Peter A
texts
eye 714
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A series of experiments to measure pressure and heating for code validation involving hypersonic, laminar, separated flows was conducted at the Calspan-University at Buffalo Research Center (CUBRC) in the Large Energy National Shock (LENS) tunnel. The experimental data serves as a focus for a code validation session but are not available to the authors until the conclusion of this session. The first set of experiments considered here involve Mach 9.5 and Mach 11.3 N, flow over a hollow...
Topics: ION ENGINES, ION PROPULSION, PLUMES, TECHNOLOGY UTILIZATION, EXPERIMENTATION, PLASMAS (PHYSICS),...
348
348
Jun 19, 2010
06/10
by
NON
texts
eye 348
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Transient and steady performance of ion rocket thrust augmentor
Topics: AUGMENTATION, ION PROPULSION, IONIZERS, ROCKET THRUST, THRUST AUGMENTATION, IONIC PROPULSION,...
0
0.0
Jan 16, 2021
01/21
by
michael chen (michaelchen0220)
data
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I have only modeled two parts which are not enough for an entire space freighter. To connect parts together, insert magnets into the cuboid holes and the parts should stick to each other.
Topics: ion propulsion, Physics & Astronomy, cargo, thingiverse, ion, space, interplanetary,...
250
250
Jun 12, 2011
06/11
by
Hollinger, Geoffrey A.; Briscoe, Jeri M
texts
eye 250
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Using the DarwinZk development software, a genetic algorithm (GA) was used to design and optimize a pipe-crawling robot for parameters such as mass, power consumption, and joint extension to further the research of the Miniature Inspection Systems Technology (MIST) team. In an attempt to improve on existing designs, a new robot was developed, the piezo robot. The final proposed design uses piezoelectric expansion actuators to move the robot with a 'chimneying' method employed by mountain...
Topics: ION PROPULSION, ROCKET ENGINES, POWER CONDITIONING, WEIGHT REDUCTION, BREADBOARD MODELS, SOLAR...
272
272
Jun 9, 2011
06/11
by
Beeler, Scott C
texts
eye 272
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The state-dependent Riccati equations (SDRE) is the basis of a technique for suboptimal feedback control of a nonlinear quadratic regulator (NQR) problem. It is an extension of the Riccati equation used for feedback control of linear problems, with the addition of nonlinearities in the state dynamics of the system resulting in a state-dependent gain matrix as the solution of the equation. In this paper several variations on the SDRE-based method will be considered for the feedback control...
Topics: ION ENGINES, ION PROPULSION, ION OPTICS, PLASMAS (PHYSICS), STEADY STATE, ALUMINUM OXIDES, HIGH...
286
286
Jun 9, 2011
06/11
by
Klein, Vladislav; Murphy, Patrick C.; Szyba, Nathan M
texts
eye 286
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Static and dynamic wind tunnel tests were performed on an 18 scale model of the F-16XL aircraft. These tests were performed over a wide range of angles of attack and sideslip with oscillation amplitudes from 5 deg. to 30 deg. and reduced frequencies from 0.073 to 0.269. Harmonic analysis was used to estimate Fourier coefficients and in-phase and out-of-phase components. For frequency dependent data from rolling oscillations, a two-step regression method was used to obtain unsteady models...
Topics: ION OPTICS, XENON, PROPULSION SYSTEM CONFIGURATIONS, PROPULSION SYSTEM PERFORMANCE, ION ENGINES,...
365
365
May 31, 2011
05/11
by
Pirzadeh, Shahyar Z.; Frink, Neal T
texts
eye 365
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An application of the NASA unstructured grid software system TetrUSS is presented for the prediction of aerodynamic drag on a transport configuration. The paper briefly describes the underlying methodology and summarizes the results obtained on the DLR-F4 transport configuration recently presented in the first AIAA computational fluid dynamics (CFD) Drag Prediction Workshop. TetrUSS is a suite of loosely coupled unstructured grid CFD codes developed at the NASA Langley Research Center. The...
Topics: ION ENGINES, ION OPTICS, ION PROPULSION, PERFORMANCE TESTS, ION EXTRACTION, MOLYBDENUM, SERVICE...
A program has been conducted in order to improve the performance characteristics of 30 cm thrusters. This program was divided into three distinct, but related tasks: (1) the discharge chamber and component design modifications proposed for inclusion in the engineering model thruster were evaluated and engineering specifications were verified; (2) thrust losses which result from the contributions of double charged ions and nonaxial ion trajectories to the ion beam current were measured and (3)...
Topics: NASA Technical Reports Server (NTRS), ION PROPULSION, ROCKET ENGINES, ELECTRIC ROCKET ENGINES,...
454
454
May 29, 2011
05/11
by
Watson, Ralph D.; Hall, Robert M.; Anders, John B
texts
eye 454
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This paper reviews flat plate skin friction data from early correlations of drag on plates in water to measurements in the cryogenic environment of The NASA Langley National Transonic Facility (NTF) in late 1996. The flat plate (zero pressure gradient with negligible surface curvature) incompressible skin friction at high Reynolds numbers is emphasized in this paper, due to its importance in assessing the accuracy of measurements, and as being important to the aerodynamics of large scale...
Topics: ION PROPULSION, SPACE RENDEZVOUS, SPACE MISSIONS, COMETS, PROBABILITY THEORY, AEROSPACE...
339
339
Jun 21, 2010
06/10
by
Berns, J. A.; Lacovic, R. F
texts
eye 339
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Capillary rise in annular region of concentric cylinders during coast periods of Atlas-Centaur flights
Topics: ION ENGINES, PLASMA PHYSICS, CESIUM ENGINES, ELECTRON BEAMS, ION PROPULSION, IONIZATION POTENTIALS,...
338
338
Jun 1, 2010
06/10
by
Lerin, C
texts
eye 338
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Electric network association with digital computers for electron trajectory determination applied to ionic propulsion
Topics: DIGITAL COMPUTERS, ELECTRIC NETWORKS, ELECTRON TRAJECTORIES, ION PROPULSION, DIGITAL COMPUTER,...
The Ion Beam Propulsion Study was a joint high-level study between the Applied Physics Laboratory operated by NASA and ASRC Aerospace at Kennedy Space Center, Florida, and Berkeley Scientific, Berkeley, California. The results were promising and suggested that work should continue if future funding becomes available. The application of ion thrusters for spacecraft propulsion is limited to quite modest ion sources with similarly modest ion beam parameters because of the mass penalty associated...
Topics: NASA Technical Reports Server (NTRS), ION BEAMS, ION PROPULSION, ION SOURCES, SAILS, IONS,...
A modified Hughes SIT-5 system is being tested for durability at the Lewis Research Center. As of October 1, 1972, the thruster subsystem has logged over 8000 hours of operation. The initial 2023 hours were run with a translating screen thrust vector grid. The thruster is currently operating with an electrostatic type vector grid. Profiles and maps taken at widely separated intervals show that performance and operating characteristics have remained essentially constant. Overall efficiency is...
Topics: NASA Technical Reports Server (NTRS), DURABILITY, ION PROPULSION, ATTITUDE CONTROL, MERCURY...
258
258
Jul 11, 2010
07/10
by
MINYUSHINA, L. S
texts
eye 258
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AN ANALYSIS OF THE SPATIAL AND TIME PROFILES OF THE ZONAL WIND FIELD AND CONTOUR CHARTS OF THE 10 MB AND 2 MB SURFACES IS PRESENTED. VARIABILITY OF THE PRESSURE FIELD IN THE QUASI-BIENNIAL CIRCULATION CYCLE IS COMPARED WITH THAT IN THE SEMIANNUAL CYCLE.
Topics: MISSION PLANNING, PROPULSION SYSTEM CONFIGURATIONS, SOLAR ELECTRIC PROPULSION, SPACE MISSIONS, ION...
242
242
Jul 26, 2010
07/10
by
Walker, Walter G.; Copp, Martin R
texts
eye 242
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comment 0
No Abstract Available
Topics: ELECTRON SOURCES, ION BEAMS, ION PROPULSION, ION SOURCES, ROCKET ENGINES, EQUATIONS OF MOTION,...
199
199
May 31, 2011
05/11
by
NON
texts
eye 199
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Automatic Picture Transmission (APT) was incorporated by NASA in the Tiros 8 weather satellite. APT included an advanced satellite camera that immediately transmitted a picture as well as low cost receiving equipment. When an advanced scanning radiometer was later introduced, ground station display equipment would not readily adjust to the new format until GSFC developed an APT Digital Scan Converter that made them compatible. A NASA Technical Note by Goddard's Vermillion and Kamoski described...
Topics: ION ENGINES, BEAM CURRENTS, ION OPTICS, PERFORMANCE TESTS, ION PROPULSION, EVALUATION, NEAR FIELDS,...
The technology status of 8 cm diameter electron bombardment ion thrusters is presented. Much of the technology resulting from the 5 cm diameter thruster has been adapted and improved upon to increase the reliability, durability, and efficiency of the 8 cm thruster. Technology discussed includes: dependence of neutralizer tip erosion upon neutralizer flow rate; impregnated and rolled-foil insert cathode performance and life testing; neutralizer position studies; thruster ion beam profile...
Topics: NASA Technical Reports Server (NTRS), ION ENGINES, ION PROPULSION, MERCURY (METAL), ELECTRON...
The NASA Solar Electric Propulsion Technology Application Readiness (NSTAR) program, managed by the Jet Propulsion Laboratory (JPL), is currently developing a high performance, simplified ion propulsion system. This propulsion system, which is throttleable from 0.5- to 2.3-kW output power to the thruster, targets primary propulsion applications for planetary and Earth-space missions and has been baselined as the primary propulsion system for the first New Millennium spacecraft. The NASA Lewis...
Topics: NASA Technical Reports Server (NTRS), ION PROPULSION, ROCKET ENGINES, POWER CONDITIONING, WEIGHT...
This report summarizes developments from November 2008. The original contract was aimed at the investigation of ion propulsion based on ionic liquids (ILs). The scope was widened with new funds ($35,000 and $50,000, received for 2008 and 2009, respectively) to study also colloidal propulsion (based on charged nanodrop beams rather than ion beams). This work would rely on electro sprays of mixtures of form-amide and propylene carbonate with selected ionic liquids. In our earlier report we...
Topics: DTIC Archive, de la Mora,Juan F, Yale University New Haven United States, ionic liquids, ION...
Inert gas ion thruster technology offers the greatest potential for providing high specific impulse, low thrust, electric propulsion on large, Earth orbital spacecraft. The development of a thruster module that can be operated on xenon or argon propellant to produce 0.2 N of thrust at a specific impulse of 3000 sec with xenon propellant and at 6000 sec with argon propellant is described. The 30 cm diameter, laboratory model thruster is considered to be scalable to produce 0.5 N thrust. A high...
Topics: NASA Technical Reports Server (NTRS), ARGON, ION PROPULSION, ROCKET PROPELLANTS, XENON, CATHODES,...
A two grid 30 cm diameter mercury ion thruster was operated with only six power supplies over the baseline J series thruster power throttle range with negligible impact on thruster performance. An analysis of the functional model power processor showed that the component mass and parts count could be reduced considerably and the electrical efficiency increased slightly by only replacing power supplies with relays. The input power, output thrust, and specific impulse of the thruster were then...
Topics: NASA Technical Reports Server (NTRS), ION PROPULSION, MERCURY (METAL), ROCKET ENGINES, THRUST,...
1,288
1.3K
Jun 21, 2010
06/10
by
NON
texts
eye 1,288
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Outer planetary mission planning and technological improvements for outer planet spacecraft
Topics: BAFFLES, ELECTRIC CONNECTORS, ELECTRIC PROPULSION, ELECTRON BOMBARDMENT, ELECTRIC ROCKET ENGINES,...
219
219
Jun 19, 2010
06/10
by
Surugue, J., et al
texts
eye 219
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Plasma accelerators, ion propulsion units, and electric propulsion systems
Topics: COLLOIDS, PLASMA ACCELERATOR, CONFERENCES, ELECTRIC PROPULSION, ION PROPULSION, PLASMA...
203
203
Jun 9, 2011
06/11
by
Samareh, Jamshid A
texts
eye 203
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The purpose of this paper is to discuss the use of Computer-Aided Design (CAD) geometry in a Multi-Disciplinary Design Optimization (MDO) environment. Two techniques are presented to facilitate the use of CAD geometry by different disciplines, such as Computational Fluid Dynamics (CFD) and Computational Structural Mechanics (CSM). One method is to transfer the load from a CFD grid to a CSM grid. The second method is to update the CAD geometry for CSM deflection.
Topics: DEEP SPACE 1 MISSION, ELECTRIC PROPULSION, HIGH TEMPERATURE, SOLAR ELECTRIC PROPULSION, MISSION...
"Kaufman thrusters," or electron bombardment thrusters, were developed for a spacecraft electric propulsion technique called ion propulsion. The technique, conceived by a Lewis Research Center engineer, is used by industry to etch microcircuits for electronic systems and deposition of thin films as coatings on gas atoms to create ions in a discharge chamber. The ions are ejected from the chamber as ion beams, then mixed with an equal number of electrons becoming a thrusting force....
Topics: NASA Technical Reports Server (NTRS), ION PROPULSION, GENERATORS, MICROELECTRONICS, ELECTRON...
A 30 cm diameter argon ion source was evaluated. Ion source beam currents up to 4a were extracted with ion energies ranging from 0.2 to 1.5 KeV. An ion optics scaling relation was developed for predicting ion beam extraction capability as a function of total extraction voltage, gas type, and screen grid open area. Ignition and emission characteristics of several hollow cathode geometries were assessed for purposes of defining discharge chamber and neutralizer cathodes. Also presented are ion...
Topics: NASA Technical Reports Server (NTRS), ARGON, ION PROPULSION, ION SOURCES, CATHODES, ION BEAMS,...
418
418
Jul 26, 2010
07/10
by
Graham, Robert W
texts
eye 418
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The possibility that life exists elsewhere in the universe, even in our own planetary system, has intrigued scientists, philosophers, and theologians for centuries. The spaceflight programs of NASA have provided much new information about our planetary neighbors and have put to rest some speculations about the existence of life on those planets or their satellites. However, there are still undetermined questions about the possibility of some form of life existing in the far distant past in our...
Topics: CATHODES, INSERTS, INTERNAL PRESSURE, ORIFICES, CURRENT DENSITY, EROSION, HOLLOW CATHODES, ION...
Initial mission profile studies have shown iodine will enable micro-satellites to accomplish several Air Force missions using much smaller, cheaper satellites; orbit raising, deorbiting, rendezvous, maintenance mission, orbital debris removal, retrieval of errant spacecraft. Iodine imparts volume-constrained spacecraft with up to three times the impulse compared to existing space propulsion systems (i.e. Hall Effect Thruster with xenon). Iodine is stored as a solid (no high pressure vessels),...
Topics: DTIC Archive, Branam,Richard D, The University of Alabama Tuscaloosa United States, Electric...
Cometary rendezvous missions using ion propulsion is considered. The characteristics of the ion engine are discussed including the fuel efficiency and acceleration, and the design of the ion engine is described. The operation of the ion drive engine and an overview of its applications are presented.
Topics: NASA Technical Reports Server (NTRS), HALLEY'S COMET, ION ENGINES, ION PROPULSION, COMETS, ROCKET...
The principal characteristics of the 30-centimeter ion propulsion thrust subsystem technology that was developed to satisfy the propulsion needs of future planetary and early orbital missions are described. Functional requirements and descriptions, interface and performance requirements, and physical characteristics of the hardware are described at the thrust subsystem, BIMOD engine system, and component level.
Topics: NASA Technical Reports Server (NTRS), ENGINE DESIGN, ION PROPULSION, MANUALS, SYSTEMS ENGINEERING,...
Apparatus and methods for large-area, high-power ion engines comprise dividing a single engine into a combination of smaller discharge chambers (or segments) configured to operate as a single large-area engine. This segmented ion thruster (SIT) approach enables the development of 100-kW class argon ion engines for operation at a specific impulse of 10,000 s. A combination of six 30-cm diameter ion chambers operating as a single engine can process over 100 kW. Such a segmented ion engine can be...
Topics: NASA Technical Reports Server (NTRS), ION ENGINES, ION PROPULSION, IONIZATION CHAMBERS, SEGMENTS,...
A method and system for storing and delivering a noble gas for an ion propulsion system where an adsorbent bearing a noble gas is heated within a storage vessel to desorb the noble gas which is then flowed through a pressure reduction device to a thruster assembly. The pressure and flow is controlled using a flow restrictor and low wattage heater which heats an adsorbent bed containing the noble gas propellant at low pressures. Flow rates of 5-60 sccm can be controlled to within about 0.5% or...
Topics: NASA Technical Reports Server (NTRS), ADSORBENTS, ION PROPULSION, RARE GASES, ION ENGINES, PATENTS,...
Two 12 cm magneto-electrostatic containment (MESC) ion thrusters were performance mapped with argon and xenon. The first, hexagonal, thruster produced optimized performance of 48.5to 79 percent argon mass utilization efficiencies at discharge energies of 240 to 425 eV/ion, respectively, Xenon mass utilization efficiencies of 78 to 95 percent were observed at discharge energies of 220 to 290 eV/ion with the same optimized hexagonal thruster. Changes to the cathode baffle reduced the discharge...
Topics: NASA Technical Reports Server (NTRS), ENGINE TESTS, ION PROPULSION, RARE GASES, ARGON, ELECTRIC...
Tests were performed to characterize the particles and fields associated with two 30 cm mercury ion thrusters operating independently and simultaneously. Flux rates and energies of ions and their distribution around the thrusters were determined. Facility effect ions were measured and their effect on thruster created flux measurements was assessed. The flux rate and distribution of sputtered metal atoms was determined and compared with theory and previous measurements. Mapping of the potential...
Topics: NASA Technical Reports Server (NTRS), ELECTRIC FIELDS, FLUX DENSITY, ION PROPULSION, MERCURY ION...
A laboratory model 8 cm thruster with improvements to minimize ion chamber erosion and peeling of sputtered metal was subjected to a cyclic endurance test for 15,040 hours and 460 restarts. A charted history of several thruster operating variables and off-normal events are shown in 600-hour segments at three points in the test. The transient behavior of these variables during a typical start-stop cycle is presented. Finding of the post-test inspection confirmed most of the expected results....
Topics: NASA Technical Reports Server (NTRS), ENGINE TESTS, ION PROPULSION, MERCURY (METAL), COMBUSTION...
The lateral neutralization of ion beams is treated by standard mathematical methods for first order, nonlinear partial differential equations. A closed form analytical solution is derived for the transient lateral beam neutralization for electron injection by means of a von Mises transformation. A nonlinear theory of the longitudinal ion beam neutralization is developed using the von Mises transformation. By means of the Lenard-Balescu equation, the intercomponent momentum transfer between...
Topics: NASA Technical Reports Server (NTRS), ION ENGINES, PLASMA PHYSICS, BOUNDARY VALUE PROBLEMS,...
A high voltage pulse generated by a capacitor discharge into a step-up transformer has been demonstrated capable of consistently igniting hollow cathode mercury discharges at propellant flows and heater power levels much below those required by conventional cathode starting. Results are presented for 3.2-mm diameter enclosed and open keeper cathodes. Starting characteristics are shown to depend on keeper voltage, mercury flow rate, heater power, keeper orifice size, emissive materials, and...
Topics: NASA Technical Reports Server (NTRS), ELECTRON BOMBARDMENT, ION PROPULSION, MERCURY VAPOR, PULSE...
The theory of the ion-thruster propulsion system is discussed along with the Space Electric Rocket Test 1 and 2. The use of electric propulsion for stationkeeping and attitude control functions of geosynchronous satellites is described, and a comparison of thruster systems is presented.
Topics: NASA Technical Reports Server (NTRS), ION PROPULSION, MERCURY ION ENGINES, ELECTRIC PROPULSION,...
The objectives of the flight test and a description on how those objectives are in support of an overall program goal of attaining user application were described. The approach to accomplishment was presented as it applies to integrating the propulsion system with the host spacecraft. A number of known interface design considerations which affect the propulsion system and the spacecraft were discussed. Analogies were drawn comparing the relationship of the organizations involved with this...
Topics: NASA Technical Reports Server (NTRS), AUXILIARY PROPULSION, FLIGHT TESTS, MERCURY ION ENGINES,...
236
236
Jun 9, 2011
06/11
by
Pougatchev, Nikita S
texts
eye 236
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Carbon monoxide is considered mission critical (TRACE-P NRA) because it is one of the gases involved in controlling the oxidizing power of the atmosphere and, as a tracer gas, is valuable in interpreting mission data sets. Carbon monoxide exhibits interannual differences, suggesting relatively short-term imbalances in sources and sinks. Sources of CO are dominated by fossil fuel combustion, biomass burning, and the photochemical oxidation of CH4 and nonmethane hydrocarbons while reaction with...
Topics: ION OPTICS, ELECTRIC POTENTIAL, TEST FACILITIES, MOLYBDENUM, VIBRATION TESTS, ION PROPULSION,...
166
166
Jul 23, 2010
07/10
by
Raman, Ganesh; Rice, Edward J.; Mankbadi, Reda R
texts
eye 166
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The limitations of single frequency plane wave excitation in mixing enhancement are investigated for a circular jet. Measurements made in an 8.8 cm diameter jet are compared with a theoretical model. The measurements are made to quantify mixing at excitation amplitudes up to 2 percent of the jet exit velocity. The initial boundary layer state, the exit mean and fluctuating velocity profiles and spectra are documented for all cases considered. The amplitude of the fundamental wave is recorded...
Topics: ARC JET ENGINES, MAGNETIC FIELDS, OPTICS, REFRACTORY MATERIALS, ELECTROSTATIC ENGINES, ION...
198
198
May 22, 2011
05/11
by
Hung, R. J
texts
eye 198
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The generalized mathematical formulation of sloshing dynamics for partially filled liquid of cryogenic superfluid helium II in dewar containers driven by the gravity gradient and jitter accelerations associated with slew motion for the purpose to perform scientific observation during the normal spacecraft operation are investigated. An example is given with the Advanced X-Ray Astrophysics Facility-Spectroscopy (AXAF-S) for slew motion which is responsible for the sloshing dynamics. The jitter...
Topics: ION ENGINES, THROTTLING, VIBRATION, ION PROPULSION, PROPULSION SYSTEM PERFORMANCE, ROCKET ENGINE...
