A5067204585- Plasma Diagnostics and Applications
- Electrohydrodynamics and Fluid Dynamics
- Astro and Planetary Science
- Advanced Data Storage Technologies
- Spacecraft and Cryogenic Technologies
- Radiation Effects in Electronics
- Particle accelerators and beam dynamics
- Magnetic Field Sensors Techniques
- Acoustic Wave Phenomena Research
- Seismic Waves and Analysis
- Seismic Imaging and Inversion Techniques
- Spacecraft Design and Technology
- Cryptographic Implementations and Security
- Planetary Science and Exploration
- Rocket and propulsion systems research
- Vacuum and Plasma Arcs
- Plasma Applications and Diagnostics
- Ultrasonics and Acoustic Wave Propagation
- Muon and positron interactions and applications
- Underwater Acoustics Research
- Metamaterials and Metasurfaces Applications
- Ionosphere and magnetosphere dynamics
- Probabilistic and Robust Engineering Design
- Electromagnetic Launch and Propulsion Technology
- Landslides and related hazards
ETH Zurich
1990-2024
Glenn Research Center
2011-2022
National Aeronautics and Space Administration
1993-2012
National Technical Information Service
2012
University of Stuttgart
2008-2012
Deutsche Telekom (United Kingdom)
2011
BASF (United States)
2008
Rheinmetall (Switzerland)
1982
University of Kaiserslautern
1978
The characterization of a miniaturized ionic liquid electrospray thruster for nanosatellite applications is presented. investigated features an emitter array 480 tips per square centimeter and propellant tank with entirely passive supply; it operated at power level less than 0.15 W. paper presents energy- mass-resolving beam spectroscopy the packaged system, as well two independent thrust measurements. This allows derivation performance parameters under realistic firing conditions, including...
The accurate, direct measurement of thrust or impulse is one the most critical elements electric thruster characterization, and it difficult measurements to make. This paper summarizes recommended practices for design, calibration, operation pendulum stands, which are widely recognized as best approach measuring micronewton- millinewton-level micronewton-per-second-level bits. fundamentals stand reviewed, along with implementation hanging pendulum, inverted torsional balance configurations....
A thrust stand for use with magnetoplasmadynamic (MPD) thrusters operated at powers up to 250 kW steady state has been built and tested. The was based on an inverted pendulum configuration which resulted in large displacements high resolution. Up 50 mm of deflection observed under a force 5 N. This range displacement significantly reduced the effects facility induced vibrations measurements. remotely system provided situ calibration prior immediately after data were obtained. Calibrations...
Abstract Mitigating the energy requirements of artificial intelligence requires novel physical substrates for computation. Phononic metamaterials have vanishingly low power dissipation and hence are a prime candidate green, always‐on computers. However, their use in machine learning applications has not been explored due to complexity design process. Current phononic restricted simple geometries (e.g., periodic tapered) do possess sufficient expressivity encode tasks. A non‐periodic...
NASA’s Glenn Research Center has been selected to lead development of Evolutionary Xenon Thruster (NEXT) system. The central feature the NEXT system is an electric propulsion thruster (EPT) that inherits knowledge gained through NSTAR successfully propelled Deep Space 1 asteroid Braille and comet Borrelly, while significantly increasing power level making improvements in performance parameters associated with NSTAR. EPT concept under a 40 cm beam diameter, twice effective area Deep-Space...
A torsional-type thrust stand has been designed and built to test pulsed plasma thrusters in both single shot repetitive operating modes. Using this stand, momentum per pulse is determined strictly as a function of deflection, spring stiffness, natural frequency. No empirical corrections are required. The accuracy the method was verified using swinging impact pendulum. Momentum transfer data between pendulum were consistent within 1%. Following initial calibrations, used Lincoln experimental...
A test to characterize the effect of varying background pressure on NASA's 12.5-kW Hall Effect Rocket with Magnetic Shielding had being completed. This thruster is baseline propulsion system for Solar Electric Propulsion Technology Demonstration Mission (SEP TDM). Potential differences in performance and oscillation characteristics when ground facilities versus on-orbit are considered a primary risk Asteroid Redirect Robotic Mission, which candidate SEP TDM. The first objective this was...
NASA's Hall Effect Rocket with Magnetic Shielding (HERMeS) 12.5 kW Technology Demonstration Unit-1 (TDU-1) has been the subject of extensive technology maturation in preparation for flight system development. Part effort included experimental evaluation TDU-1 thruster conducting and dielectric front pole cover materials two different electrical configurations. A graphite magnetic configuration body electrically tied to cathode, an alumina floating were evaluated. Both configurations also...
James S. Sovey, John A. Hamley, Thomas W. Haag, Michael J. Patterson, Eric Pencil,Todd T. Peterson, Luis R. Pinero, L. Power, Vincent K. Rawlin, and Charles SarmientoNASA Lewis Research Center, Cleveland, OhioJohn Anderson, Raymond Becker, Brophy, E. PolkJet Propulsion Laboratory, Pasadena, CaliforniaGerald Benson, Bond, G. I. Cardwell, Jon Christensen, Kenneth Freick,David Hamel, Stephen Hart, McDowell, Kirk Norenberg, Keith Phelps,Ezequiel Solis, Harold YostHughes Electron Dynamics...
ABSTRACT The Seismic Experiment for Interior Structures (SEIS) was deployed on Mars in November 2018 and began science operations March 2019. SEIS is the primary instrument of Exploration using Investigations, Geodesy Heat Transport (InSight) mission, which launched by National Aeronautics Space Administration (NASA). acquisition control (AC) electronics a key element SEIS. AC acquires seismic signals two sets sensors with high resolution, stores data its local nonvolatile memory later...
Practical implementation of the proposed Jupiter Icy Moon Orbiter (JIMO) mission, which would require a total delta V approximately 38 km/s, will development high power, specific impulse propulsion system. Initial analyses show that power gridded ion thrusters could satisfy JIMO mission requirements. A NASA GRC-led team is developing large area, impulse, nominally 25 kW thruster to both performance and lifetime requirements for this mission. The design philosophy status as well assessment...
fabrication of the thruster, assembly test setup, and operation vacuum facility.
The performance of many Hall thrusters has been shown to exhibit sensitivity background pressure in ground-based test facilities, and this property can have an impact on the prediction in-space performance. SPT-140 thruster, similar design SPT-100 which shows such sensitivity, was subjected a series tests characterize effects thruster over discharge power range 0.9–4.5 kW. Thrust pressure, absolute sense, largest at 4.5 kW decreased with until there little-to-no measurable effect 0.9 In...
The performance of a three-channel, 100-kW nested Hall thruster was evaluated on xenon propellant for total powers up to 102 kW. demonstrated stable operation in all seven available channel combinations at discharge voltages from 300 500 V and three different current densities. resulting test matrix contained forty-six unique conditions ranging 5 kW power 16 247 A current. At each operating condition, thrust, specific impulse, efficiency were characterized. All showed similar given voltage...
NASA’s Glenn Research Center (GRC) is leading the development of Evolutionary Xenon Thruster (NEXT) system. The central feature NEXT system an electric propulsion thruster that inherits knowledge gained through NSTAR successfully propelled Deep Space 1 to asteroid Braille and comet Borrelly, while significantly increasing power level making improvements in performance parameters associated with NSTAR. under has a 40 cm beam diameter, twice effective area Deep-Space thruster. It incorporates...
The performance of the NASA Glenn Research Center designed and fabricated 20 kW NASA-300M thruster was evaluated. Testing performed at power levels between 2.5 with xenon krypton propellants. all discharge voltage conditions indicated that operation stable, no anomalous behavior or thermal limitations on were observed. Xenon propellant testing a peak total thrust efficiency 67% specific impulse 2,920 s voltages 500 600 V, respectively. Krypton revealed 63% 3,223 V.
Overview of the
We present a fundamentally new approach to laboratory acoustic and seismic wave experimentation that enables full immersion of physical propagation experiment within virtual numerical environment. Using recent theory immersive boundary conditions relies on measurements made an inner closed surface sensors, the output numerous closely spaced sources around domain is continuously varied in time space. This allows waves seamlessly propagate back forth between both domains, without being...
Wave manipulation for cloaking and holography is difficult in practice, because most techniques are limited bandwidth their ability to adapt response varying incoming wave fields. In this study, acoustic sources on closed surfaces have responses calculated fed back real time, suppress forward backward scattering from objects without prior knowledge of the incident field. Furthermore, arbitrary virtual can be emulated by changing boundary conditions applied surface. The authors demonstrate...
For missions beyond low Earth orbit, spacecraft size and mass can be dominated by onboard chemical propulsion systems propellants that may constitute more than 50 percent of the mass. This impact substantially reduced through utilization Solar Electric Propulsion (SEP) due to its higher specific impulse. Studies performed for NASA's Human Exploration Operations Mission Directorate Science have demonstrated a 50kW-class SEP capability enabling both near term future architectures science...
Covers advancements in spacecraft and tactical strategic missile systems, including subsystem design application, mission analysis, materials structures, developments space sciences, processing manufacturing, operations, applications of technologies to other fields.