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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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At least 253 records · Page 14
All sourcesNASA NTRSDOE OSTI
DOE OSTI2024

High-resolution ion mobility based on traveling wave structures for lossless ion manipulation resolves hidden lipid features

Abstract High-resolution ion mobility (resolving power > 200) coupled with mass spectrometry (MS) is a powerful analytical tool for resolving isobars and isomers in complex samples. High-resolution ion mobility is capable of discerning additional structurally distinct features, which are not observed with conventional resolving power ion mobility (IM, resolving power ~ 50) techniques such as traveling wave IM and drift tube ion mobility (DTIM). DTIM in particular is considered to be the “gold standard” IM technique since collision cross section (CCS) values are directly obtained through a first-principles relationship, whereas traveling wave IM techniques require an additional calibration strategy to determine accurate CCS values. In this study, we aim to evaluate the separation capabilities of a traveling wave ion mobility structures for lossless ion manipulation platform integrated with mass spectrometry analysis (SLIM IM-MS) for both lipid isomer standards and complex lipid samples. A cross-platform investigation of seven subclass-specific lipid extracts examined by both DTIM-MS and SLIM IM-MS showed additional features were observed for all lipid extracts when examined under high resolving power IM conditions, with the number of CCS-aligned features that resolve into additional peaks from DTIM-MS to SLIM IM-MS analysis varying between 5 and 50%, depending on the specific lipid sub-class investigated. Lipid CCS values are obtained from SLIM IM ( TW(SLIM) CCS) through a two-step calibration procedure to align these measurements to within 2% average bias to reference values obtained via DTIM ( DT CCS). A total of 225 lipid features from seven lipid extracts are subsequently identified in the high resolving power IM analysis by a combination of accurate mass-to-charge, CCS, retention time, and linear mobility-mass correlations to curate a high-resolution IM lipid structural atlas. These results emphasize the high isomeric complexity present in lipidomic samples and underscore the need for multiple analytical stages of separation operated at high resolution. Graphical abstract

Reardon, Allison R. (ORCID:0000000165830134)↗
DOE OSTI2021

Structural Insights into the Vapochromic Behavior of Pt- and Pd-Based Compounds

Anionic complexes having vapochromic behavior are investigated: [K(H 2 O)][M(ppy)(CN) 2 ], [K(H 2 O)][M(bzq)(CN) 2 ], and [Li(H 2 O) n ][Pt(bzq)(CN) 2 ], where ppy = 2-phenylpyridinate, bzq = 7,8-benzoquinolate, and M = Pt(II) or Pd(II). These hydrated potassium/lithium salts exhibit a change in color upon being heated to 380 K, and they transform back into the original color upon absorption of water molecules from the environment. The challenging characterization of their structure in the vapochromic transition has been carried out by combining several experimental techniques, despite the availability of partially ordered and/or impure crystalline material. Room-temperature single-crystal and powder X-ray diffraction investigation revealed that [K(H 2 O)][Pt(ppy)(CN) 2 ] crystallizes in the Pbca space group and is isostructural to [K(H 2 O)][Pd(ppy)(CN) 2 ]. Variable-temperature powder X-ray diffraction allowed the color transition to be related to changes in the diffraction pattern and the decrease in sample crystallinity. Water loss, monitored by thermogravimetric analysis, occurs in two stages, well separated for potassium Pt compounds and strongly overlapped for potassium Pd compounds. Furthermore, the local structure of potassium compounds was monitored by in situ pair distribution function (PDF) measurements, which highlighted changes in the intermolecular distances due to a rearrangement of the crystal packing upon vapochromic transition.

36 MATERIALS SCIENCE↗
DOE OSTI2018

Effect of synchrotron radiation on the dynamics of electron spin precession in the process of laser-plasma acceleration

A model was developed and tested for studying the dynamics of spin precession and trajectories of charged particles in the wake fields generated in a laser-plasma accelerator. The model takes into account the radiation reaction force in the Landau – Lifshits form. An investigation is made of the effect of synchrotron radiation on the dynamics of energy gaining and spin precession of electrons accelerated in model constant fields as well as on the particle beam polarisation in the acceleration at a separate acceleration stage in the case of self-consistent description of the nonlinear dynamics of a laser pulse and its generated accelerating and focusing plasma wake fields. It is shown that synchrotron radiation hardly affects the energy gain rate and polarisation of the electrons that are accelerated in the fields characteristic for a moderately nonlinear mode of laser-plasma acceleration up to an energy of 3.8 TeV. (extreme light fields and their interaction with matter)

70 PLASMA PHYSICS AND FUSION TECHNOLOGY↗
DOE OSTI2019

Anomalous interfacial stress generation during sodium intercalation/extraction in MoS 2 thin-film anodes

Although the generation of mechanical stress in the anode material is suggested as a possible reason for electrode degradation and fading of storage capacity in batteries, only limited knowledge of the electrode stress and its evolution is available at present. Here, we show real-time monitoring of the interfacial stress of a few-layer MoS 2 system under the sodiation/desodiation process using microcantilever electrodes. During the first sodiation with a voltage plateau of 1.0 to 0.85 V, the MoS 2 exhibits a compressive stress (2.1 Nm -1 ), which is substantially smaller than that measured (9.8 Nm -1 ) during subsequent plateaus at 0.85 to 0.4 V due to the differential volume expansion of the MoS 2 film. The conversion reaction to Mo below 0.1 V generates an anomalous compressive stress of 43 Nm -1 with detrimental effects. These results also suggest the existence of a separate discharge stage between 0.6 and 0.1 V, where the generated stress is only approximately one-third of that observed below 0.1 V. This approach can be adapted to help resolve the localized stress in a wide range of electrode materials, to gain additional insights into mechanical effects of charge storage, and for long-lifetime battery design.

36 MATERIALS SCIENCE↗
DOE OSTI2019

A Review of Nonscaling CW FFAs for Proton and Ion Therapy Applications

Significant progress on compact, variable-energy versions of non-scaling fixed field accelerators with alternating strong-focusing gradients (nsFFA) has been made and adapted to proton and ion therapy. Not only has isochronous (CW) capability been demonstrated in a realizable design, an isochronous racetrack format has evolved which supports lengthy, synchrotron-like straight sections. Long straight insertions promote low-loss injection and extraction systems and further facilitate extracting lower-energy orbits using a bipolar bump-magnet system. To efficiently extract variable energy using this method, the accelerator complex requires separated accelerator stages, each stage with limited but therapeutically optimized energy ranges targeting specific cancer types and penetration depths. Different energy stages further support multiple treatment rooms increasing patient throughput and reducing treatment cost. The staged system proposed here also realizes cost savings in gantries by tailoring delivery to different therapeutic energies and beam requirements, promoting the requirement for only one high-energy gantry in the facility. The proposed facility consists of 3 stages, a 30 MeV injector, a 30 - 90 MeV/nucleon FFA for shallow cancers, and 90 - 250/330 MeV/nucleon stage for deep tumors, pelvis for example. The higher energy of the final stage, 330 MeV/nucleon is preferred to support Proton Computed Tomography. Isochronous FFA stages can be designed to accelerate either protons or ions with charge to mass of 1/2.

43 PARTICLE ACCELERATORS↗
DOE OSTI2019

Additive Manufacturing Fabrication of PEEK Counter-Current Centrifugal Contactor Components

Additive manufacturing (AM, also known as 3D printing) offers significant advantages for the fabrication of annular centrifugal contactor-separator (CCS) stages, particularly when complemented by post-processing via traditional machining. The shortcomings of 3D printing of CCSs are offset by its low cost, quick turnaround, and ability to manufacture enhanced mixing sections and multistage modules. High-density acrylic materials show promise for improved chemical resistance and mechanical properties. The demonstration of the MOEX process using acrylic AM CCS stages confirmed their full functionality and showed significant flexibility in geometry design while using relatively low-cost plastic materials. Over the past two years, AM has been used to produce low-cost centrifugal contactor components, ranging from bench-scale laboratory testing to a full-scale industrial process with on-hand availability of spare parts and great flexibility in design modifications and quick testing and implementation. However, the shortcomings of stereo lithography assembly (SLA)-printed acrylic components became apparent rather quickly. By the completion of the initial MOEX demonstration using the 9-stage 2-cm CCS bank, nearly half of the rotors had begun to fail from pitting and cracking. These problems were most likely caused by swelling of the rotor due to liquid absorption, resulting in improper excess run out, mechanical abrasion, and chemical exposure of the roughened surface. Additional deterioration of the acrylic stages was later discovered when the interiors of the acrylic housings began to experience flaking and delamination as the plastic dried out several weeks after the tests. All of these issues caused severe limitations to the lifespan of the CCS stages, which are acceptable for R&D but undesirable for commercial-scale production.

42 ENGINEERING↗
NASA NTRS1972

The space shuttle

Two objectives of the space shuttle, or reusable reentry vehicle, are economy and the speed with which it can be made operational. Its mission will be carried out in six stages: launching, separation of the fuel tank, separation of the booster, placing the payload in orbit, return to the atmosphere, and the actual landing. The major element, the orbiter, is described. Some aspects of European participation in the program are discussed.

Myers, D. D.↗
NASA NTRS1973

Space Shuttle system solid rocket booster.

Description of the mission and systems requirement of the solid rocket booster as it supports the Shuttle vehicle configuration. The solid booster is equipped with load skirts and linkages that can accommodate full mission loads, a solid propellant motor for delivering required performance, thrust vector control for augmentation of Shuttle vehicle ascent control, staging and separation systems, and electrical subsystems. To recover and reuse the solid booster case a recovery package is provided. The definition of these functional elements of the solid booster are discussed with the requirements placed on each element to satisfy the overall booster objective.

Thomason, H. E.↗
NASA NTRS1980

Improved PFB operations: 400-hour turbine test results

A pressurized fluidized bed (PFB) coal-burning reactor was used to provide hot effluent gases for operation of a small gas turbine. Preliminary tests determined the optimum operating conditions that would result in minimum bed particle carryover in the combustion gases. Solids were removed from the gases before they could be transported into the test turbine by use of a modified two stage cyclone separator. Design changes and refined operation procedures resulted in a significant decrease in particle carryover, from 2800 to 93 ppm (1.5 to 0.05 grains/std cu ft), with minimal drop in gas temperature and pressure. The achievement of stable burn conditions and low solids loadings made possible a 400 hr test of small superalloy rotor, 15 cm (6 in.) in diameter, operating in the effluent. Blades removed and examined metallographically after 200 hr exhibited accelerated oxidation over most of the blade surface, with subsurface alumina penetration to 20 micron m. After 400 hours, average erosion loss was about 25 micron m (1 mil). Sulfide particles, indicating hot corrosion, were present in depletion zones, and their presence corresponded in general to the areas of adherent solids deposit. Sulfidation appears to be a materials problem equal in importance to erosion.

Rollbuhler, R. J.↗
NASA NTRS1985

Experimental studies on the reaction kinetics of 1,1-dimethylhydrazine and oxygen

Measurements behind shock waves in highly diluted 1,1 dimethylhydrazine-O2-Ar mixtures clearly showed a two-stage reaction. In the first stage, UDMH decomposes via a unimolecular step; in the second stage, clearly separated from the first one, the decay products react further with O2. Values for the rate constant of unimolecular decomposition were obtained.

Just, T.↗
NASA NTRS1988

Application of pattern recognition techniques to the identification of aerospace acoustic sources

A pattern recognition system was developed that successfully recognizes simulated spectra of five different types of transportation noise sources. The system generates hyperplanes during a training stage to separate the classes and correctly classify unknown patterns in classification mode. A feature selector in the system reduces a large number of features to a smaller optimal set, maximizing performance and minimizing computation.

Fuller, Chris R.↗
NASA NTRS1989

Space nuclear power applied to electric propulsion

Space reactor power systems with characteristics ideal for advanced spacecraft systems applications are discussed. These characteristics are: high power-to-weight ratio (15 to 33 W/kg); high volume density (high ballistic coefficient); no preferential orientation in orbit; long operational life; high reliability; and total launch and operational safety. These characteristics allow the use of electric propulsion to raise spacecraft from low earth parking orbits to operational orbits, greatly increasing the useful orbit payload for a given launch vehicle by eliminating the need for a separation injection stage. A proposed demonstration mission is described.

Vicente, F. A.↗
NASA NTRS1991

Atomic oxygen degradation of Intelsat 4-type solar array interconnects: Laboratory investigations

A Hughes 506 type communication satellite belonging to the Intelsat organization was marooned in low Earth orbit on March 14, 1990, following failure of the Titan third stage to separate properly. The satellite, Intelsat VI, was designed for service in geosynchronous orbit and contains several material configurations which are susceptible to attack by atomic oxygen. Analysis showed the silver foil interconnects in the satellite photovoltaic array to be the key materials issue because the silver is exposed directly to the atomic oxygen ram flux. The results are reported of atomic oxygen degradation testing of Intelsat VI type silver foil interconnects both as virgin material and in a configured solar cell element. Test results indicate that more than 80 pct. of the original thickness of silver in the Intelsat VI solar array interconnects should remain after completion of the proposed Space Shuttle rescue and/or reboost mission.

Koontz, S. L.↗
NASA NTRS1993

Use of switched capacitor filters to implement the discrete wavelet transform

This paper analyzes the use of IIR switched capacitor filters to implement the discrete wavelet transform and the inverse transform, using quadrature mirror filters (QMF) which have the necessary symmetry for reconstruction of the data. This is done by examining the sensitivity of the QMF transforms to the manufacturing variance in the desired capacitances. The performance is evaluated at the outputs of the separate filter stages and the error in the reconstruction of the inverse transform is compared with the desired results.

Kaiser, Kraig E.↗
NASA NTRS1994

Intelsat solar array coupon atomic oxygen flight experiment

A Hughes communications satellite (INTELSAT series) belonging to the INTELSAT Organization was marooned in low-Earth orbit (LEO) on March 14, 1990, following failure of the Titan launch vehicle third stage to separate properly. The satellite, INTELSAT 6, was designed for service in geosynchronous orbit and contains several materials that are potentially susceptible to attack by atomic oxygen. Analysis showed that direct exposure of the silver interconnects in the satellite photovoltaic array to atomic oxygen in LEO was the key materials issue. Available data on atomic oxygen degradation of silver are limited and show high variance, so solar array configurations of the INTELSAT 6 type and individual interconnects were tested in ground-based facilities and during STS-41 (Space Shuttle Discovery, October 1990) as part of the ISAC flight experiment. Several materials for which little or no flight data exist were also tested for atomic oxygen reactivity. Dry lubricants, elastomers, and polymeric and inorganic materials were exposed to an oxygen atom fluence of 1.1 x 10(exp 20) atoms cm(exp 2). Many of the samples were selected to support Space Station Freedom design and decision making. This paper provides an overview of the ISAC flight experiment and a brief summary of results. In addition to new data on materials not before flown, ISAC provided data supporting the decision to rescue INTELSAT 6, which was successfully undertaken in May 1992.

TRT-GENERAL REVIEW↗
NASA NTRS1998

Deep Space 2: The Mars Microprobe Project and Beyond

The Mars Microprobe Project, or Deep Space 2 (DS2), is the second of the New Millennium Program planetary missions and is designed to enable future space science network missions through flight validation of new technologies. A secondary goal is the collection of meaningful science data. Two micropenetrators will be deployed to carry out surface and subsurface science. The penetrators are being carried as a piggyback payload on the Mars Polar Lander cruise ring and will be launched in January 1999. The microprobe has no active control, attitude determination, or propulsive systems. It is a single stage from separation until landing and will passively orient itself due to its aerodynamic design. The aeroshell will be made of a nonerosive heat shield material, Silicon impregnated Reusable Ceramic Ablator(SIRCA), developed at Ames Research Center. The aeroshell shatters on impact, at which time the probe separates into an aftbody that remains at the surface and a forebody that penetrates into the subsurface. Each probe has a total mass of up to 3 kg, including the aeroshell. The impact velocity will be about 180 meters per second. The forebody will experience up to 30,000 g's and penetrate between 0.3 and 2 meters, depending on the ice content of the soil. The aftbody deceleration will be up to 80,000 g. The penetrators arrive in December 1999. The landing ellipse latitude range is 73 deg-77 deg S. The longitude will be selected by the Mars Surveyor Project to place the lander on the polar layered deposits in the range of 180 deg -230 deg W. The two micropenetrators are likely to land within 100 km of the Mars Surveyor Lander, on the polar deposits. The likely arrival date is L(sub s) = 256, late southern spring. The nominal mission lasts 2 days. A science team was selected in April 1998.

Smrekar, S. E.↗