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  • Other Sources  (8,440)
  • 2015-2019  (8,440)
  • 1950-1954
  • 2015  (8,440)
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  • 2015-2019  (8,440)
  • 1950-1954
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  • 1
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    Environmental development and local human impact in the Jeetzel valley (N Germany) since 10 ka BP as detected by geoarchaeological analyses in a coupled aeolian and lacustrine sediment archive at Soven (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: While archaeological records indicate an intensive Mesolithic occupation of dune areas situated along river valleys, relatively little knowledge exists about environmental interactions in the form of land-use strategies and their possible local impacts. The combination of geoarchaeological, chronological, geochemical and palaeoecological research methods and their application both on a Mesoltihic site situated on top of a dune and the adjacent palaeochannel sediments allows for a detailed reconstruction of the local environmental development around the Soven site in the Jeetzel valley (Northern Germany) since ~10.5 ka cal BP. Based on the results, we identified four phases that may be related to local human impact twice during the Mesolithic, the Neolithic and the Iron Ages and are discussed on the backdrop of the regional settlement history. Although nearby Mesolithic occupation is evident on archaeological grounds, the identification of synchronous impacts on the vegetation in the local environmental records remains tentative even in respect of the broad methodical spectrum applied. Vice versa, human impact is strongly indicated by palaeoecological and geochemical proxies during the Neolithic period, but cannot be connected to archaeological records in the area so far. A younger phase of human impact – probably consisting of seasonal livestock farming in the wetlands – is ascribed to the Iron Age economy and comprises local soil erosion, raised concentrations of phosphates and urease, and the facilitation of grazing related taxa.
    Description: research
    Keywords: 551.7 ; aeolian sand ; pollen ; mesolithic ; iron age ; charcoal ; human impact ; OSL ; Neolithisation
    Language: English
    Type: article , Verlagsversion
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  • 2
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    A sound nebula. The origin of the Solar System in the field of a standing sound wave (2015)
    Details
    Publication Date: 2021-03-29
    Description: manual
    Keywords: 523.2 ; 550
    Type: article , draft
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  • 3
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    Periglaziäre, polygonal-verzweigte rinnenförmige Bildungen und glazitektonische Strukturen in Saale-Till am Elbe-Urstomtalrand bei Wedel (Schleswig-Holstein) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: Remarkable polygenetical structures were observed at a refinery rehabilitation site in Wedel/Holstein. The polygonal shaped, channel-like structures are incised in mid-Saalian clayey, chalk-rich till. They are symmetrically semicircular shaped and filled with calcareous, silty sands that can be interpreted as sandy reworked till with aeolian components. The width reaches from approx. 0.3 to 1.5 metres, the depth up to approx. 0.8 metres. Horizontal cracks up to more than 10 meters in lengths, occurring as narrow belts of sand with reddish colour, are often centrally aligned in the channel-like structures. The present-day red colour is not natural but related to pollution. These belts reach down to the bottom of the channel like structures. At the lower site of the channel-like structures glacitectonic fissures with a width up to a few centimetres were to be traced into a depth of several metres to the basis of the excavat ion. The genesis of the channel-like structures is discussed. e. g. a possible relation with the pre-existing glacitectonic joints resp. the expected periglacial paleohydrogeological setting.
    Description: research
    Keywords: 551.7 ; periglacial channels ; Weichselian periglacial ; frost wedges ; glacitectonism ; paleohydrogeology ; talik ; Elbe spillway
    Language: German
    Type: article , Verlagsversion
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  • 4
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    Chronostratigraphy of the Hochterrassen in the lower Lech valley (Northern Alpine Foreland) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: Hochterrassen (High or Higher Terraces) are a prominent geomorphological feature of the Northern Alpine Foreland and have traditionally been attributed to the Rissian glaciation. However, distinct morphological sublevels observed for this feature have often raised the question of their age. This issue is exemplarily investigated here on the Langweider and Rainer Hochterrassen in the lower Lech valley using different relative and numerical dating techniques. The lowest sublevel, the Übergangsterrasse is only preserved in small patches at the western rim of the Rainer Hochterrasse and is most probably of early Würmian age. The sublevel of the Jüngere Hochterrasse is older than the Last Interglacial, as indicated by luminescence ages of overlying loess/palaeosol sequence and the development of a luvisol on top of the terrace gravel. This terrace is composed of stacked gravel units that represent at least two accumulation phases correlating with Marine Isotope Stage (MIS) 6 for the top gravel and MIS 7 to MIS 10 (or older) for the basal gravel. It is not yet clear, if the deposition of the basal gravel unit corresponds to one or more aggradation phases during the Middle Pleistocene. The highest sublevel, the Ältere Hochterrasse also shows a compositon of two stacked gravel units but so far, no numerical ages have been achieved for these units.
    Description: research
    Keywords: 551.7 ; northern alpine foreland ; middle pleistocene ; luminescence dating ; Hochterrassen ; fluvial terraces
    Language: English
    Type: article , Verlagsversion
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  • 5
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    Late Pleistocene spotted hyena den sites and specialized rhinoceros scavengers in the karstified Zechstein areas of the Thuringian Mountains (Central Germany) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: Crocuta crocuta spelaea (Goldfuss 1823) cranial and postcranial remains of the Pößneck region in the Zechstein Karst region of the Thuringian Mountains (Central Germany) were excavated historically in the Wüste Scheuer Cavity at Döbritz. Nearby, at the Krölpa gypsum karst open air site, additionally a woolly rhinoceros, partially scavenged by Ice Age spotted hyenas, was found. The amount at Wüste Scheuer Cavity includes chew damaged Coelodonta antiquitatis remains and is classified herein as communal den type. At both den/scavenging sites, only a small amount of prey material of Late Pleistocene megafauna of rare M. primigenius, mainly C. antiquitatis, E. c. przewalskii, and fewer B. priscus and R. tarandus was accumulated. The dominance of woolly rhinoceros, bison and Przewalski horse bones are typical for hyena bone assemblages in European low mountain regions, where mammoth was nearly absent as a result of topography. In the Thuringian Karst Mountains nine Late Pleistocene Ice Age spotted hyena den sites are identified. Solely hyena dens are present in Zechstein open air gypsum and limestone karstic regions of Bad Köstritz, Krölpa and Fuchsluken Cavities near Saalfeld. In the Wüste Scheuer their remains overlap with Middle Palaeolithic Neanderthal human camp sites, similar as in the Ilsen Cave at Ranis and Lindenthal Cave in Gera, which demonstrates competition for prey and shelter cavities. At such cave sites, bone remains were historically misinterpreted as „solely of Neanderthal human kitchen rubbish” or even as “bone tools” (e.g. “bone scrapers” = woolly rhinoceros tibia bones chewed by hyenas).
    Description: research
    Keywords: 551.7 ; late pleistocene ; Ice Age spotted hyenas ; den types ; Thuringian Mountains ; Central Germany
    Language: English
    Type: article , Verlagsversion
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  • 6
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    Ein Uferprofil am Priesterbäker See: Slawenzeitlich-mittelalterliche Seespiegelschwankungen im Bereich der „Specker Seen“ (Mecklenburg) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-03-29
    Description: Eine durch einen Bodenschurf aufgeschlossene Boden-Sediment-Folge einer alten Seeterrasse im Einzugsgebiet des Priesterbäker Sees zeigt deutliche Fazieswechsel im Uferbereich des Gewässers. Die Abfolge von liegenden humosen Sanden, welche einen ehemaligen Verlandungssaum nachzeichnen, limnischen Sanden mit Bodenbildung und hangenden Flugsanden belegt Änderungen in der Sedimentation, welche mit säkularen Grundwasser- bzw. Seespiegelschwankungen zu erklären sind. Mit Hilfe von geophysikalischen Datierungen lassen sich gegenüber dem heutigen Niveau höhere Wasserstände für den Priesterbäker See bzw. die so genannten „Specker Seen“ östlich der Müritz während des 7.–9. und 12.–14. Jahrhunderts ableiten.
    Description: research
    Keywords: 551 ; 554.3 ; seespiegelschwankungen ; mecklenburg ; Seeterrasse ; Priesterbäker See ; Slawenzeit
    Language: German
    Type: article , Verlagsversion
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  • 7
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    Weichselzeitliche Kryocalcite als Hinweise für Eisseen in der Hüttenbläserschachthöhle (Iserlohn/NRW) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: C/O-stable isotope composition (VPDB) of speleothems from the Makkaronihalle of the Hüttenbläserschacht Cave in Iserlohn shows a clear separation between glacial and interglacial calcites. In contrast to normal speleothems (stalagmites, excentriques, crystals in cave ponds, draperies; δ18O: –4.0 to –6.1 ‰, δ13C: –4.9 to –10.9 ‰), rhombohedral crystal sinter and spherulitic speleoparticles are characterised by lower δ18O (–8.9 to –17.9 ‰) and higher δ13C values (+0.7 to –6.1 ‰). This suggests that these speleogenetic particles were formed in slowly freezing waterpools on ice during the transition from a stadial to an interstadial phase. Precise 230Th/U-dating shows younger Weichselian ages of 28.6 to 33.0 ka for these speleogenetic particles from north-west Germany. These formation periods indicate freezing conditions overlain by 34 m of hostrock and provide the minimum depth of permafrost penetration for the younger Weichselian in the area of the northern Sauerland (north-west Germany).
    Description: research
    Keywords: 551.7 ; permafrost ; Cryogenic calcites ; C/O isotopes ; Upper Weichselian ; ice caves ; north-western Germany
    Language: German
    Type: article , Verlagsversion
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  • 8
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    Spätsaalezeitliche und eemzeitliche Makrofaunen aus dem Kliffaufschluss Klein Klütz Höved (NW-Mecklenburg) (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: On the basis of the work done by Strahl et al. (1994), the mollusc specimens in the Late Saalian glacial and Eemian interglacial sediments from the cliff outcrop of Klein Klütz Höved (NW Mecklenburg) were re-examined and, in the process, a few vertebrates (fishes, micromammals) were also found. The mollusc specimens from the Late Saalian sand and mud alone comprise approximately 40 species among which terrestrial varieties, e.g. Succinella oblonga, Pupilla loessica, P. pratensis, Vallonia tenuilabris or Vertigo genesii, are clearly predominant as far as the number of individual specimens is concerned. Among the limnic varieties were also found the glacial index species Pisidium obtusale f. lapponicum and P. stewarti. It was also possible to prove the northern-most presence for Germany of the steppe lemming Lagurus lagurus in the Late Saalian. In the Eemian mud, the molluscs found were almost exclusively limnic. This about 20 species comprising fauna is characte-ristic of a river system with calmer areas, oxbow lakes and in-coming springs. These fluvial conditions were confirmed by the freshwater bivalves Pisidium amnicum, P. supinum, P. moitessierianum, P. ponderosum and Unio tumidus. For the first time in Mecklenburg-Western Pomerania, evidence was found of the spring snail Belgrandia germanica as an interglacial index species. The limnic-fluvial section of the Eemian is topped by a cryoturbate structures. Its sandy, gravelly pockets contain marine molluscs. The index species for the marine Eemian found in the southern Baltic region are Polititapes senescens and Bittium reticulatum.
    Description: research
    Keywords: 551.7 ; molluscs ; Saalian deposits ; limnic and marine Eemian facies ; Belgrandia germanica ; micromammals ; Lagurus lagurus ; Mecklenburg-Western Pomerania
    Language: German
    Type: article , Verlagsversion
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  • 9
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    Klima, Grundwassernutzung oder Waldbewirtschaftung? Ursachen tendenziell fallender Grundwasserstände am Beispiel Südwest-Usedoms (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-03-29
    Description: Tendenziell fallende Grundwasserstände können vielfältige Ursachen haben, z.B. die Änderung der klimatischen Bedingungen, Modifikationen der Landnutzung oder die Entnahme von Grundwasser. Am Beispiel Südwest-Usedoms wird dargestellt, wie mögliche Einflussfaktoren analysiert und quantifiziert werden können. Für das Untersuchungsgebiet zeigte sich, dass die über Jahrzehnte gesunkenen Grundwasserstände überwiegend aus der Kahlschlagbewirtschaftung des Waldes resultieren und damit weniger einen Trend als eine überjährliche Schwankung ausweisen.
    Description: research
    Keywords: 551 ; 554.3 ; forest ; Sickerwasser ; Grundwasser ; Grundwasserneubildung ; Wald ; Landschaftswasserhaushalt ; Trend ; Grundwasserentnahme ; geohydraulisches Modell ; Landscape water regime ; Groundwater ; Groundwater recharge ; percolate water ; Groundwater extraction ; Groundwater modelling ; Geohydraulic model ; Grundwasserströmung ; Modellierung
    Language: German
    Type: article , Verlagsversion
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  • 10
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    Bw horizon in Holocene slope deposits (Kratzeburg, NE Germany) – dating and pedological characteristics (2015)
    Geozon Science Media
    Details
    Publication Date: 2021-05-06
    Description: A soil-sediment sequence in NE Germany has provided information about the duration and intensity of formation of a Bw horizon in Holocene slope deposits. With a combination of optically stimulated luminescence (OSL), 14C- and archaeological dating methods, colluvial layers taken from a former castle wall trench constructed during the Bronze Age were dated. With this chronology, the relative age of the postsedimentary Bw horizon formation within the colluvial sediments was derived, resulting in the first valid pedochronological data (maximum and minimum age) for a Holocene Bw horizon in NE Germany. The horizon was formed within 2400 years. Weathering and brunification have altered the Holocene parent material. However, the geochemical characteristics of the Holocene soil formation are weak compared to Bw horizons from the Late Glacial and the Late Glacial to Holocene. The results presented here enhance our understanding of soil formation processes in northern Germany, while highlighting the role of colluvial layers as sedimentological tracers of Holocene soil formation processes.
    Description: research
    Keywords: 551.7 ; holocene ; ne germany ; dating ; Bw horizon ; Slope deposits ; soil formation
    Language: English
    Type: article , Verlagsversion
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  • 11
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    Neue Möglichkeiten interaktiver 3-dimensionaler Modellierungen von Potentialfeldern und ihrer Ableitungen (2015)
    DGMK/ÖGEW
    Details
    Publication Date: 2021-03-29
    Description: Die hier dargestellten Methoden dienen der drei-dimensionalen, interaktiven Bearbeitung der Potentialfelder Gravimetrie und Magnetik, sowie ihrer Ableitungen (Schwere- und Magnetik-Tensor). Die Methodik ist sowohl für terrestrische, als auch Bohrloch- und Airborne-Verfahren einsetzbar. Um die Mehrdeutigkeit der interaktiven Bearbeitung bei der Vorwärtsrechnung und Inversion der Felder zu minimieren, beziehen die numerischen Verfahren verstärkt eine schnelle Computergraphik ein, sodass die Randbedingungen (meist aus der Reflexionsseismik) für die Berechnungen durch den Anwender stets sichtbar sind. Die Vorwärtsrechnungen basieren auf der Approximation geologischer Strukturen durch Polyeder, die Inversionsrechnungen für Geometrie und Gesteinsparameter (Dichte, remanente und induzierte Gesteinsmagnetisierung) werden mit Hilfe der CMA-ES (covariance-matrix-adoption evolution strategy) durchgeführt. CMA-ES ist die ideale Methode, um stark nicht-lineare und komplexe Probleme der Geophysik zu optimieren. Der Benutzer hat die Möglichkeit, die Inversion visuell zu steuern und zu beeinflussen. Die die Untergrundstrukturen approximierenden Polyeder sind durch konstante Gesteinsparameter charakterisiert; durch die Überlagerung eines Voxelmodells sind auch Strukturen mit hochgradig variabler Gesteinsparameterverteilung darstellbar. In vielen Anwendungen liegen häufig Daten vor, deren Auflösung für eine Potentialfelder-Modellierung nicht unbedingt erforderlich ist: Hier helfen neu entwickelte automatisierte Verfahren der gestalt-erhaltenden Datenreduktion. Für die Visualisierung von Potentialfeldern in Bohrlöchern werden Beispiele für eine nutzerfreundliche Visualisierung gezeigt.
    Description: conference
    Keywords: 622.15 ; 550.28 ; 550 ; Gravimetrie ; 3D Modelling ; Visualisierung ; Bohrlochtool
    Language: German
    Type: anthologyArticle , publishedVersion
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  • 12
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    Holocene Vegetation and Land Use History in the Northern Vosges (France) (2015)
    Geozon Science Media
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    Publication Date: 2021-05-06
    Description: A radiocarbon-dated peat profile from Rond Pertuis supérieure mire in the uplands of the Northern Vosges is studied using palynological methods. The profile dates from the middle Atlantic period (4500–3100 B.C.) to recent times. During the middle of the Atlantic period an oak forest rich in pine covered the Northern Vosges. Fir and beech immigrated at the end of the Atlantic leading to the decline of oak and pine in the forest. This also marked the onset of decisive human influence on the development of the terrestrial vegetation. Five land use phases were detected, the first one at the end of the Neolithic period (~4000–2200 B.C.). Subsequently, continuous land use is evident from the Bronze Age (2200–800 B.C.) up to now. In the late Middle Ages (A.D. 900–1500) and the early Modern Era (since A.D. 1500), the woodlands were completely altered by human activities. During the 19th century modern forestry introduced spruce into the investigated area in the Northern Vosges. Spruce afforestation then accelerated in the middle of the 20th century.
    Description: research
    Keywords: 551.7 ; holocene ; pollen analysis ; france ; human impact ; Northern Vosges
    Language: English
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  • 13
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    Wahrnehmung und Akzeptanz des bundesländerübergreifenden Naturparks Barnim (2015)
    Ernst-Moritz-Arndt Universität Greifswald
    Details
    Publication Date: 2021-12-09
    Description: Die vorliegende Arbeit hat das Ziel, gesellschaftliche Entwicklungen im Naturpark Barnim zu untersuchen und darzustellen. Eine Zusammenfassung der Ergebnisse zweier quantitativer Bevölkerungsbefragungen untersucht die Einstellung der Menschen in Bezug auf ihre Region, Natur und Landschaft sowie in Bezug auf den Naturpark Barnim selbst. Die Ergebnisse liefern der Naturparkverwaltung damit empirische Daten, um das Management an die lokalen Bedürfnisse anzupassen. Begleitet wird diese Studie von einem Vorwort des Barnimer Naturparkleiters Dr. Peter Gärtner sowie von zwei Abschlussarbeiten, die im Rahmen des Bachelorstudiums am Lehrstuhl für Nachhaltigkeitswissenschaft und Angewandte Geographie entstanden. Für ausgewählte Berliner Stadtbezirke werden hierbei die Wahrnehmung und die Akzeptanz des Naturparks sowie der ihn prägenden Landschaften analysiert.
    Description: In Kooperation mit: Naturschutzfonds Brandenburg
    Description: research
    Keywords: 910 ; QGB 640 ; QFG 050 ; Brandenburg {Geographie} ; Regionalanalyse und Strukturforschung {Raumordnung und Raumplanung} ; Naturpark ; Barnim ; Sozioökonomisches Monitoring ; Regionale Identität
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  • 14
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    Local Perception and Preferences for Landscape and Land Use in the Fischland-Darß-Zingst Region, German Baltic Sea. (2015)
    Ernst-Moritz-Arndt Universität Greifswald
    Details
    Publication Date: 2021-12-09
    Description: Die vorliegende Arbeit entstand im Rahmen des Forschungsprojektes COMTESS (Sustainable Coastal Land Management: Trade-offs in Ecosystem Services). Ziel des COMTESS-Projektes ist es, konkrete aktions- und entscheidungsorientierte Vorschläge auf lokaler und regionaler Ebene zu erarbeiten, die eine nachhaltige Nutzung gefährdeter Küstenlandschaften an der ostfriesischen Nordseeküste und der Vorpommerschen Boddenlandschaft als Antworten auf den Klimawandel fördern. Der erste Teil dieser Arbeit beschäftigt sich mit regionaler Identität. Die Wahrnehmung und Bewertung der Bevölkerung von Landschaft und Landnutzung sowie wahrgenommene Veränderungen werden dahingehend untersucht, in wie weit sie die regionale Identität der Bevölkerung beeinflussen. Der zweite Teil der Arbeit beschäftigt sich mit der Bewertung von Rückdeichung als präferierte Maßnahme im Küstenzonenmanagement. Identifiziert werden Diskrepanzen zwischen der positiven Bewertung dieser Maßnahme durch Wissenschaft, Politik und Regionalplanung und der negativen Bewertung von Rückdeichung auf Seiten der Bevölkerung.
    Description: In Kooperation mit: Bundesministerium für Bildung und Forschung (BMBF)
    Description: research
    Keywords: 910 ; QGB 570 ; QFG 050 ; QG 606 ; Mecklenburg-Vorpommern {Geographie} ; Regionalanalyse und Strukturforschung {Raumordnung und Raumplanung} ; Angewandte Geographie der Küsten {Geographie} ; Nachhaltiges Landmanagement ; Küstenzonenmanagement ; Klimawandelanpassung ; Rückdeichung ; Regionale Identität
    Language: English
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  • 15
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    Geochemical/hydrochemical evaluation of the geothermal potential of the Lamongan volcanic field (Eastern Java, Indonesia) (2015)
    Details
    Publication Date: 2022-10-07
    Description: Magmatic settings involving active volcanism are potential locations for economic geothermal systems due to the occurrence of high temperature and steam pressures. Indonesia, located along active plate margins, hosts more than 100 volcanoes and, therefore, belongs to the regions with the greatest geothermal potential worldwide. However, tropical conditions and steep terrain reduce the spectrum of applicable exploration methods, in particular in remote areas. In a case study from the Lamongan volcanic field in East Java, we combine field-based data on the regional structural geology, elemental and isotopic composition of thermal waters, and the mineralogical and geochemical signatures of volcanic rocks in exploring hidden geothermal systems. Results suggest infiltration of groundwater at the volcanoes and faults. After infiltration, water is heated and reacts with rocks before rising to the surface. The existence of a potential heat source is petrologically and geophysically constrained to be an active shallow mafic-magma chamber, but its occurrence is not properly reflected in the composition of the collected warmed spring waters that are predominantly meteoric in origin. In conclusion, spring temperature and hydrochemistry alone may not always correctly reflect the deep geothermal potential of an area.
    Keywords: ddc:551
    Language: English
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  • 16
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    Känozoische Scher- und Dehnungstektonik im Pfälzerwald und mesozoische Vorbeanspruchungen (2015)
    Details
    Publication Date: 2022-07-27
    Description: Ausgewertet wurden eigene Messungen und tektonische Literaturangaben im Pfälzerwald und seinen Nachbargebieten. Neben normalen Störungen (Abschiebungen) sind vor allem Schräg- bzw. Horizontalbewegungen und die sie begleitenden Scherklüfte (Horizontalharnische) von Interesse. Am Rand des Oberrheingrabens (Haardtrand) kommen sogar Falten und (Schräg-) Aufschiebungen vor. Die Strukturen entstammen mehreren unterschiedlichen Deformationsereignissen zwischen dem Oberjura und heute (Abb. 8 und 26, Tab. 1). Besonders ausgeprägt ist die früheozäne Horizontaltektonik, die auf eine im Uhrzeigersinn rotierende Nord-Süd- Schubspannung zurückging (s1 = 161 bis 10° Streichen). Deren horizontalen Versätze erreichen 1,7 km. Die oberjurassische (s1 = 80 bis 95°) und die oberoligozäne (s1 = 35 bis 45°) Schertektonik ist deutlich, aber von geringerer Bedeutung. Die unterkretazischen, die mittelmiozänen und die subrezenten Scherbeanspruchungen waren relativ schwach. Wichtige Dehnungsereignisse fanden im Mitteljura und im Unteroligozän statt, zwischenzeitliche Extension im Zeitraum Oberplio-Pleisto-Holozän ist ebenfalls nachweisbar. Erzgebirgisch (WSW-ENE) streichende Sockelstrukturen – schon im Buntsandstein synsedimentär aktiv – wurden im Mitteljura ins Deckgebirge durchgepaust und nachfolgend verschiedentlich mobilisiert. Die herzynisch (Nordwest-Südost) streichenden Querstörungen bilden spätvariskische Transferstörungen (STOLLHOFEN 1998) im paläo - zoischen Unterlager ab. Sie sind im Oberjura ins Deckgebirge durchgepaust und sinistral scherend bewegt worden. Im Eozän wurden sie dextral invertiert und dann im Neogen dehnend überprägt. Ihre durchgepausten „Spuren“ formierten im Gebirgskörper vergleichsweise mobile und dadurch diagnostisch wichtige „Querstörungszonen“ unterschiedlicher Breite und Prägnanz.
    Description: The Tectonic development in the Palatine Forest (Pfälzerwald) with its adjacent regions was studied. Own structural measurements and tectonic data derived from regional literature have been interpreted. Not only normal faulting but especially remains of horizontal crustal motions were analysed. The latter comprised strikeslip faults and accompanying shear joints and planes with oblique resp. horizontal slip striations. At the edge of the Upper Rhine Graben even folds and (oblique) thrust faults occur in the covering rocks of late permian and early triassic age. All these structures can be assigned to several different paleostress fields, which occured between Upper Jurassic and today (fig. 8 and 26). Especially accentuated were the strike-slip movements of early eocene times. They were caused by North-South-directed compressional stresses, slowly rotating clockwise (s1 striking 161° to 10°). The horizontal fault throws reach 1.7 km. The shear tectonics of upper jurassic (s1: 80 to 95°) and upper oligocene age (s1: 35 to 45°) are noticeable, but of lower importance. The shear strains of lower cretaceous, middle miocene and subrecent age appear relatively weak. Important extensional phases happened in middle jurassic and in lower oligocene times. Interfering extension can also be traced in the Upper Pliocene–Pleistocene– Holocene time span. WSW-ENE striking structures of the basement, which had already been slightly active in lower Triassic times, were traced into the covering rocks of the (early) mesozoic Pfälzerwald-succession during middle Jurassic times and mobilized in different ways afterwards. Northwest-Southeast striking faults (so-called Querstörungen) are due to late variscan transfer faults (sensu STOLLHOFEN 1998) in the Paleozoic basement. They were traced into the covering rocks during Upper Jurassic while they have carried out sinistral shear motions. During early eocene times they were dextrally inver ted and then, during Neogene, extensionally overprinted. Their traced fractures formed tectonical mobile zones of different width and consiseness, which are of high diagnostic value.
    Description: 1. Einführung 1.1. Frühere Bearbeitungen 1.2. Datenbasis und methodische Grundlagen 2. Ererbte Strukturen 2.1. Erzgebirgisch streichende Strukturen 2.2. Nordwest-Südost-streichende Querstörungen 3. Eozäne Bewegungen 4. Oligozäne Bewegungen 5. Miozäne Bewegungen 6. Pliozäne bis subrezente Bewegungen 7. Reliktische Spuren mesozoischer Deformationen 8. Zeitlicher Ablauf der Deformationsgeschichte 9. Ausblick Schriften
    Description: research
    Keywords: ddc:551.8
    Language: German
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  • 17
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    Zum Häutungsverhalten einiger Trilobiten aus den Rupbach-Schiefern (spätes Oberemsium bis frühes Eifelium; Südwestliche Lahn-Mulde, Rhenoherzynikum) (2015)
    Details
    Publication Date: 2022-08-02
    Description: Mit Hilfe taphonomischer Befunde wird das Häutungsverhalten der Trilobiten Aulacopleura (Paraaulacopleura) n. sp., Cyphaspides n. sp., Chotecops sollei Struve, 1984 und Kettneraspis sp. aus dem Steinbruch “Gutenacker“ sowie Diademaproetus n. sp., Rhenocynproetus n. sp., Cyphaspis spp., Harpes sp., Acastoides n. sp., Destombesina n. sp., Barrandeops n. sp., Kettneraspis seiberti Basse, 2004, Leonaspis kleini Basse, 2004 und Koneprusia spp. von der Fundlokation “Heckelmanns Mühle” beschrieben. Beide Örtlichkeiten befinden sich im Rupbachtal, einer bekannten Fund - region für fossile Faunen aus dem Unter-/Mitteldevon-Grenzbereich. Innerhalb der verschiedenen Trilobitenarten sowie innerartlich wurden hierin eine Vielzahl verschiedener Häutungsmodi nachgewiesen. Der Nachweis infaunaler Häutungen erklärt womöglich das Vorkommen unzerstörter Häutungsensembles in den hiesigen Schlammströmen (Lahars). Diese endobenthischen Häutungen lassen sich an bestimmten Häutungskonfigurationen erkennen. Dazu wird neben den bisher bekannten Mustern hier zusätzlich der „Akkordeon-Effekt“ eingeführt. Den in einigen Odontopleuridae besonders ausgebildeten vorderen Randanhängen der Pleuren wird eine Verankerungsfunktion zur Unterstützung des Häutungsvorgangs zugeschrieben. Mit der „Anker-Strategie“ wird eine spezielle Häutungsweise bei Arten mit ankerförmigem Cephalon, wie z. B. Diademaproetus, für möglich gehalten und beschrieben. Innerhalb der Fauna von „Heckelmanns Mühle“ folgten Häutungen eher individuellen Rhythmen während in „Gutenacker“ Ansammlungen von Häutungsresten auf zeitlich koinzidierende Häutungsevents hinweisen. Der letztere Lebensraum wurde offenbar von manchen Arten speziell zur Häutung aufgesucht.
    Description: Abstract: Some molting-habits and related taphonomic implications of the trilobites Aulacopleura (Paraaulacopleura) n. sp., Cyphaspides n. sp., Chotecops sollei Struve, 1984 and Kettneraspis sp. from the “Gutenacker” quarry such as Diademaproetus n. sp., Rhenocynproetus n. sp., Cyphaspis spp., Harpes sp., Acastoides n. sp., Destombesina n. sp., Barrandeops n. sp., Kettneraspis seiberti Basse, 2004, Leonaspis kleini Basse, 2004 and Koneprusia spp. from the “Heckelmanns Mühle” fossil site are described. Both sites are situated in the Rupbach-valley in the south-eastern part of the Rhenish Massif, known for its numerous transitional Lower/Middle Devonian faunas. The variety of supposed molt procedures was high both extra- and intraspecifically. Infaunal molting occurred in some cases and may explain the occurrence of moult ensembles inside of some debris flows (lahars). Infaunal molting can be recognized by typical molting configurations as according to previous work and/or the “accordion-effect”, introduced herein. The function of specific anterior pleural spines, developed in some Odontopleuridae is interpreted as an auxiliary means for exuviation. An “anchor molt strategy” is considered possible and described for species with anchor-shaped cephala, especially Diademaproetus. In the “Heckelmanns Mühle”-fauna molting rather followed individual rhythms whereas in “Gutenacker” clustered molt remains are indicative of synchronized molting events. The latter site was apparently frequented especially for exuviation by some species.
    Description: research
    Keywords: ddc:562
    Language: German
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  • 18
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    Sedimentationsgeschichte der Oppenheim-Formation im Mainzer Becken und angrenzenden tertiären Senkungsgebieten (2015)
    Details
    Publication Date: 2022-09-29
    Description: Die Oppenheim-Formation ist im gesamten Mainzer und Hanauer Becken verbreitet und stellenweise auch in der Wetterau-Senke nachgewiesen. Sie ist gekennzeichnet durch fossilreiche, überwiegend stark karbonatische Sedimente. Verbreitet treten auch tonig-mergelige Zwischenlagen und an den Beckenrändern Quarzsand auf. Von der liegenden Hochheim-Formation ist die Oppenheim-Formation lithofaziell und biofaziell verschieden durch starke Reduktion der Algenkalkbildung und wesentlich arten-und individuenreichere marin-brackische Faunen, ebenso wie durch eine andersartige Landschneckenfauna. Im höchsten Teil der Oppenheim-Formation setzt Aussüßung ein, die eine faunistische Abtrennung zur hangenden Oberrad- Formation ermöglicht. Der Ablagerungsraum wird als Karbonatplattform im Randbereich des Oberrheingrabens gedeutet, wobei Schichtlücken und der litorallagunäre Charakter der Fauna variable, aber überwiegend sehr geringe Wassertiefen anzeigen. Die aquatischen Faunen sind mäßig divers, wobei Neuerscheinungen und Aussterben von Mollusken eine im ganzen Ablagerungsraum durchgehende Untergliederung in 7 Einheiten (Aquatische Molluskenzonen Vb bis VIe) ermöglichen. Ansätze zu entsprechenden Untergliederungen mittels Foraminiferen, Ostrakoden und Otolithen werden aufgezeigt. Nach Nannoplankton kann der Basisbereich der Oppen - heim-Formation in das jüngere Chattium (NP 25) eingestuft werden. Zuordnungen zur Mammalierstratigraphie sind derzeit nur begrenzt möglich, weil die präzise lithostratigraphische Herkunft der zahlreichen Funde größtenteils unbekannt ist; der obere Bereich der Oppenheim-Formation, wahrscheinlich aber auch tiefere Teile, gehören der Mammalierzone MN 1 an.
    Description: Abstract: The Oppenheim Formation is distributed throughout the entire Mainz and Hanau Basin and furthermore proved in parts of the Wetterau-Depression. It is characterized by fossiliferous, predominantly highly carbonatic sediments. Also marly clays are widely spread as intercalations and at the basin margins quartz sand become significant. The Oppenheim Formation is distinguished from the underlying Hochheim Formation by its litho-and biofacies: strong reduction of algal limestone formation and significantly richer (in diversity and frequency) marine-brackish faunas, as well as in a change of the land snail associations. In the uppermost part of the Oppenheim-Formation a reduction in salinity sets in, which facilitates a faunistic differentiation from the overlying Oberrad Formation. The sedimentation area is inter - preted as a carbonate platform at the margin of the Upper Rhine Graben; discontinuities and the littoral-lagoonal character of the faunas suggest predominantly shallow waters. The aquatic faunal associations are modestly diverse; immigrations and extinctions of mollusks enable a subdivision throughout the entire area of distribution in 7 units (Aquatic mollusk zones Vb to VIe). Indications of subdivisions by foraminifers, ostracods and otoliths are shown. The basal part of the Oppenheim Formation can be attributed to the late Chattian (Nannoplankton zone NP 25). Datings by mammal stratigraphy are currently only possible to a very limited extent, as the precise lithostratigraphic origin of many finds was not recorded; the upper part of the Oppenheim Formation, and probably also deeper parts, are in mammal zone MN1.
    Description: research
    Keywords: ddc:554.3
    Language: German
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  • 19
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    Vorkommen der lepospondylen Amphibien im saarpfälzischen Rotliegend (Karbon-/Perm-Grenzbereich; W-Deutschland) (2015)
    Details
    Publication Date: 2022-10-06
    Description: Um einen Überblick über das Vorkommen der Lepospondyli des saarpfälzischen Rotliegend zu erhalten, wurden in verschiedenen Seeablagerungen enthaltene Knochen untersucht. Aus der Remigiusberg-Formation stammen die ältesten nachgewiesenen Lepospondyli-Reste (Microsauria- und Lysorophia-Wirbel). Die etwas jüngere Altenglan-Formation beinhaltet Altenglanerpeton und die noch etwas jüngere Meisenheim-Formation Batropetes. Hinweise auf Lepospondyli fehlen von der Donnersberg- bis Wadern-Formation – außer im Dornbach-See mit Nectridea, Lyso - rophia und Aïstopoda.
    Description: Abstract: For gaining an overview of the incidence of lepospondyls in the Saar- Nahe-Basin, bones preserved in sediments of different lakes were examined. The oldest evident remains of lepospondyls (vertebrae of Microsauria and Lysorophia) come from the Remigiusberg Formation. The younger Altenglan Formation contains Alten glanerpeton and the even younger Meisenheim Formation contains Batropetes. Indications of lepospondyls are missing from Donnersberg Formation until Wadern Formation – except for the Dornbach-Lake containing Nectridea, Lysorophia and Aïstopoda.
    Description: research
    Keywords: ddc:567.8
    Language: German
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  • 20
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    Steckbriefe Moorsubstrate, 2. Auflage (2015)
    Hochschule für nachhaltige Entwicklung Eberswalde (Hrsg.)
    Details
    Publication Date: 2022-06-14
    Description: Moore sind faszinierende Lebensräume, die überaus bemerkenswerte Funktionen im Wirkungsgefüge einer Landschaft erfüllen. Der Erhaltungszustand der Moore in Deutschland ist jedoch nach wie vor besorgniserregend und führte zu verstärkten Aktivitäten in den letzten Jahren zum Schutz und Erhalt dieser gefährdeten Ökosysteme. Eine Grundvoraussetzung für erfolgreiche Renaturierungen ist die oft vernachlässigte Kenntnis über den unterirdischen Schichtenaufbau eines Moores. Dieser Schichtenaufbau kann aus verschiedenen, teilweise in einem charakteristischen Wechsel vorliegenden Moorsubstraten (vor allem Torfe und Mudden) bestehen. Die für eine effektive Managementplanung so entscheidende korrekte Ansprache dieser Moorsubstrate ist allerdings bislang nur spezialisierten Fachleuten möglich. Daher ist es das Ziel der „Steckbriefe Moorsubstrate“, durch eine umfassende und fachlich fundierte Darstellung mit detaillierten Beschreibungen und zahlreichen aussagekräftigen Fotografien die Substratansprache erheblich zu erleichtern und einem breiten Anwenderkreis zu ermöglichen. Die Sammelmappe „Steckbriefe Moorsubstrate“ gliedert sich in zwei Teile: Den Kern bilden die als Geländeunterlagen konzipierten 24 eigentlichen Steckbriefe der häufigsten Moorsubstrate sowie ein darauf abgestimmter Bestimmungsschlüssel und eine Übersicht für die Ableitung von Zersetzungsgraden und Konsistenzstufen. Der Einführungsteil liefert zahlreiche Informationen rund um die Themen Moor, Moortypen, Moorsubstrate und Moorböden. Weiterhin finden Sie hier Hinweise zum Vorgehen bei der Aufnahme eines Moorprofils sowie zur Ableitung des Moortyps anhand des erfassten Schichtenaufbaus.
    Description: http://www.mire-substrates.com/
    Description: research
    Keywords: ddc:553.21
    Language: German
    Type: doc-type:book , publishedVersion
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  • 21
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    Die Verwendung heimischer Naturwerksteine als Beitrag zur regionalen Identität von Rheinhessen (2015)
    Details
    Publication Date: 2022-08-09
    Description: Im Jahr 2016 wird an die 200-jährige Wiederkehr der Inbesitznahme des neu gebildeten Landesteils „Rheinhessen“ durch das Großherzogtum Hessen erinnert. Obwohl die Eigenständigkeit von Rheinhessen als selbständiger politischer Verwaltungs einheit schon wieder Geschichte ist, beschäftigen sich im Vorfeld dieses Jubiläums zahlreiche Gremien, Öffentliche Amtsträger und Printmedien mit der Frage nach einer regionalen Identität dieser Region. Aus geologischer Sicht ist dabei zunächst die Frage nach dem Werden und einheitlichen geologischen Aufbau der rheinhessischen Landschaft zu diskutieren und wie sich die Landnutzungsformen durch die Menschen im Freiraum der Landschaft und in den Gemeinden widerspiegeln. Bei der Errichtung von zahlreichen, häufig denkmal geschützten Bauwerken spielt die Verwendung einheimischer Gesteine wie Kalksteine, Sandsteine, Andesite und Rhyolithe in unverwechselbarer regionaltypischer Ausbildung eine wichtige Rolle. Aus örtlich vorkommendem Löss, Mergeln und Tonen gebrannte Mauer- und Dachziegel tragen in den historischen Ortskernen rheinhessischer Gemeinden ebenfalls dazu bei, eine sichtbare regionale Identität zu begründen.
    Description: Abstract: In 2016 people will look back to the 200th anniversary of the appropriation of “Rheinhessen” as a newly formed part of the grand duchy of Hessen. Although the status of Rheinhessen as an independent political administrative unit is already history, numerous committees, officials and printed media will contribute to the question of the regional identity of Rheinhessen. From a geological point of view it is necessary to discuss first of all the origin and the uniform geological structure of the landscape. Furthermore it is essential to clarify how the form of land use by men is reflected in the open land as well as in the villages and towns. The use of domestic rocks plays a dominant role in the construction of versatile, frequently historic landmarked buildings, using limestones, sandstones, andesites and rhyolithes in an distinctive typical formation. Bricks and roof tiles made of local loess, marl and clay contribute well in forming a regional identity in the historic middle of Rheinhessen villages and towns.
    Description: 1. Einleitung 2. Entstehung und Abgrenzung von Rheinhessen 3. Merkmale der Kulturlandschaft 4. Typisch rheinhessisch – Auf der Suche nach einer Identität 5. Charakteristik der Geologie von Rheinhessen 6. Die Naturwerksteine und ihre Bauwerke 6.1. Kalkstein, Mergel 6.2. Sandstein 6.3. Rhyolith („Quarzporphyr“) 6.4. Andesit 6.5. Quarzit, Grauwacke, Schiefer 6.6. Kombinationen rheinhessischer Naturwerksteine und Ziegel Schriften
    Description: research
    Keywords: ddc:690 ; ddc:550
    Language: German
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  • 22
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    Torfmooskultivierung: Moorschutz durch Moornutzung (2015)
    Details
    Publication Date: 2024-02-28
    Description: Abstract: Slightly humified Sphagnum peat is (next to strongly humified Sphagnum peat) the most important raw material for the production of horticultural substrates. The global annual consumption amounts to 30 million m³ of which 3 million m³ are consumed in Germany. This fossil raw material is excavated from peatlands. As its availability is strongly decreasing in Germany, it is increasingly imported from the Baltic countries. Alternative raw materials with comparable properties are not yet available in sufficient amounts. Peat moss (Sphagnum) biomass has similar physical and chemical properties as slightly humified peat and its use as a raw material for growing media in professional modern horticulture has been tested successfully. The cultivation of peat moss biomass (Sphagnum farming) on rewetted bogs provides several advantages. Rewetting halts the further degradation of the peat body and reduces the emission of greenhouse gases. Sphagnum farming ensures a lasting supply of high quality renewable raw material. Moreover, it supports regional economies and the conservation and protection of biodiversity, water resources and peat archives. Over the past decade, extensive studies on the cultivation of peat moss have been carried out by the University of Greifswald in cooperation with various research and industrial partners. Field tests have convincingly demonstrated the feasibility of large scale Sphagnum farming on degraded bog peat sites.
    Description: Zusammenfassung: Weißtorf (schwach zersetzter Hochmoortorf) ist, neben Schwarztorf (stark zersetzter Hochmoortorf), der wichtigste Substratrohstoff und Produktionsgrundlage im modernen Gartenbau. Weltweit werden dafür jährlich 30 Mio. m³ Weißtorf, davon 3 Mio. m³ in Deutschland verbraucht. Dieser fossile Rohstoff wird aus Mooren abgebaut, und seine Verfügbarkeit sinkt in Deutschland stark, so dass der Bedarf zunehmend durch Torfimporte vorwiegend aus den baltischen Ländern, gedeckt werden muss. Alternative Rohstoffe, die die Substratqualitäten von Weißtorf aufweisen und in ausreichender Menge verfügbar sind, fehlen bislang. In pflanzenbaulichen Tests wurde gezeigt, dass Torfmoos-Biomasse gleiche Substrateigenschaften wie Weißtorf aufweist und als Substratrohstoff geeignet ist. Torfmooskultivierung bietet durch nasse Moorbewirtschaftung einen Erhalt des Torfkörpers, die dauerhafte Versorgung der Torf- und Humuswirtschaft mit einem nachwachsenden Rohstoff in Verbindung mit regionaler Wertschöpfung, die Verringerung der Treibhausgasemissionen im Vergleich zur herkömmlichen Nutzung sowie weitere Vorteile, wie Arten-, Gewässer- und Archivschutz. Die Universität Greifswald führt, gemeinsam mit zahlreichen Projektpartnern, seit mehr als 10 Jahren Untersuchungen zur Kultivierung von Torfmoosen (Sphagnum) durch. In Feldversuchen werden dabei die Machbarkeit und die Möglichkeiten einer großflächigen Umsetzung auf degradierten Hochmoor standorten demonstriert.
    Description: DFG, SUB Göttingen, DGMT
    Description: research
    Keywords: ddc:553.21 ; ddc:630.914 ; Moor ; mire ; peatland ; land-use ; Sphagnum ; substrate ; Wiedervernässung ; Paludikultur
    Language: German
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  • 23
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    Logistics Needs for Potential Deep Space Mission Scenarios Post Asteroid Crewed Mission (2015)
    In:  CASI
    Details
    Publication Date: 2014-12-24
    Description: A deep-space mission has been proposed to identify and redirect an asteroid to a distant retrograde orbit around the moon, and explore it by sending a crew using the Space Launch System and the Orion spacecraft. The Asteroid Redirect Crewed Mission (ARCM), which represents the third segment of the Asteroid Redirect Mission (ARM), could be performed on EM-3 or EM-4 depending on asteroid return date. Recent NASA studies have raised questions on how we could progress from current Human Space Flight (HSF) efforts to longer term human exploration of Mars. This paper will describe the benefits of execution of the ARM as the initial stepping stone towards Mars exploration, and how the capabilities required to send humans to Mars could be built upon those developed for the asteroid mission. A series of potential interim missions aimed at developing such capabilities will be described, and the feasibility of such mission manifest will be discussed. Options for the asteroid crewed mission will also be addressed, including crew size and mission duration.
    Keywords: Space Sciences (General)
    Type: JSC-CN-31463 , 2015 IEEE Aerospace Conference; 7-14 Mar. 2015; Big Sky, MT; United States
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    Do Responses to Different Anthropogenic Forcings Add Linearly in Climate Models? (2015)
    In:  CASI
    Details
    Publication Date: 2016-11-04
    Description: Many detection and attribution and pattern scaling studies assume that the global climate response to multiple forcings is additive: that the response over the historical period is statistically indistinguishable from the sum of the responses to individual forcings. Here, we use the NASA Goddard Institute for Space Studies (GISS) and National Center for Atmospheric Research Community Climate System Model (CCSM) simulations from the CMIP5 archive to test this assumption for multi-year trends in global-average, annual-average temperature and precipitation at multiple timescales. We find that responses in models forced by pre-computed aerosol and ozone concentrations are generally additive across forcings; however, we demonstrate that there are significant nonlinearities in precipitation responses to dierent forcings in a configuration of the GISS model that interactively computes these concentrations from precursor emissions. We attribute these to dierences in ozone forcing arising from interactions between forcing agents. Our results suggest that attribution to specific forcings may be complicated in a model with fully interactive chemistry and may provide motivation for other modeling groups to conduct further single-forcing experiments.
    Keywords: Meteorology and Climatology
    Type: GSFC-E-DAA-TN26978 , Environmental Research Letters (e-ISSN 1748-9326); Volume 10; No. 10; 104010
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    NASA Engine Icing Research Overview: Aeronautics Evaluation and Test Capabilities (AETC) Project (2015)
    In:  CASI
    Details
    Publication Date: 2016-12-20
    Description: The occurrence of ice accretion within commercial high bypass aircraft turbine engines has been reported by airlines under certain atmospheric conditions. Engine anomalies have taken place at high altitudes that have been attributed to ice crystal ingestion by the engine. The ice crystals can result in degraded engine performance, loss of thrust control, compressor surge or stall, and flameout of the combustor. The Aviation Safety Program at NASA has taken on the technical challenge of a turbofan engine icing caused by ice crystals which can exist in high altitude convective clouds. The NASA engine icing project consists of an integrated approach with four concurrent and ongoing research elements, each of which feeds critical information to the next element. The project objective is to gain understanding of high altitude ice crystals by developing knowledge bases and test facilities for testing full engines and engine components. The first element is to utilize a highly instrumented aircraft to characterize the high altitude convective cloud environment. The second element is the enhancement of the Propulsion Systems Laboratory altitude test facility for gas turbine engines to include the addition of an ice crystal cloud. The third element is basic research of the fundamental physics associated with ice crystal ice accretion. The fourth and final element is the development of computational tools with the goal of simulating the effects of ice crystal ingestion on compressor and gas turbine engine performance. The NASA goal is to provide knowledge to the engine and aircraft manufacturing communities to help mitigate, or eliminate turbofan engine interruptions, engine damage, and failures due to ice crystal ingestion.
    Keywords: Aircraft Propulsion and Power
    Type: GRC-E-DAA-TN20926 , Department of Aerospace Engineering and Engineering Mechanics Graduate Seminar; 4 May 2015; Cincinnati, OH; United States
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    NASA Capabilities That Could Impact Terrestrial Smart Grids of the Future (2015)
    In:  CASI
    Details
    Publication Date: 2015-12-11
    Description: Incremental steps to steadily build, test, refine, and qualify capabilities that lead to affordable flight elements and a deep space capability. Potential Deep Space Vehicle Power system characteristics: power 10 kilowatts average; two independent power channels with multi-level cross-strapping; solar array power 24 plus kilowatts; multi-junction arrays; lithium Ion battery storage 200 plus ampere-hours; sized for deep space or low lunar orbit operation; distribution120 volts secondary (SAE AS 5698); 2 kilowatt power transfer between vehicles.
    Keywords: Lunar and Planetary Science and Exploration; Electronics and Electrical Engineering
    Type: GRC-E-DAA-TN21535 , Electro Expo; 11-12 Mar. 2015; Cleveland, OH; United States
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    NASA'S Space Launch System: Opening Opportunities for Mission Design (2015)
    In:  CASI
    Details
    Publication Date: 2015-12-11
    Description: Designed to meet the stringent requirements of human exploration missions into deep space and to Mars, NASA's Space Launch System (SLS) vehicle represents a unique new launch capability opening new opportunities for mission design. While SLS's super-heavy launch vehicle predecessor, the Saturn V, was used for only two types of missions - launching Apollo spacecraft to the moon and lofting the Skylab space station into Earth orbit - NASA is working to identify new ways to use SLS to enable new missions or mission profiles. In its initial Block 1 configuration, capable of launching 70 metric tons (t) to low Earth orbit (LEO), SLS is capable of not only propelling the Orion crew vehicle into cislunar space, but also delivering small satellites to deep space destinations. With a 5-meter (m) fairing consistent with contemporary Evolved Expendable Launch Vehicles (EELVs), the Block 1 configuration can also deliver science payloads to high-characteristic-energy (C3) trajectories to the outer solar system. With the addition of an upper stage, the Block 1B configuration of SLS will be able to deliver 105 t to LEO and enable more ambitious human missions into the proving ground of space. This configuration offers opportunities for launching co-manifested payloads with the Orion crew vehicle, and a new class of secondary payloads, larger than today's cubesats. The evolved configurations of SLS, including both Block 1B and the 130 t Block 2, also offer the capability to carry 8.4- or 10-m payload fairings, larger than any contemporary launch vehicle. With unmatched mass-lift capability, payload volume, and C3, SLS not only enables spacecraft or mission designs currently impossible with contemporary EELVs, it also offers enhancing benefits, such as reduced risk and operational costs associated with shorter transit time to destination and reduced risk and complexity associated with launching large systems either monolithically or in fewer components. As this paper will demonstrate, SLS is making strong progress toward first launch, and represents a unique new capability for spaceflight, and an opportunity to reinvent space by developing out-of-the-box missions and mission designs unlike any flown before.
    Keywords: Launch Vehicles and Launch Operations; Lunar and Planetary Science and Exploration
    Type: M15-4723 , Reinventing Space Conference (RIspace 2015); 9-13 Nov. 2015; Oxford; United Kingdom
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    In-Orbit Servicing: The Master Enabler (2015)
    In:  CASI
    Details
    Publication Date: 2016-01-23
    Description: Some of the most noteworthy missions in space exploration have occurred in the last two decades and owe their success to on-orbit servicing. The tremendously successful Hubble Space Telescope repair and upgrade missions, as well as the completed assembly of the International Space Station (ISS) and its full utilization, lead us to the next chapter and set of challenges. These include fully exploiting the many space systems already launched, assembling large structures in situ thereby enabling new scientific discoveries, and providing systems that reliably and cost-effectively support the next steps in space exploration. In-orbit servicing is a tool--a tool that can serve as the master enabler to create space architectures that would otherwise be unattainable. This paper will survey how NASA's satellite-servicing technology development efforts are being applied to the planning and execution of two such ambitious missions, specifically asteroid capture and the in-space assembly of a very large life-finding telescope.
    Keywords: Astronautics (General); Lunar and Planetary Science and Exploration
    Type: GSFC-E-DAA-TN26171-2 , Space 2015; 31 Aug. - 1 Sep. 2015; Pasadena, CA; United States
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    The "Master Enabler" - In-Orbit Servicing (2015)
    In:  CASI
    Details
    Publication Date: 2015-12-01
    Description: Some of the most noteworthy missions in space exploration have occurred in the last two decades and owe their success to on-orbit servicing. The tremendously successful Hubble Space Telescope repair and upgrade missions, as well as the completed assembly of the International Space Station (ISS) and its full utilization, lead us to the next chapter and set of challenges. These include fully exploiting the many space systems already launched, assembling large structures in situ thereby enabling new scientific discoveries, and providing systems that reliably and cost-effectively support the next steps in space exploration. In-orbit servicing is a tool-a tool that can serve as the master enabler to create space architectures that would otherwise be unattainable. This paper will survey how NASA's satellite-servicing technology development efforts are being applied to the planning and execution of two such ambitious missions, specifically asteroid capture and the in-space assembly of a very large life-finding telescope.
    Keywords: Lunar and Planetary Science and Exploration; Astronautics (General)
    Type: GSFC-E-DAA-TN26171-1 , Space 2015; 31 Aug. - 2 Sep. 2015; Pasadena, CA; United States
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    Advances in Robotic Servicing Technology Development (2015)
    In:  CASI
    Details
    Publication Date: 2015-11-07
    Description: NASA's Satellite Servicing Capabilities Office (SSCO) has matured robotic and automation technologies applicable to in-space robotic servicing and robotic exploration over the last six years. This paper presents the progress of technology development activities at the Goddard Space Flight Center Servicing Technology Center and on the ISS, with an emphasis on those occurring in the past year. Highlighted advancements are design reference mission analysis for servicing in low Earth orbit (LEO) and asteroid redirection; delivery of the engineering development unit of the NASA Servicing Arm; an update on International Space Station Robotic Refueling Mission; and status of a comprehensive ground-based space robot technology demonstration expanding in-space robotic servicing capabilities beginning fall 2015.
    Keywords: Cybernetics, Artificial Intelligence and Robotics
    Type: GSFC-E-DAA-TN23498 , AIAA Space 2015; 31 Aug. - 2 Sep. 2015; Pasedena, CA; United States
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    Automation in Unmanned Aerial Vehicles (UAS) (2015)
    In:  CASI
    Details
    Publication Date: 2019-03-05
    Description: No abstract available
    Keywords: Air Transportation and Safety
    Type: ARC-E-DAA-TN21732 , Transitioning to Autonomy: Changes in the Role of Humans in Air Transportation; 10-12 Mar. 2015; Moffett Field, CA; United States
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    Challenges of In Space Robotic Servicing (2015)
    In:  Other Sources
    Details
    Publication Date: 2017-10-04
    Description: As future space missions extend beyond the friendly confines of low earth orbit, robots are becoming an increasingly vital component on flight manifests. While the main focus to-date has been on satellite servicing due to its high commercial potential, robots are also being considered for orbital debris removal, space construction, and asteroid sample retrieval. The robotic technologies and automation required to carry out these missions represent a significant advancement beyond the manipulation technology used previously on the Space Shuttle, the International Space Station, and planetary rovers. While higher demands are being driven by the more ambitious nature of the tasks, the handling of uncooperative targets such as satellites and asteroids, present a greater challenge.
    Keywords: Cybernetics, Artificial Intelligence and Robotics; Astronautics (General)
    Type: GSFC-E-DAA-TN24383 , IEEE Conference on Robotics and Automation (ICRA 2015); 26-30 May 2015; Seattle, WA; United States
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    Bio-Inspired Somatic Robots (2015)
    In:  CASI
    Details
    Publication Date: 2017-02-18
    Description: No abstract available
    Keywords: Aerospace Medicine; Lunar and Planetary Science and Exploration; Cybernetics, Artificial Intelligence and Robotics
    Type: ARC-E-DAA-TN24983 , Annual Multi-Use Technology Symposium; 9 Jul. 2015; Ridgecrest, CA; United States
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    Reinvigorating the Entrepreneurial Spirit of NASA (2015)
    In:  CASI
    Details
    Publication Date: 2017-06-08
    Description: This talk gives a rundown of a career in servicing and looks to the future of servicing and scientific missions working together. The talk attempts to reinvigorate the old NASA entrepreneurial spirit.
    Keywords: Mechanical Engineering; Cybernetics, Artificial Intelligence and Robotics
    Type: GSFC-E-DAA-TN26323 , Maniac Talk; 28 Aug. 2015; Greenbelt, MD; United States
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    Jovian plasma modeling for mission design (2015)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: The purpose of this report is to address uncertainties in the plasma models at Jupiter responsible for surface charging and to update the jovian plasma models using the most recent data available. The updated plasma environment models were then used to evaluate two proposed Europa mission designs for spacecraft charging effects using the Nascap-2k code. The original Divine/Garrett jovian plasma model (or "DG1", T. N. Divine and H. B. Garrett, "Charged particle distributions in Jupiter's magnetosphere," J. Geophys. Res., vol. 88, pp. 6889-6903,1983) has not been updated in 30 years, and there are known errors in the model. As an example, the cold ion plasma temperatures between approx.5 and 10 Jupiter radii (Rj) were found by the experimenters who originally published the data to have been underestimated by approx.2 shortly after publication of the original DG1 model. As knowledge of the plasma environment is critical to any evaluation of the surface charging at Jupiter, the original DG1 model needed to be updated to correct for this and other changes in our interpretation of the data so that charging levels could beproperly estimated using the Nascap-2k charging code. As an additional task, the Nascap-2k spacecraft charging tool has been adapted to incorporate the so-called Kappa plasma distribution function--an important component of the plasma model necessary to compute the particle fluxes between approx.5 keV and 100 keV (at the outset of this study,Nascap-2k did not directly incorporate this common representation of the plasma thus limiting the accuracy of our charging estimates). The updating of the DG1 model and its integration into the Nascap-2k design tool means that charging concerns can now be more efficiently evaluated and mitigated. (We note that, given the subsequent decision by the Europa project to utilize solar arrays for its baseline design, surface charging effects have becomeeven more of an issue for its mission design). The modifications and results of those modifications to the DG1 model to produce the new DG2 model presented here and the steps taken to integrate the DG2 predictions into Nascap-2k are described in this report.
    Keywords: Plasma Physics
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    Inflight Characterization of the Cassini Spacecraft Propellant Slosh and Structural Frequencies (2015)
    In:  Other Sources
    Details
    Publication Date: 2018-06-11
    Description: While there has been extensive theoretical and analytical research regarding the characterization of spacecraft propellant slosh and structural frequencies, there have been limited studies to compare the analytical predictions with measured flight data. This paper uses flight telemetry from the Cassini spacecraft to get estimates of high-g propellant slosh frequencies and the magnetometer boom frequency characteristics, and compares these values with those predicted by theoretical works. Most Cassini attitude control data are available at a telemetry frequency of 0.5 Hz. Moreover, liquid sloshing is attenuated by propellant management device and attitude controllers. Identification of slosh and structural frequency are made on a best-effort basis. This paper reviews the analytical approaches that were used to predict the Cassini propellant slosh frequencies. The predicted frequencies are then compared with those estimated using telemetry from selected Cassini burns where propellant sloshing was observed (such as the Saturn Orbit Insertion burn). Determination of the magnetometer boom structural frequency is also discussed.
    Keywords: Spacecraft Design, Testing and Performance; Propellants and Fuels
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    Electronegative Gas Thruster (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The project is an international collaboration and academic partnership to mature an innovative electric propulsion thruster concept to Technology Research Level-3 (TRL-3) through direct thrust measurement. The project includes application assessment of the technology ranging from small spacecraft to high power. The Plasma propulsion with Electronegative GASES(PEGASES) basic proof of concept has been matured to TRL-2 by Ane Aanesland of Laboratoire de Physique des Plasma at Ecole Polytechnique. The concept has advantages through eliminating the neutralizer requirement and should yield longer life and lower cost over conventional gridded ion engines. The objective of this research is to validate the proof of concept through the first direct thrust measurements and mature the concept to TRL-3.
    Keywords: Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 132-133; NASA/TM-2015-218204
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    Interplanetary Radiation and Fault Tolerant Mini-Star Tracker System (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Charles Stark Draper Laboratory, Inc. is partnering with the NASA Marshall Space Flight Center (MSFC) Engineering Directorate's Avionics Design Division and Flight Mechanics & Analysis Division to develop and test a prototype small, low-weight, low-power, radiation-hardened, fault-tolerant mini-star tracker (fig. 1). The project is expected to enable Draper Laboratory and its small business partner, L-1 Standards and Technologies, Inc., to develop a new guidance, navigation, and control sensor product for the growing small sat technology market. The project also addresses MSFC's need for sophisticated small sat technologies to support a variety of science missions in Earth orbit and beyond. The prototype star tracker will be tested on the night sky on MSFC's Automated Lunar and Meteor Observatory (ALAMO) telescope. The specific goal of the project is to address the need for a compact, low size, weight, and power, yet radiation hardened and fault tolerant star tracker system that can be used as a stand-alone attitude determination system or incorporated into a complete attitude determination and control system for emerging interplanetary and operational CubeSat and small sat missions.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 174-175; NASA/TM-2015-218204
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    NanoLaunch (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: NASA's NanoLaunch effort will provide the framework to mature both Earth-to-orbit and on-orbit propulsion and avionics technologies while also providing affordable, dedicated access to low-Earth orbit for CubeSat-class payloads. The project will also serve as an early career personnel training opportunity with mentors to gain hands-on project experience.
    Keywords: Spacecraft Instrumentation and Astrionics; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 164-165; NASA/TM-2015-218204
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    Iodine Satellite (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This project is a collaborative effort to mature an iodine propulsion system while reducing risk and increasing fidelity of a technology demonstration mission concept. 1 The FY 2014 tasks include investments leveraged throughout NASA, from multiple mission directorates, as a partnership with NASA Glenn Research Center (GRC), a NASA Marshall Space Flight Center (MSFC) Technology Investment Project, and an Air Force partnership. Propulsion technology is often a critical enabling technology for space missions. NASA is investing in technologies to enable high value missions with very small and low-cost spacecraft, even CubeSats. However, these small spacecraft currently lack any appreciable propulsion capability. CubeSats are typically deployed and drift without any ability to transfer to higher value orbits, perform orbit maintenance, or deorbit. However, the iodine Hall system can allow the spacecraft to transfer into a higher value science orbit. The iodine satellite (iSAT) will be able to achieve a (Delta)V of 〉500 m/s with 〈1 kg of solid iodine propellant, which can be stored in an unpressurized benign state prior to launch. The iSAT propulsion system consists of the 200 W Hall thruster, solid iodine propellant tank, a power processing unit, and the necessary valves and tubing to route the iodine vapor. The propulsion system is led by GRC, with critical hardware provided by the Busek Co. The propellant tank begins with solid iodine unpressurized on the ground and in-flight before operations, which is then heated via tank heaters to a temperature at which solid iodine sublimates to iodine vapor. The vapor is then routed through tubing and custom valves to control mass flow to the thruster and cathode assembly. 2 The thruster then ionizes the vapor and accelerates it via magnetic and electrostatic fields, resulting in thrust with a specific impulse 〉1,300 s. The iSAT spacecraft, illustrated in figure 1, is currently a 12U CubeSat. The spacecraft chassis will be constructed from aluminum with a finish to prevent iodine-driven corrosion. The iSAT spacecraft includes full three-axis control using wheels, magnetic torque rods, inertial management unit, and a suite of sensors and optics. The spacecraft will leverage heat generated by spacecraft components and radiators for a passive thermal control system.
    Keywords: Spacecraft Design, Testing and Performance; Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 162-163; NASA/TM-2015-218204
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    Printing Outside the Box: Additive Manufacturing Processes for Fabrication of Large Aerospace Structures (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: To achieve NASA's mission of space exploration, innovative manufacturing processes are being applied to the fabrication of propulsion elements. Liquid rocket engines (LREs) are comprised of a thrust chamber and nozzle extension as illustrated in figure 1 for the J2X upper stage engine. Development of the J2X engine, designed for the Ares I launch vehicle, is currently being incorporated on the Space Launch System. A nozzle extension is attached to the combustion chamber to obtain the expansion ratio needed to increase specific impulse. If the nozzle extension could be printed as one piece using free-form additive manufacturing (AM) processes, rather than the current method of forming welded parts, a considerable time savings could be realized. Not only would this provide a more homogenous microstructure than a welded structure, but could also greatly shorten the overall fabrication time. The main objective of this study is to fabricate test specimens using a pulsed arc source and solid wire as shown in figure 2. The mechanical properties of these specimens will be compared with those fabricated using the powder bed, selective laser melting technology at NASA Marshall Space Flight Center. As printed components become larger, maintaining a constant temperature during the build process becomes critical. This predictive capability will require modeling of the moving heat source as illustrated in figure 3. Predictive understanding of the heat profile will allow a constant temperature to be maintained as a function of height from substrate while printing complex shapes. In addition, to avoid slumping, this will also allow better control of the microstructural development and hence the properties. Figure 4 shows a preliminary comparison of the mechanical properties obtained.
    Keywords: Astronautics (General); Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 172-173; NASA/TM-2015-218204
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    Improving Interlaminar Shear Strength (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: To achieve NASA's mission of space exploration, innovative manufacturing processes are being applied to the fabrication of complex propulsion elements.1 Use of fiber-reinforced, polymeric composite tanks are known to reduce weight while increasing performance of propulsion vehicles. Maximizing the performance of these materials is needed to reduce the hardware weight to result in increased performance in support of NASA's missions. NASA has partnered with the Mississippi State University (MSU) to utilize a unique scalable approach of locally improving the critical properties needed for composite structures. MSU is responsible for the primary development of the concept with material and engineering support provided by NASA. The all-composite tank shown in figure 1 is fabricated using a prepreg system of IM7 carbon fiber/CYCOM 5320-1 epoxy resin. This is a resin system developed for out-of-autoclave applications. This new technology is needed to support the fabrication of large, all composite structures and is currently being evaluated on a joint project with Boeing for the Space Launch System (SLS) program. In initial efforts to form an all composite pressure vessel using this prepreg system, a 60% decrease in properties was observed in scarf joint regions. Inspection of these areas identified interlaminar failure in the adjacent laminated structure as the main failure mechanism. This project seeks to improve the interlaminar shear strength (ILSS) within the prepreg layup by locally modifying the interply region shown in figure 2.2
    Keywords: Launch Vehicles and Launch Operations; Composite Materials
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 170-171; NASA/TM-2015-218204
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    Low Noise Camera for Suborbital Science Applications (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Low-cost, commercial-off-the-shelf- (COTS-) based science cameras are intended for lab use only and are not suitable for flight deployment as they are difficult to ruggedize and repackage into instruments. Also, COTS implementation may not be suitable since mission science objectives are tied to specific measurement requirements, and often require performance beyond that required by the commercial market. Custom camera development for each application is cost prohibitive for the International Space Station (ISS) or midrange science payloads due to nonrecurring expenses (~$2,000 K) for ground-up camera electronics design. While each new science mission has a different suite of requirements for camera performance (detector noise, speed of image acquisition, charge-coupled device (CCD) size, operation temperature, packaging, etc.), the analog-to-digital conversion, power supply, and communications can be standardized to accommodate many different applications. The low noise camera for suborbital applications is a rugged standard camera platform that can accommodate a range of detector types and science requirements for use in inexpensive to mid range payloads supporting Earth science, solar physics, robotic vision, or astronomy experiments. Cameras developed on this platform have demonstrated the performance found in custom flight cameras at a price per camera more than an order of magnitude lower.
    Keywords: Instrumentation and Photography
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 166-167; NASA/TM-2015-218204
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    Grazing Incidence Optics Technology (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This project is to demonstrate the capability to directly fabricate lightweight, high-resolution, grazing-incidence x-ray optics using a commercially available robotic polishing machine. Typical x-ray optics production at NASA Marshall Space Flight Center (MSFC) uses a replication process in which metal mirrors are electroformed on to figured and polished mandrels from which they are later removed. The attraction of this process is that multiple copies can be made from a single master. The drawback is that the replication process limits the angular resolution that can be attained. By directly fabricating each shell, errors inherent in the replication process are removed. The principal challenge now becomes how to support the mirror shell during all aspects of fabrication, including the necessary metrology to converge on the required mirror performance specifications. This program makes use of a Zeeko seven-axis computer-controlled polishing machine (see fig. 1) and supporting fabrication, metrology, and test equipment at MSFC. The overall development plan calls for proof-of-concept demonstration with relatively thick mirror shells (5-6 mm, fig. 2) which are straightforward to support and then a transition to much thinner shells (2-3 mm), which are an order of magnitude thinner than those used for Chandra. Both glass and metal substrates are being investigated. Currently, a thick glass shell is being figured. This has enabled experience to be gained with programming and operating the polishing machine without worrying about shell distortions or breakage. It has also allowed time for more complex support mechanisms for figuring/ polishing and metrology to be designed for the more challenging thinner shells. These are now in fabrication. Figure 1: Zeeko polishing machine.
    Keywords: Optics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 158-159; NASA/TM-2015-218204
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    Formation Flying for Satellites and Unmanned Aerial Vehicles (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The shrinking size of satellites and unmanned aerial vehicles (UAVs) is enabling lower cost missions. As sensors and electronics continue to downsize, the next step is multiple vehicles providing different perspectives or variations for more precise measurements. While flying a single satellite or UAV autonomously is a challenge, flying multiple vehicles in a precise formation is even more challenging. The goal of this project is to develop a scalable mesh network between vehicles (satellites or UAVs) to share real-time position data and maintain formations autonomously. Newly available low-cost, commercial off-the-shelf credit card size computers will be used as the basis for this network. Mesh networking techniques will be used to provide redundant links and a flexible network. The Small Projects Rapid Integration and Test Environment Lab will be used to simulate formation flying of satellites. UAVs built by the Aero-M team will be used to demonstrate the formation flying in the West Test Area. The ability to test in flight on NASA-owned UAVs allows this technology to achieve a high Technology Readiness Level (TRL) (TRL-4 for satellites and TRL-7 for UAVs). The low cost of small UAVs and the availability of a large test range (West Test Area) dramatically reduces the expense of testing. The end goal is for this technology to be ready to use on any multiple satellite or UAV mission.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking; Computer Systems
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 150-151; NASA/TM-2015-218204
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    Low-Energy Microfocus X-Ray Source for Enhanced Testing Capability in the Stray Light Facility (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Research toward high-resolution, soft x-ray optics (mirrors and gratings) necessary for the next generation large x-ray observatories requires x-ray testing using a low-energy x-ray source with fine angular size (〈1 arcsecond). To accommodate this somewhat demanding requirement, NASA Marshall Space Flight Center (MSFC) has procured a custom, windowless low-energy microfocus (approximately 0.1 mm spot) x-ray source from TruFocus Corporation that mates directly to the Stray Light Facility (SLF). MSFC X-ray Astronomy team members are internationally recognized for their expertise in the development, fabrication, and testing of grazing-incidence optics for x-ray telescopes. One of the key MSFC facilities for testing novel x-ray instrumentation is the SLF. This facility is an approximately 100-m-long beam line equipped with multiple x-ray sources and detectors. This new source adds to the already robust compliment of instrumentation, allowing MSFC to support additional internal and community x-ray testing needs.
    Keywords: Optics; Ground Support Systems and Facilities (Space); Astronomy
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 140-141; NASA/TM-2015-218204
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    Charge Analyzer Responsive Local Oscillations (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The first transatlantic radio transmission, demonstrated by Marconi in December of 1901, revealed the essential role of the ionosphere for radio communications. This ionized layer of the upper atmosphere controls the amount of radio power transmitted through, reflected off of, and absorbed by the atmospheric medium. Low-frequency radio signals can propagate long distances around the globe via repeated reflections off of the ionosphere and the Earth's surface. Higher frequency radio signals can punch through the ionosphere to be received at orbiting satellites. However, any turbulence in the ionosphere can distort these signals, compromising the performance or even availability of space-based communication and navigations systems. The physics associated with this distortion effect is analogous to the situation when underwater images are distorted by convecting air bubbles. In fact, these ionospheric features are often called 'plasma bubbles' since they exhibit some of the similar behavior as underwater air bubbles. These events, instigated by solar and geomagnetic storms, can cause communication and navigation outages that last for hours. To help understand and predict these outages, a world-wide community of space scientists and technologists are devoted to researching this topic. One aspect of this research is to develop instruments capable of measuring the ionospheric plasma bubbles. Figure 1 shows a photo of the Charge Analyzer Responsive to Local Oscillations (CARLO), a new instrument under development at NASA Marshall Space Flight Center (MSFC). It is a frequency-domain ion spectrum analyzer designed to measure the distributions of ionospheric turbulence from 1 Hz to 10 kHz (i.e., spatial scales from a few kilometers down to a few centimeters). This frequency range is important since it focuses on turbulence scales that affect VHF/UHF satellite communications, GPS systems, and over-the-horizon radar systems. CARLO is based on the flight-proven Plasma Local Anomalous Noise Environment (PLANE) instrument, previously flown on a U.S. Air Force low-Earth orbiting satellite, which successfully measured ion turbulence in five frequency decades from 0.1 Hz to 10 kHz (fig 2).
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 142-143; NASA/TM-2015-218204
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    Active Collision Avoidance for Planetary Landers (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The use of automotive radar systems are being evaluated for collision avoidance in planetary landers. Our focus is to develop a low-cost, light-weight collision avoidance system that overcomes the drawbacks identified with optical-based systems. We also seek to complement the Autonomous Landing and Hazard Avoidance Technology system by providing mission planners an alternative system that can be used on low-cost, small robotic missions and in close approach. Our approach takes advantage of how electromagnetic radiation interacts with solids. As the wavelength increases, the sensitivity of the radiation to isolated solids of a specific particle size decreases. Thus, rocket exhaust-blown dust particles, which have major significance in visible wavelengths, have much less significance at radar wavelengths.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking; Spacecraft Instrumentation and Astrionics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 128-129; NASA/TM-2015-218204
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    Direct Drive Solar-Powered Arcjet Thruster (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Electric thrusters typically require a power processing unit (PPU) to convert the spacecraft-provided power to the voltage and current that a thruster needs for operation. NASA Marshall Space Flight Center has initiated fundamental studies on whether an arcjet thruster can be operated directly with the power produced by solar arrays without any additional conversion. Elimination of the PPU significantly reduces system-level complexity of the propulsion system, and lowers developmental cost and risk. The proposed work will aim to refine the proof-of-concept presently being assembled and begin to identify and address technical questions related to power conditioning and noise suppression in the system, and heating of the thruster in long-duration operation. The apparatus proposed for investigation has a target power level of 400 to 1,000 W. The proposed direct-drive arcjet is potentially a highly scalable concept, applicable to spacecraft with up to hundreds of kilowatts and beyond. The design of the arcjet built for this effort was based on previous low power (1 kW class) arcjets.1-3 It has a precision machined 99.95% pure tungsten anode that also serves as the nozzle with a 0.040-in- (1-mm-) diameter, 0.040-in-long constrictor region. An additional anode with a 0.020-in- (0.5-mm-) diameter, 0.020-inlong constrictor region was purchased, but has not yet been used. The cathode is a 0.125-in-diameter tungsten welding electrode doped with lanthum-oxygen; its tip was precision ground to a 308deg angle and terminates in a blunt end. The two electrodes are separated by a boron-nitride insulator that also serves as the propellant manifold; it ends in six small holes which introduce the propellant gas in the diverging section of the nozzle, directly adjacent to the cathode. The electrodes and insulator are housed in a stainless-steel outer body, with a Macor insulator at the mid-plane to provide thermal isolation between the front and back halves of the device. The gas seals were made using Grafoil gaskets. Figure 1(a) shows the assembled thruster; figure 1(b) shows the thruster in the vacuum chamber with electrical and propellant connections.
    Keywords: General; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 126-127; NASA/TM-2015-218204
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    Flexible Electrostatic Technologies for Capture and Handling, Phase 1 (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Fundamental to many of NASA's in-space transportation missions is the capture and handling of various objects and vehicles in various orbits for servicing, debris disposal, sample retrieval, and assembly without the benefit of sufficient grapple fixtures and docking ports. To perform similar material handling tasks on Earth, pincher grippers, suction grippers, or magnetic chucks are used, but are unable to reliably grip aluminum and composite spacecraft, insulation, radiators, solar arrays, or extra-terrestrial objects in the vacuum of outer space without dedicated handles in the right places. The electronic Flexible Electrostatic Technologies for space Capture and Handling (FETCH) will enable reliable and compliant gripping (soft dock) of practically any object in various orbits or surfaces without dedicated mechanical features, very low impact capture, and built-in proximity sensing without any conventional actuators. Originally developed to handle semiconductor and glass wafers during vacuum chamber processing without contamination, the normal rigid wafer handling chucks are replaced with thin metal foil segments laminated in flexible insulation driven by commercial off-the-shelf solid state, high-voltage power supplies. Preliminary testing in NASA Marshall Space Flight Center's (MSFC's) Flat Floor Robotics Lab demonstrated compliant alignment and gripping with a full-sized, 150-lb microsat mockup and translation before a clean release with a flip of a switch. The flexible electrostatic gripper pads can be adapted to various space applications with different sizes, shapes, and foil electrode layouts even with openings through the gripper pads for addition of guidance sensors or injection of permanent adhesives. With gripping forces estimated between 0.5 and 2.5 lb/in2 or 70-300 lb/ft2 of surface contact, the FETCH can turn on and off rapidly and repeatedly to enable sample handling, soft docking, in-space assembly, precision relocation, and surface translation for accurate anchoring.
    Keywords: General; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 124-125; NASA/TM-2015-218204
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    Spherically Actuated Motor (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: A three degree of freedom (DOF) spherical actuator is proposed that will replace functions requiring three single DOF actuators in robotic manipulators providing space and weight savings while reducing the overall failure rate. Exploration satellites, Space Station payload manipulators, and rovers requiring pan, tilt, and rotate movements need an actuator for each function. Not only does each actuator introduce additional failure modes and require bulky mechanical gimbals, each contains many moving parts, decreasing mean time to failure. A conventional robotic manipulator is shown in figure 1. Spherical motors perform all three actuation functions, i.e., three DOF, with only one moving part. Given a standard three actuator system whose actuators have a given failure rate compared to a spherical motor with an equal failure rate, the three actuator system is three times as likely to fail over the latter. The Jet Propulsion Laboratory reliability studies of NASA robotic spacecraft have shown that mechanical hardware/mechanism failures are more frequent and more likely to significantly affect mission success than are electronic failures. Unfortunately, previously designed spherical motors have been unable to provide the performance needed by space missions. This inadequacy is also why they are unavailable commercially. An improved patentable spherically actuated motor (SAM) is proposed to provide the performance and versatility required by NASA missions.
    Keywords: General; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 120-121; NASA/TM-2015-218204
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    Targeted Structural Optimization with Additive Manufacturing of Metals (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The recent advances in additive manufacturing (AM) of metals have now improved the state-of-the-art such that traditionally non-producible parts can be readily produced in a cost-effective way. Because of these advances in manufacturing technology, structural optimization techniques are well positioned to supplement and advance this new technology. The goal of this project is to develop a structural design, analysis, and optimization framework combined with AM to significantly light-weight the interior of metallic structures while maintaining the selected structural properties of the original solid. This is a new state-of-the-art capability to significantly reduce mass, while maintaining the structural integrity of the original design, something that can only be done with AM. In addition, this framework will couple the design, analysis, and fabrication process, meaning that what has been designed directly represents the produced part, thus closing the loop on the design cycle and removing human iteration between design and fabrication. This fundamental concept has applications from light-weighting launch vehicle components to in situ resource fabrication.
    Keywords: Metals and Metallic Materials; Mechanical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 122-123; NASA/TM-2015-218204
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    Solid State Ultracapacitor (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: NASA analyzes, tests, packages, and fabricates electrical, electronic, and electromechanical (EEE) parts used in space vehicles. One area that NASA wishes to advance is energy storage and delivery. Currently, space vehicles use rechargeable batteries that utilize silver zinc or lithium ion electrochemical processes. These current state-of-the-art rechargeable batteries cannot be rapidly charged, contain harmful chemicals, and suffer from early wear-out mechanisms. A solid state ultracapacitor is an EEE part that offers significant advantages over current electrochemical and electrolytic devices. The objective of this research is to develop an internal barrier layer ultracapacitor (IBLC) using novel dielectric materials as a battery replacement with a focus on these advantages: longer life, lower mass-toweight ratio, rapid charging, on-demand pulse power, improved on-pad standby time without maintenance, and environmental friendliness. The approach is unique in two areas. A deposition technique is used that has been shown to produce a more uniformly coated nanoparticle than sol-gel, which has resulted in colossal permittivities. These particles are then distributed in an ink formulation developed at NASA Marshall Space Flight Center (MSFC) and deposited utilizing a 3D aerosol jet technique. This additive manufacturing technique controls layer thickness, resulting in extremely large capacitance and energy density.
    Keywords: Launch Vehicles and Launch Operations; Electronics and Electrical Engineering; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 118-119; NASA/TM-2015-218204
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    Flexible Hybrid Battery/Pseudocapacitor (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Batteries keep devices working by utilizing high energy density, however, they can run down and take tens of minutes to hours to recharge. For rapid power delivery and recharging, high-power density devices, i.e., supercapacitors, are used. The electrochemical processes which occur in batteries and supercapacitors give rise to different charge-storage properties. In lithium ion (Li+) batteries, the insertion of Li+, which enables redox reactions in bulk electrode materials, is diffusion controlled and can be slow. Supercapacitor devices, also known as electrical double-layer capacitors (EDLCs) store charge by adsorption of electrolyte ions onto the surface of electrode materials. No redox reactions are necessary, so the response to changes in potential without diffusion limitations is rapid and leads to high power. However, the charge in EDLCs is confined to the surface, so the energy density is lower than that of batteries.
    Keywords: Electronics and Electrical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 112-113; NASA/TM-2015-218204
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    Ultrasonic Stir Welding Development for Ground-Based and In Situ Fabrication and Repair for In-Space Propulsion Systems/Commercial Space Sector (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The completed Center Innovation Fund (CIF) project used the upgraded Ultrasonic Stir Weld (USW) Prototype System (built in 2013/2014) to begin characterizing the weld process using 2219 aluminum (fig. 1). This work is being done in Bldg. 4755 at NASA Marshall Space Flight Center (MSFC). The capabilities of the USW system provides the means to precisely control and document individual welding parameters. The current upgraded system has the following capabilities: (1) Ability to 'pulse' ultrasonic (US) energy on and off and adjust parameters real-time (travel speed, spindle rpm, US amplitude, X and Z axis positions, and plunge and pin axis force; (2) Means to measure draw force; (3) Ability to record US power versus time; (4) Increasing stiffness of Z axis drive and reduce head deflection using laser technology; (5) Adding linear encoder to better control tool penetration setting; (6) Ultrasonic energy integrated into stir rod and containment plate; (7) Maximum 600 rpm; (8) Maximum Z force 15,000 lb; (9) Real-time data acquisition and logging capabilities at a minimum frequency of 10 Hz; and (10) Two separate transducer power supplies operating at 4.5 kW power.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 114-115; NASA/TM-2015-218204
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    Small Business Innovation Research and Small Business Technology Transfer Programs (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Small Business Innovation Research (SBIR)/Small Business Technology Transfer (STTR) programs fund the research, development, and demonstration of innovative technologies that fulfill NASA's needs as described in the annual Solicitations and have significant potential for successful commercialization. The only eligible participants are small business concern (SBC) with 500 or fewer employees or a nonprofit research institute such as a university or a research laboratory with ties to an SBC. These programs are potential sources of seed funding for the development of small business innovations.
    Keywords: Administration and Management
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 108-109; NASA/TM-2015-218204
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    Lightweight Damage Tolerant, High-Temperature Radiators for Nuclear Power and Propulsion (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: NASA is increasingly emphasizing exploration to bodies beyond near-Earth orbit. New propulsion systems and new spacecraft are being built for these missions. As the target bodies get further out from Earth, high energy density systems, e.g., nuclear fusion, for propulsion and power will be advantageous. The mass and size of these systems, including supporting systems such as the heat exchange system, including thermal radiators, will need to be as small as possible. Conventional heat exchange systems are a significant portion of the total thermal management mass and size. Nuclear electric propulsion (NEP) is a promising option for high-speed, in-space travel due to the high energy density of nuclear fission power sources and efficient electric thrusters. Heat from the reactor is converted to power for use in propulsion or for system power. The heat not used in the power conversion is then radiated to space as shown in figure 1. Advanced power conversion technologies will require high operating temperatures and would benefit from lightweight radiator materials. Radiator performance dictates power output for nuclear electric propulsion systems. Pitch-based carbon fiber materials have the potential to offer significant improvements in operating temperature, thermal conductivity, and mass. These properties combine to allow significant decreases in the total mass of the radiators and significant increases in the operating temperature of the fins. A Center-funded project at NASA Marshall Space Flight Center has shown that high thermal conductivity, woven carbon fiber fins with no matrix material, can be used to dissipate waste heat from NEP systems and because of high specific power (kW/kg), will require less mass and possibly less total area than standard metal and composite radiator fins for radiating the same amount of heat. This project uses an innovative approach to reduce the mass and size required for the thermal radiators to the point that in-space NEP and power is enabled. High thermal conductivity carbon fibers are lightweight, damage tolerant, and can be heated to high temperature. Areal densities in the NASA set target range of 2 to 4 kg/m2 (for enabling NEP) are achieved and with specific powers (kW/kg) a factor of about 7 greater than conventional metal fins and about 1.5 greater than carbon composite fins. Figure 2 shows one fin under test. All tests were done under vacuum conditions.
    Keywords: Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 116-117; NASA/TM-2015-218204
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    Programmable Ultra-Lightweight System Adaptable Radio (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The programmable ultra-lightweight system adaptable radio (PULSAR) is a NASA Marshall Space Flight Center transceiver designed for the CubeSat market, but has the potential for other markets. The PULSAR project aims to reduce size, weight, and power while increasing telemetry data rate. The current version of the PULSAR has a mass of 2.2 kg and a footprint of 10.8 cm2. The height depends on the specific configuration. The PULSAR S-Band Communications Subsystem is an S- and X-band transponder system comprised of a receiver/detector (receiver) element, a transmitter element(s), and related power distribution, command, control, and telemetry element for operation and information interfaces. It is capable of receiving commands, encoding and transmitting telemetry, as well as providing tracking data in a manner compatible with Earthbased ground stations, near Earth network, and deep space network station resources. The software-defined radio's (SDR's) data format characteristics can be defined and reconfigured during spaceflight or prior to launch. The PULSAR team continues to evolve the SDR to improve the performance and form factor to meet the requirements that the CubeSat market space requires. One of the unique features is that the actual radio design can change (somewhat), but not require any hardware modifications due to the use of field programmable gate arrays.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 102-103; NASA/TM-2015-218204
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    Microelectrospray Thrusters (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Propulsion technology is often a critical enabling technology for space missions. NASA is investing in technologies to enable high value missions with very small spacecraft, even CubeSats. However, these nanosatellites currently lack any appreciable propulsion capability. CubeSats are typically deployed and tumble or drift without any ability to transfer to higher value orbits, perform orbit maintenance, or perform de-orbit. Larger spacecraft can also benefit from high precision attitude control systems. Existing practices include reaction wheels with lifetime concerns and system level complexity. Microelectrospray thrusters will provide new propulsion capabilities to address these mission needs. Electric propulsion is an approach to accelerate propellant to very high exhaust velocities through the use of electrical power. Typical propulsion systems are limited to the combustion energy available in the chemical bonds of the fuel and then acceleration through a converging diverging nozzle. However, electric propulsion can accelerate propellant to ten times higher velocities and therefore increase momentum transfer efficiency, or essentially, increase the fuel economy. Fuel efficiency of thrusters is proportional to the exhaust velocity and referred to as specific impulse (Isp). The state-of-the-art (SOA) for CubeSats is cold gas propulsion with an Isp of 50-80 s. The Space Shuttle main engine demonstrated a specific impulse of 450 s. The target Isp for the Mars Exploration Program (MEP) systems is 〉1,500 s. This propellant efficiency can enable a 1-kg, 10-cm cube to transfer from low-Earth orbit to interplanetary space with only 200 g of propellant. In September 2013, NASA's Game Changing Development program competitively awarded three teams with contracts to develop MEP systems from Technology Readiness Level-3 (TRL-3), experimental concept, to TRL-5, system validation in a relevant environment. The project is planned for 18 months of system development. Due to the ambitious project goals, NASA has awarded contracts to mature three unique methods to achieve the desired goals. Some of the MEP concepts have been developed for more than a decade at the component level, but are now ready for system maturation. The three concepts include the high aspect ratio porous surface (HARPS) microthruster system, the scalable ion electrospray propulsion system (S-iEPS), and an indium microfluidic electrospray propulsion system. The HARPS system is under development by Busek Co. The HARPS thruster is an electrospray thruster that relies on surface emission of a porous metal with a passive capillary wicking system for propellant management. The HARPS thruster is expected to provide a simple, high V and low-cost solution. The HARPS thruster concept is shown in figure 1. Figure 1 includes the thruster, integrated power processing unit, and propellant reservoir.
    Keywords: Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 104-105; NASA/TM-2015-218204
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    Space Synthetic Biology Project (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Synthetic biology is an effort to make genetic engineering more useful by standardizing sections of genetic code. By standardizing genetic components, biological engineering will become much more similar to traditional fields of engineering, in which well-defined components and subsystems are readily available in markets. Specifications of the behavior of those components and subsystems can be used to model a system which incorporates them. Then, the behavior of the novel system can be simulated and optimized. Finally, the components and subsystems can be purchased and assembled to create the optimized system, which most often will exhibit behavior similar to that indicated by the model. The Space Synthetic Biology project began in 2012 as a multi-Center effort. The purpose of this project was to harness Synthetic Biology principals to enable NASA's missions. A central target for application was to Environmental Control & Life Support (ECLS). Engineers from NASA Marshall Space Flight Center's (MSFC's) ECLS Systems Development Branch (ES62) were brought into the project to contribute expertise in operational ECLS systems. Project lead scientists chose to pursue the development of bioelectrochemical technologies to spacecraft life support. Therefore, the ECLS element of the project became essentially an effort to develop a bioelectrochemical ECLS subsystem. Bioelectrochemical systems exploit the ability of many microorganisms to drive their metabolisms by direct or indirect utilization of electrical potential gradients. Whereas many microorganisms are capable of deriving the energy required for the processes of interest (such as carbon dioxide (CO2) fixation) from sunlight, it is believed that subsystems utilizing electrotrophs will exhibit smaller mass, volume, and power requirements than those that derive their energy from sunlight. In the first 2 years of the project, MSFC personnel conducted modeling, simulation, and conceptual design efforts to assist the project in selecting the best approaches to the application of bioelectrochemical technologies to ECLS. Figure 1 shows results of simulation of charge transport in an experimental system. Figure 2 shows one of five conceptual designs for ECLS subsystems based on bioelectrochemical reactors. Also during the first 2 years, some work was undertaken to gather fundamental data (conductivities, overpotentials) relevant to the modeling efforts.
    Keywords: Man/System Technology and Life Support; Life Sciences (General)
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 100-101; NASA/TM-2015-218204
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    Low Cost, Upper Stage-Class Propulsion (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The low cost, upper stage-class propulsion (LCUSP) element will develop a high strength copper alloy additive manufacturing (AM) process as well as critical components for an upper stage-class propulsion system that will be demonstrated with testing. As manufacturing technologies have matured, it now appears possible to build all the major components and subsystems of an upper stage-class rocket engine for substantially less money and much faster than traditionally done. However, several enabling technologies must be developed before that can happen. This activity will address these technologies and demonstrate the concept by designing, manufacturing, and testing the critical components of a rocket engine. The processes developed and materials' property data will be transitioned to industry upon completion of the activity. Technologies to enable the concept are AM copper alloy process development, AM post-processing finishing to minimize surface roughness, AM material deposition on existing copper alloy substrate, and materials characterization.
    Keywords: Spacecraft Propulsion and Power; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 98-99; NASA/TM-2015-218204
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    Materials Genome Initiative (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Materials Genome Initiative (MGI) project element is a cross-Center effort that is focused on the integration of computational tools to simulate manufacturing processes and materials behavior. These computational simulations will be utilized to gain understanding of processes and materials behavior to accelerate process development and certification to more efficiently integrate new materials in existing NASA projects and to lead to the design of new materials for improved performance. This NASA effort looks to collaborate with efforts at other government agencies and universities working under the national MGI. MGI plans to develop integrated computational/experimental/ processing methodologies for accelerating discovery and insertion of materials to satisfy NASA's unique mission demands. The challenges include validated design tools that incorporate materials properties, processes, and design requirements; and materials process control to rapidly mature emerging manufacturing methods and develop certified manufacturing processes
    Keywords: Computer Programming and Software; Mechanical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 96-97; NASA/TM-2015-218204
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    Advanced Near Net Shape Technology (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The objective of the Advanced Near Net Shape Technology (ANNST) project is to radically improve near net shape manufacturing methods from the current Technology/ Manufacturing Readiness Levels (TRL/MRL 3-4) to the point where they are viable candidates (TRL/ MRL-6) for shortening the time and cost for insertion of new aluminum alloys and revolutionary manufacturing methods into the development/improvement of space structures. Conventional cyrotank manufacturing processes require fabrication of multiple pieces welded together to form a complete tank. A variety of near net shape manufacturing processes has demonstrated excellent potential for enabling single-piece construction of components such as domes, barrels, and ring frames. Utilization of such processes can dramatically reduce the extent of welding and joining needed to construct cryogenic tanks and other aerospace structures. The specific focus of this project is to successfully mature the integrally stiffened cylinder (ISC) process in which a single-piece cylinder with integral stiffeners is formed in one spin/flow forming process. Structural launch vehicle components, like cryogenic fuel tanks (e.g., space shuttle external tank), are currently fabricated via multipiece assembly of parts produced through subtractive manufacturing techniques. Stiffened structural panels are heavily machined from thick plate, which results in excessive scrap rates. Multipiece construction requires welds to assemble the structure, which increases the risk for defects and catastrophic failures.
    Keywords: General; Spacecraft Design, Testing and Performance; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 94-95; NASA/TM-2015-218204
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    Composite Cryotank Technologies and Demonstration (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: NASA is exploring advanced composite materials and processes to reduce the overall cost and weight of liquid hydrogen (LH2) cryotanks while maintaining the reliability of existing metallic designs. The fundamental goal of the composite cryotank project was to provide new and innovative technologies that enable human space exploration to destinations beyond low-Earth orbit such as the Moon, near-Earth asteroids, and Mars. In September 2011, NASA awarded Boeing the contract to design, manufacture, and test two lightweight composite cryogenic propellant tanks. The all-composite tanks shown iare fabricated with an automated fiber placement machine using a prepreg system of IM7 carbon fiber/CYCOM 5320-1 epoxy resin. This is a resin system developed for out-of-autoclave applications. Switching from metallic to composite construction holds the potential to dramatically increase the performance capabilities of future space systems through a dramatic reduction in weight. Composite Cryotank Technologies and Demonstration testing was an agency-wide effort with NASA Marshall Space Flight Center (MSFC) leading project management, manufacturing, and test; Glenn Research Center leading the materials; and Langley Research Center leading the structures effort for this project. Significant contributions from NASA loads/stress personnel contributed to the understanding of thermal/mechanical strain response while undergoing testing at cryogenic temperatures. The project finalized in September 2014.
    Keywords: Propellants and Fuels; Launch Vehicles and Launch Operations; Composite Materials
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 92-93; NASA/TM-2015-218204
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    Magnetogram Forecast: An All-Clear Space Weather Forecasting System (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Solar flares and coronal mass ejections (CMEs) are the drivers of severe space weather. Forecasting the probability of their occurrence is critical in improving space weather forecasts. The National Oceanic and Atmospheric Administration (NOAA) currently uses the McIntosh active region category system, in which each active region on the disk is assigned to one of 60 categories, and uses the historical flare rates of that category to make an initial forecast that can then be adjusted by the NOAA forecaster. Flares and CMEs are caused by the sudden release of energy from the coronal magnetic field by magnetic reconnection. It is believed that the rate of flare and CME occurrence in an active region is correlated with the free energy of an active region. While the free energy cannot be measured directly with present observations, proxies of the free energy can instead be used to characterize the relative free energy of an active region. The Magnetogram Forecast (MAG4) (output is available at the Community Coordinated Modeling Center) was conceived and designed to be a databased, all-clear forecasting system to support the operational goals of NASA's Space Radiation Analysis Group. The MAG4 system automatically downloads nearreal- time line-of-sight Helioseismic and Magnetic Imager (HMI) magnetograms on the Solar Dynamics Observatory (SDO) satellite, identifies active regions on the solar disk, measures a free-energy proxy, and then applies forecasting curves to convert the free-energy proxy into predicted event rates for X-class flares, M- and X-class flares, CMEs, fast CMEs, and solar energetic particle events (SPEs). The forecast curves themselves are derived from a sample of 40,000 magnetograms from 1,300 active region samples, observed by the Solar and Heliospheric Observatory Michelson Doppler Imager. Figure 1 is an example of MAG4 visual output
    Keywords: Launch Vehicles and Launch Operations; Solar Physics; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 90-91; NASA/TM-2015-218204
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    Multi-Spacecraft Autonomous Positioning System (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: As the number of spacecraft in simultaneous operation continues to grow, there is an increased dependency on ground-based navigation support. The current baseline system for deep space navigation utilizes Earth-based radiometric tracking, requiring long-duration observations to perform orbit determination and generate a state update. The age, complexity, and high utilization of the ground assets pose a risk to spacecraft navigation performance. In order to perform complex operations at large distances from Earth, such as extraterrestrial landing and proximity operations, autonomous systems are required. With increasingly complex mission operations, the need for frequent and Earth-independent navigation capabilities is further reinforced. The Multi-spacecraft Autonomous Positioning System (MAPS) takes advantage of the growing interspacecraft communication network and infrastructure to allow for Earth-autonomous state measurements to enable network-based space navigation. A notional concept of operations is given in figure 1. This network is already being implemented and routinely used in Martian communications through the use of the Mars Reconnaissance Orbiter and Mars Odyssey spacecraft as relays for surface assets. The growth of this communications architecture is continued through MAVEN, and future potential commercial Mars telecom orbiters. This growing network provides an initial Marslocal capability for inter-spacecraft communication and navigation. These navigation updates are enabled by cross-communication between assets in the network, coupled with onboard navigation estimation routines to integrate packet travel time to generate ranging measurements. Inter-spacecraft communication allows for frequent state broadcasts and time updates from trusted references. The architecture is a software-based solution, enabling its implementation on a wide variety of current assets, with the operational constraints and measurement accuracy determined by onboard systems.
    Keywords: Space Communications, Spacecraft Communications, Command and Tracking
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 88-89; NASA/TM-2015-218204
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    Altitude Compensating Nozzle (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The dual-bell nozzle (fig. 1) is an altitude-compensating nozzle that has an inner contour consisting of two overlapped bells. At low altitudes, the dual-bell nozzle operates in mode 1, only utilizing the smaller, first bell of the nozzle. In mode 1, the nozzle flow separates from the wall at the inflection point between the two bell contours. As the vehicle reaches higher altitudes, the dual-bell nozzle flow transitions to mode 2, to flow full into the second, larger bell. This dual-mode operation allows near optimal expansion at two altitudes, enabling a higher mission average specific impulse (Isp) relative to that of a conventional, single-bell nozzle. Dual-bell nozzles have been studied analytically and subscale nozzle tests have been completed.1 This higher mission averaged Isp can provide up to a 5% increase2 in payload to orbit for existing launch vehicles. The next important step for the dual-bell nozzle is to confirm its potential in a relevant flight environment. Toward this end, NASA Marshall Space Flight Center (MSFC) and Armstrong Flight Research Center (AFRC) have been working to develop a subscale, hot-fire, dual-bell nozzle test article for flight testing on AFRC's F15-D flight test bed (figs. 2 and 3). Flight test data demonstrating a dual-bell ability to control the mode transition and result in a sufficient increase in a rocket's mission averaged Isp should help convince the launch service providers that the dual-bell nozzle would provide a return on the required investment to bring a dual-bell into flight operation. The Game Changing Department provided 0.2 FTE to ER42 for this effort in 2014.
    Keywords: Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 86-87; NASA/TM-2015-218204
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    Adjustable Grazing-Incidence X-Ray Optics (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: With its unique subarcsecond imaging performance, NASA's Chandra X-ray Observatory illustrates the importance of fine angular resolution for x-ray astronomy. Indeed, the future of x-ray astronomy relies upon x-ray telescopes with comparable angular resolution but larger aperture areas. Combined with the special requirements of nested grazing-incidence optics, mass, and envelope constraints of space-borne telescopes render such advances technologically and programmatically challenging. The goal of this technology research is to enable the cost-effective fabrication of large-area, lightweight grazing-incidence x-ray optics with subarcsecond resolution. Toward this end, the project is developing active x-ray optics using slumped-glass mirrors with thin-film piezoelectric arrays for correction of intrinsic or mount-induced distortions.
    Keywords: Optics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 84-85; NASA/TM-2015-218204
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    Soldier-Warfighter Operationally Responsive Deployer for Space (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Soldier-Warfighter Operationally Responsive Deployer for Space (SWORDS) project was a joint project between the U.S. Army Space & Missile Defense Command (SMDC) and NASA. The effort, lead by SMDC, was intended to develop a three-stage liquid bipropellant (liquid oxygen/liquid methane), pressure-fed launch vehicle capable of inserting a payload of at least 25 kg to a 750-km circular orbit. The vehicle design was driven by low cost instead of high performance. SWORDS leveraged commercial industry standards to utilize standard hardware and technologies over customized unique aerospace designs. SWORDS identified broadly based global industries that have achieved adequate levels of quality control and reliability in their products and then designed around their expertise and business motivations.
    Keywords: Launch Vehicles and Launch Operations; Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 80-81; NASA/TM-2015-218204
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    Fast Light Optical Gyroscopes (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Next-generation space missions are currently constrained by existing spacecraft navigation systems which are not fully autonomous. These systems suffer from accumulated dead-reckoning errors and must therefore rely on periodic corrections provided by supplementary technologies that depend on line-of-sight signals from Earth, satellites, or other celestial bodies for absolute attitude and position determination, which can be spoofed, incorrectly identified, occluded, obscured, attenuated, or insufficiently available. These dead-reckoning errors originate in the ring laser gyros themselves, which constitute inertial measurement units. Increasing the time for standalone spacecraft navigation therefore requires fundamental improvements in gyroscope technologies. One promising solution to enhance gyro sensitivity is to place an anomalous dispersion or fast light material inside the gyro cavity. The fast light essentially provides a positive feedback to the gyro response, resulting in a larger measured beat frequency for a given rotation rate as shown in figure 1. Game Changing Development has been investing in this idea through the Fast Light Optical Gyros (FLOG) project, a collaborative effort which began in FY 2013 between NASA Marshall Space Flight Center (MSFC), the U.S. Army Aviation and Missile Research, Development, and Engineering Center (AMRDEC), and Northwestern University. MSFC and AMRDEC are working on the development of a passive FLOG (PFLOG), while Northwestern is developing an active FLOG (AFLOG). The project has demonstrated new benchmarks in the state of the art for scale factor sensitivity enhancement. Recent results show cavity scale factor enhancements of approx.100 for passive cavities.
    Keywords: Spacecraft Instrumentation and Astrionics; Space Communications, Spacecraft Communications, Command and Tracking
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 82-83; NASA/TM-2015-218204
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    Bosch Reactor Development for High Percentage Oxygen Recovery from Carbon Dioxide (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This next Generation Life Support Project entails the development and demonstration of Bosch reaction technologies to improve oxygen recovery from metabolically generated oxygen and/or space environments. A primary focus was placed on alternate carbon formation reactor concepts to improve useful catalyst life for space vehicle applications, and make use of in situ catalyst resources for non-terrestrial surface missions. Current state-of-the-art oxygen recovery systems onboard the International Space Station are able to effectively recover approximately 45 percent of the oxygen consumed by humans and exhausted in the form of carbon dioxide (CO2). Excess CO2 is vented overboard and the oxygen contained in the molecules is lost. For long-duration missions beyond the reaches of Earth for resupply, it will be necessary to recover greater amounts of constituents such as oxygen that are necessary for sustaining life. Bosch technologies theoretically recover 100 percent of the oxygen from CO2, producing pure carbon as the sole waste product. Challenges with this technology revolve around the carbon product fouling catalyst materials, drastically limiting catalyst life. This project successfully demonstrated techniques to extend catalyst surface area exposure times to improve catalyst life for vehicle applications, and demonstrated the use of Martian and lunar regolith as viable catalyst Bosch Reactor Development for High Percentage Oxygen Recovery From Carbon Dioxide materials for surface missions. The Bosch process generates carbon nanotube formation within the regolith, which has been shown to improve mechanical properties of building materials. Production of bricks from post reaction regolith for building and radiation shielding applications were also explored.
    Keywords: Man/System Technology and Life Support; Lunar and Planetary Science and Exploration
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 78-79; NASA/TM-2015-218204
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    Centennial Challenges Program (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: NASA's Centennial Challenges Program was initiated in 2005 to directly engage the public in the process of advanced technology development. The program offers incentive prizes to generate revolutionary solutions to problems of interest to NASA and the nation. The program seeks innovations from diverse and nontraditional sources. Competitors are not supported by government funding and awards are only made to successful teams when the challenges are met. In keeping with the spirit of the Wright Brothers and other American innovators, the Centennial Challenge prizes are offered to independent inventors including small businesses, student groups, and individuals. These independent inventors are sought to generate innovative solutions for technical problems of interest to NASA and the nation and to provide them with the opportunity to stimulate or create new business ventures.
    Keywords: General; Social and Information Sciences (General)
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 74-75; NASA/TM-2015-218204
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    Cryogenic Propellant Storage and Transfer Engineering Development Unit Hydrogen Tank (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Cryogenic Propellant Storage and Transfer (CPST) project has been a long-running program in the Space Technology Mission Directorate to enhance the knowledge and technology related to handling cryogenic propellants, specifically liquid hydrogen. This particular effort, the CPST engineering development unit (EDU), was a proof of manufacturability effort in support of a flight article. The EDU was built to find and overcome issues related to manufacturability and collect data to anchor the thermal models for use on the flight design.
    Keywords: Propellants and Fuels
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 70-71; NASA/TM-2015-218204
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    Mars Ascent Vehicle-First Stage Motor (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This project is development effort of a first stage solid motor based on a two-stage solid motor Mars Ascent Vehicle (MAV) design for the robotic Mars Sample Return (MSR) mission (fig. 1). The MSR MAV has been studied for decades and multiple concepts have been shown to meet the mission objectives as posed.1 However, there remains significant uncertainty with the MAV requirements. The sample container and sample cache itself is immature. Additionally, MAV-specific requirements ranging from full three-axis controlled and strict communication requirements to minimal capability concepts are still under consideration. Given the maturity of the overall mission requirements, the MAV has been limited to a large number of parametric analyses and paper studies. Recently, a Jet Propulsion Laboratory study highlighted the flexibility of a two-stage solid motor concept. The MAV itself is driven by the constraints of the Entry, Decent, and Landing (EDL) system. Within the EDL constraints, there is a range of MAV options ranging in complexity from simple spun upper stage options to higher capability three-axis controlled solutions. There are also options to trade the ratio of mission (Delta)V between the first and second stage. Finally, sensitivity studies also indicated that solid motors with a high percentage of off-load flexability only had minor impact on the total system mass over a single point design optimized motor. This flexibility in the first stage motor has allowed NASA to mature the design of the motor beyond parametric analyses and start to address known design challenges of the motor.
    Keywords: Spacecraft Propulsion and Power; Spacecraft Design, Testing and Performance
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 60-61; NASA/TM-2015-218204
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    Mars Ascent Vehicle-Propellant Aging (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This project is to develop and test a new propellant formulation specifically for the Mars Ascent Vehicle (MAV) for the robotic Mars Sample Return mission. The project was initiated under the Planetary Sciences Division In-Space Propulsion Technology (ISPT) program and is continuing under the Mars Exploration Program. The two-stage, solid motor-based MAV has been the leading MAV solution for more than a decade. Additional studies show promise for alternative technologies including hybrid and bipropellant options, but the solid motor design has significant propellant density advantages well suited for physical constraints imposed while using the SkyCrane descent stage. The solid motor concept has lower specific impulse (Isp) than alternatives, but if the first stage and payload remain sufficiently small, the two-stage solid MAV represents a potential low risk approach to meet the mission needs. As the need date for the MAV slips, opportunities exist to advance technology with high on-ramp potential. The baseline propellant for the MAV is currently the carboxyl terminated polybutadiene (CTPB) based formulation TP-H-3062 due to its advantageous low temperature mechanical properties and flight heritage. However, the flight heritage is limited and outside the environments, the MAV must endure. The ISPT program competed a propellant formulation project with industry and selected ATK to develop a new propellant formulation specifically for the MAV application. Working with ATK, a large number of propellant formulations were assessed to either increase performance of a CTPB propellant or improve the low temperature mechanical properties of a hydroxyl terminated polybutadiene (HTPB) propellant. Both propellants demonstrated potential to increase performance over heritage options, but an HTPB propellant formulation, TP-H-3544, was selected for production and testing. The test plan includes propellant aging first at high vacuum conditions, representative of the Mars transit, followed by an additional year at simulated Mars surface conditions. The actual Mars surface environment is based on the igloo design, actively maintains the propellant at or above -40 degC, 95% carbon dioxide at Mars surface pressure. The NASA Marshall Space Flight Center (MSFC) Mars environment test facility is shown in figure 1 and located in the East Test area of Redstone Arsenal due to storage of live propellants. The facility consists of a vacuum chamber placed inside a large freezer unit. The facility includes pressure and temperature monitoring equipment in addition to a vacuum quality monitoring system spectrometer to record any outgassing products.
    Keywords: General; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 62-63; NASA/TM-2015-218204
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    Advanced UVOIR Mirror Technology Development for Very Large Space Telescopes (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Advanced Mirror Technology Development (AMTD) project is in phase 2 of a multiyear effort, initiated in FY 2012. This effort is to mature, by at least a half Technology Readiness Level step, the critical technologies required to enable 4-meter or larger ultraviolet, optical, and infrared (UVOIR) space telescope primary mirror assemblies for both general astrophysics and ultra-high contrast observations of exoplanets. AMTD continues to achieve all of its goals and has accomplished all of its milestones to date. This has been achieved by assembling an outstanding team from academia, industry, and government with extensive expertise in astrophysics and exoplanet characterization, and in the design/manufacture of monolithic and segmented space telescopes; by deriving engineering specifications for advanced normal-incidence mirror systems needed to make the required science measurements; and by defining and prioritizing the most important technical problems to be solved. Our results have been presented to the CoPAG and Mirror Tech Days 2013, and proceedings papers of the 2013 and 2014 SPIE Optics & Photonics Symposia have been published.
    Keywords: Optics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; Stahl, H. Philip; 58-59; NASA/TM-2015-218204
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    Technology Demonstration Missions (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Technology Demonstration Missions (TDM) is in its third year of execution, being initiated in 2010 and baselined in January of 2012. There are 11 projects that NASA Marshall Space Flight Center (MSFC) has contributed to or led: (1) Evolvable Cryogenics (eCryo): Cyrogenic Propellant Storage and Transfer Engineering Development Unit (EDU), a proof of manufacturability effort, used to enhance knowledge and technology related to handling cryogenic propellants, specifically liquid hydrogen. (2) Composites for Exploration Upper Stage (CEUS): Design, build, test, and address flight certification of a large composite shell suitable for the second stage of the Space Launch System (SLS). (3) Deep Space Atomic Clock (DSAC): Spaceflight to demo small, low-mass atomic clock that can provide unprecedented stability for deep space navigation. (4) Green Propellant Infusion Mission (GPIM): Demo of high-performance, green propellant propulsion system suitable for Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA)-class spacecraft. (5) Human Exploration Telerobotics (HET): Demonstrating how telerobotics, remote control of a variety of robotic systems, can take routine, highly repetitive, dangerous or long-duration tasks out of human hands. (6) Laser Communication Relay Demo (LCRD): Demo to advance optical communications technology toward infusion into deep space and near Earth operational systems, while growing the capabilities of industry sources. (7) Low Density Supersonic Decelerator (LDSD): Demo new supersonic inflatable decelerator and parachute technologies to enable Mars landings of larger payloads with greater precision at a wider range of altitudes. (8) Mars Science Laboratory (MSL) Entry Descent & Landing Instrumentation (MEDLI): Demo of embedded sensors embedded in the MSL heat shield, designed to record the heat and atmospheric pressure experienced during the spacecraft's high-speed, hot entry in the Martian atmosphere. (9) Solar Electric Propulsion (SEP): 50-kW class spacecraft that uses flexible blanket solar arrays for power generation and an electric propulsion system that delivers payload from low-Earth orbit to higher orbits. (10) Solar Sail Demonstration (SSD): Demo to validate sail deployment techniques for solar sails that are propelled by the pressure of sunlight. (11) Terrestrial HIAD Orbit Reentry (THOR): Demo of a 3.7-m Hypersonic Inflatable Aerodynamic Decelerator (HIAD) entry vehicle to test second generation aerothermal performance and modeling.
    Keywords: General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 68-69; NASA/TM-2015-218204
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    Performance Improvement of Friction Stir Welds by Better Surface Finish (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The as-welded friction stir weld has a cross section that may act as a stress concentrator. The geometry associated with the stress concentration may reduce the weld strength and it makes the weld challenging to inspect with ultrasound. In some cases, the geometry leads to false positive nondestructive evaluation (NDE) indications and, in many cases, it requires manual blending to facilitate the inspection. This study will measure the stress concentration effect and develop an improved phased array ultrasound testing (PAUT) technique for friction stir welding. Post-welding, the friction stir weld (FSW) tool would be fitted with an end mill that would machine the weld smooth, trimmed shaved. This would eliminate the need for manual weld preparation for ultrasonic inspections. Manual surface preparation is a hand operation that varies widely depending on the person preparing the welds. Shaving is a process that can be automated and tightly controlled.
    Keywords: Mechanical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 54-55; NASA/TM-2015-218204
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    Thermal Protection System Application to Composite Cryotank Technology Demonstrator (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The EM41 Thermal Protection System (TPS) team contributed to the success of the Composite Cryotank Technology Demonstrator (CCTD) manufacturing by developing and implementing a low-cost solution to apply cryoinsulation foam on the exterior surface of the tank in the NASA Marshall Space Flight Center (MSFC) TPS Development Facility, Bldg. 4765. The TPS team used techniques developed for the smallscale composite cryotank to apply Stepanfoam S-180 polyurethane foam to the 5.5-meter CCTD using a manual spray process. Manual spray foam technicians utilized lifts and scaffolding to access the barrel and dome sections of the large-scale tank in the horizontal orientation. During manufacturing, the tank was then oriented vertically, allowing access to the final barrel section for manual spray foam application. The CCTD was the largest application of manual spray foam performed to date with the S-180 polyurethane foam and required the TPS team to employ best practices for process controls on the development article.
    Keywords: Composite Materials; Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; Nettles, Mindy; 52-53; NASA/TM-2015-218204
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    Aluminum 2195 T8 Gore Development for Space Launch System Core and Upper Stage (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Gores are pie-shaped panels that are welded together to form the dome ends of rocket fuel tanks as shown in figure 1. Replacing aluminum alloy 2219 with aluminum (Al)-lithium (Li) alloy 2195 as the Space Launch System (SLS) cryogenic tank material would save enormous amounts of weight. In fact, it has been calculated that simply replacing Al 2219 gores with Al 2195 gores on the SLS core stage domes could save approximately 3,800 pound-mass. This is because the Al-Li 2195 alloy exhibits both higher mechanical properties and lower density than the SLS baseline Al 2219 alloy. Indeed, the known advantages of Al 2195 led to its use as a replacement for Al 2219 in the shuttle external tank program. The required thicknesses of Al 2195 gores for either SLS core stage tanks or upper stage tanks will depend on the specific design configurations. The required thicknesses or widths may exceed the current experience base in the manufacture of such gores by the stretch-forming process. Accordingly, the primary objective of this project was to enhance the formability of Al 2195 by optimizing the heat treatment and stretch-forming process for gore thicknesses up to 0.75 inches, which envelop the maximum expected gore thicknesses for SLS tank configurations.
    Keywords: Metals and Metallic Materials; Spacecraft Propulsion and Power; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 50-51; NASA/TM-2015-218204
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    Insulation Reformulation Development (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The current Space Launch System (SLS) internal solid rocket motor insulation, polybenzimidazole acrylonitrile butadiene rubber (PBI-NBR), is a new insulation that replaced asbestos-based insulations found in Space Shuttle heritage solid rocket boosters. PBI-NBR has some outstanding characteristics such as an excellent thermal erosion resistance, low thermal conductivity, and low density. PBI-NBR also has some significant challenges associated with its use: Air entrainment/entrapment during manufacture and lay-up/cure and low mechanical properties such as tensile strength, modulus, and fracture toughness. This technology development attempted to overcome these challenges by testing various reformulated versions of booster insulation. The results suggest the SLS program should continue to investigate material alternatives for potential block upgrades or use an entirely new, more advanced booster. The experimental design was composed of a logic path that performs iterative formulation and testing in order to maximize the effort. A lab mixing baseline was developed and documented for the Rubber Laboratory in Bldg. 4602/Room 1178.
    Keywords: Nonmetallic Materials
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 48-49; NASA/TM-2015-218204
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    Hot-Fire Test of Liquid Oxygen/Hydrogen Space Launch Mission Injector Applicable to Exploration Upper Stage (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This task is to hot-fire test an existing Space Launch Mission (SLM) injector that is applicable for all expander cycle engines being considered for the exploration upper stage. The work leverages investment made in FY 2013 that was used to additively manufacture three injectors (fig. 1) all by different vendors..
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 44-45; NASA/TM-2015-218204
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    Lattice Boltzmann Method for Spacecraft Propellant Slosh Simulation (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: No abstract available
    Keywords: Propellants and Fuels; Fluid Mechanics and Thermodynamics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 42-43; NASA/TM-2015-218204
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    Nanoelectric Materials Laboratory Development (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Ultracapacitor Research and Development project is a collaborative effort between the NASA Marshall Space Flight Center's (MSFC's) ES43 Parts, Packaging, and Fabrication Branch and the EM41 Nonmetallic Materials Branch. NASA's Ultracapacitor Research is an effort to develop solid-state energy storage devices through processing of ceramic materials into printable dielectric inks, which can be formed and treated to produce solid state ultracapacitor cells capable of exceeding lithium-ion battery energy density at a fraction of the weight. Research and development efforts into solid state ultracapacitors have highlighted a series of technical challenges such as understanding as-received nature of ceramic powders, treatment and optimization of ceramic powders, dielectric and conductor ink formulation, and firing of printed (green) ultracapacitor cells. Two facilities have been continually developed since project inception: the Additive Electronics Lab in Bldg. 4487 and the Nanoelectric Materials Lab in Bldg. 4602. The Nanoelectric Materials Lab has become a unique facility at MSFC, capable of custom processing a wide range of media for additive electronics. As research has progressed, it was discovered that additional in-house processing was necessary to achieve smaller, more uniform particle diameters. A vibratory mill was obtained that can agitate powder and media in three directions, which has shown to be much more effective than ball milling. However, in order to understand the effects of milling, a particle size analysis system has been installed to characterize as-received and milled materials Continued research into the ultracapacitor technology included advanced milling and optimization of ceramic nanoparticles, fluidized bed treatment of atomic-layer deposition- (ALD-) coated ceramic particles, custom development of dielectric and conductor inks, as well as custom ink precursors such as polyvinylidene diflouride- (PVDF-) loaded vehicles. Experiments with graphene-based inks were also conducted.
    Keywords: Electronics and Electrical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 46-47; NASA/TM-2015-218204
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    Advanced Booster Liquid Engine Combustion Stability (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Combustion instability is a phenomenon in liquid rocket engines caused by complex coupling between the time-varying combustion processes and the fluid dynamics in the combustor. Consequences of the large pressure oscillations associated with combustion instability often cause significant hardware damage and can be catastrophic. The current combustion stability assessment tools are limited by the level of empiricism in many inputs and embedded models. This limited predictive capability creates significant uncertainty in stability assessments. This large uncertainty then increases hardware development costs due to heavy reliance on expensive and time-consuming testing.
    Keywords: Spacecraft Propulsion and Power; Fluid Mechanics and Thermodynamics
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 40-41; NASA/TM-2015-218204
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    Composite Dry Structure Cost Improvement Approach (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This effort demonstrates that by focusing only on properties of relevance, composite interstage and shroud structures can be placed on the Space Launch System vehicle that simultaneously reduces cost, improves reliability, and maximizes performance, thus providing the Advanced Development Group with a new methodology of how to utilize composites to reduce weight for composite structures on launch vehicles. Interstage and shroud structures were chosen since both of these structures are simple in configuration and do not experience extreme environments (such as cryogenic or hot gas temperatures) and should represent a good starting point for flying composites on a 'man-rated' vehicle. They are used as an example only. The project involves using polymer matrix composites for launch vehicle structures, and the logic and rationale behind the proposed new methodology.
    Keywords: Launch Vehicles and Launch Operations; Composite Materials
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 38-39; NASA/TM-2015-218204
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    Hexavalent Chromium IV-Free Primer Development (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Primer materials provide corrosion protection for metal parts as well as an increased adhesion between metallic substrates and thermal protection systems (TPSs). Current primers for use in cryogenic applications contain hexavalent chromium. This hexavalent chromium provides excellent corrosion protection even in a cryogenic environment, but it is a carcinogen that requires special equipment and waste control procedures to use. The hazardous nature of hexavalent chromium makes it an obsolescence risk in the future. This study included two phases of evaluation. Thirteen primers were initially identified as candidates and twelve of those primers were tested in phase 1. Four of the best performing candidates from phase 1 continued into phase 2 testing. Phase 1 testing consisted mostly of liquid constituent and physical property testing. Cryoflex and salt fog testing were included in phase 1 because of their importance to the overall success of a candidate material. Phase 2 consisted of physical, thermal, and mechanical properties for nominally processed and fabricated specimens.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 34-35; NASA/TM-2015-218204
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    Low-Profile Diffuser (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The propellant tanks used in liquid rockets require pressurization gases in order to maintain tank pressure while the tanks are being drained during engine operation. The pressurization gas, which is typically much warmer than the relatively cold propellants in the tank, must be introduced into the empty ullage space at the top of the tank. The purpose of the diffuser is to control the flow of the gas into the tank in order to prevent direct impingement of the gas on the liquid surface and/or the tank walls. If the diffuser did not perform those tasks, the warm gas can create excess heat transfer causing an increase in the amount of pressurization mass required. Typical diffusers are long vertical cylinders that create a large exit area in order to minimize gas velocities. However, long vertical cylinders limit the amount of liquid that can be loaded into the tank in order not to have the liquid surface near the diffuser. A design goal for a pressurization diffuser is to create uniform flow in order to prevent jets that can impact the liquid surface and/or tank walls. The purpose of the task was to create a diffuser design that had a lower vertical profile (in order to be able to raise the liquid surface) while still maintaining uniform flow.
    Keywords: Fluid Mechanics and Thermodynamics; General; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 36-37; NASA/TM-2015-218204
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    Cryoinsulation Material Development to Mitigate Obsolescence Risk for Global Warming Potential Foams (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Cryoinsulation foams currently being qualified for the Space Launch System (SLS) core stage are nonozone- depleting substances (ODP) and are compliant with current environmental regulations. However, these materials contain the blowing agent HFC-245fa, a hydrofluorocarbon (HFC), which is a Global Warming Potential (GWP) substance. In August 2014, the Environmental Protection Agency (EPA) proposed a policy change to reduce or eliminate certain HFCs, including HFC-245fa, in end-use categories including foam blowing agents beginning in 2017. The policy proposes a limited exception to allow continued use of HFC and HFC-blend foam blowing agents for military or space- and aeronautics-related applications, including rigid polyurethane spray foams, but only until 2022.
    Keywords: Launch Vehicles and Launch Operations; Nonmetallic Materials
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 32-33; NASA/TM-2015-218204
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  • 90
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    Booster Interface Loads (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The interaction between shock waves and the wake shed from the forward booster/core attach hardware results in unsteady pressure fluctuations, which can lead to large buffeting loads on the vehicle. This task investigates whether computational tools can adequately predict these flows, and whether alternative booster nose shapes can reduce these loads. Results from wind tunnel tests will be used to validate the computations and provide design information for future Space Launch System (SLS) configurations. The current work combines numerical simulations with wind tunnel testing to predict buffeting loads caused by the boosters. Variations in nosecone shape, similar to the Ariane 5 design (fig. 1), are being evaluated with regard to lowering the buffet loads. The task will provide design information for the mitigation of buffet loads for SLS, along with validated simulation tools to be used to assess future SLS designs.
    Keywords: Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 30-31; NASA/TM-2015-218204
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  • 91
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    Additive Manufacturing Infrared Inspection (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Additive Manufacturing Infrared Inspection Task started the development of a real-time dimensional inspection technique and digital quality record for the additive manufacturing process using infrared camera imaging and processing techniques. This project will benefit additive manufacturing by providing real-time inspection of internal geometry that is not currently possible and reduce the time and cost of additive manufactured parts with automated real-time dimensional inspections which deletes post-production inspections.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 29; NASA/TM-2015-218204
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  • 92
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    Testing of Selective Laser Melting Turbomachinery Applicable to Exploration Upper Stage (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This task is to design, fabricate, and spin test to failure a Ti6-4 hydrogen turbopump impeller that was built using the selective laser melting (SLM) fabrication process (fig. 1). The impeller is sized around upper stage engine requirements. In addition to the spin burst test, material testing will be performed on coupons that are built with the impeller.
    Keywords: Mechanical Engineering; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 28; NASA/TM-2015-218204
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    Q4 Titanium 6-4 Material Properties Development (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This task involves development and characterization of selective laser melting (SLM) parameters for additive manufacturing of titanium-6%aluminum-4%vanadium (Ti-6Al-4V or Ti64). SLM is a relatively new manufacturing technology that fabricates complex metal components by fusing thin layers of powder with a high-powered laser beam, utilizing a 3D computer design to direct the energy and form the shape without traditional tools, dies, or molds. There are several metal SLM technologies and materials on the market today, and various efforts to quantify the mechanical properties, however, nothing consolidated or formal to date. Meanwhile, SLM material fatigue properties of Ti64 are currently highly sought after by NASA propulsion designers for rotating turbomachinery components.
    Keywords: Metals and Metallic Materials; Mechanical Engineering
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 26-27; NASA/TM-2015-218204
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  • 94
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    Source Contaminant Control for the Heat Melt Compactor (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Logistics Reduction and Repurposing project includes the heat melt compactor (HMC), a device that compacts waste containing plastic into a tile that will minimize volume, and may be used as materials for radiation shielding. During the process, a small purge gas stream is directed through the HMC chamber to transport out gasses and humidity released from the process. NASA Marshall Space Flight Center is tasked with developing and delivering a contamination control system to clean the purge gas prior to exhausting it back into the cabin for crew inhalation.
    Keywords: Man/System Technology and Life Support
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 18-19; NASA/TM-2015-218204
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    Advanced Booster Composite Case/Polybenzimidazole Nitrile Butadiene Rubber Insulation Development (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The NASA Engineering and Safety Center (NESC) was requested to examine processing sensitivities (e.g., cure temperature control/variance, debonds, density variations) of polybenzimidazole nitrile butadiene rubber (PBI-NBR) insulation, case fiber, and resin systems and to evaluate nondestructive evaluation (NDE) and damage tolerance methods/models required to support human-rated composite motor cases. The proposed use of composite motor cases in Blocks IA and II was expected to increase performance capability through optimizing operating pressure and increasing propellant mass fraction. This assessment was to support the evaluation of risk reduction for large booster component development/fabrication, NDE of low mass-to-strength ratio material structures, and solid booster propellant formulation as requested in the Space Launch System NASA Research Announcement for Advanced Booster Engineering Demonstration and/or Risk Reduction. Composite case materials and high-energy propellants represent an enabling capability in the Agency's ability to provide affordable, high-performing advanced booster concepts. The NESC team was requested to provide an assessment of co- and multiple-cure processing of composite case and PBI-NBR insulation materials and evaluation of high-energy propellant formulations.
    Keywords: Composite Materials; Launch Vehicles and Launch Operations
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 24-25; NASA/TM-2015-218204
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    Atmosphere Resource Recovery and Environmental Monitoring (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Atmosphere Resource Recovery and Environmental Monitoring (ARREM) is a project focused on evolving existing and maturing emerging 'closed loop' atmosphere revitalization (AR) life support systems that produce clean, breathable air for crewmembers, and developing a suite of low mass, low power environmental monitors to detect and measure air- and waterborne constituents and contaminants. The objective is to improve reliability and efficiency, reduce mass and volume, and increase recovery of oxygen from carbon dioxide created by human metabolism from 43% to greater than 90%. The technology developments under ARREM are vital to extending human space missions from low-Earth orbit like the International Space Station to destinations deeper into space such as Mars where dependency on Earth for resupply of maintenance items and critical life support elements such as water and oxygen is not possible. The primary goal of the ARREM project is to demonstrate that systems meet the more stringent performance parameters for deep space exploration and are compatible with other systems within closed loop life support through a series of integrated tests performed in an environmental test chamber capable of simulating human metabolic activities and measuring systems outputs.
    Keywords: Man/System Technology and Life Support
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 20-21; NASA/TM-2015-218204
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    Near-Earth Asteroid Scout (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Near-Earth asteroids (NEAs) are easily accessible objects in Earth's vicinity. As NASA continues to refine its plans to possibly explore NEAs with humans, initial reconnaissance with comparatively inexpensive robotic precursors is necessary. Obtaining and analyzing relevant data about these bodies via robotic precursors before committing a crew to visit an NEA will significantly minimize crew and mission risk, as well as maximize exploration return potential. The NASA Marshall Space Flight Center (MSFC) and NASA Jet Propulsion Laboratory are jointly developing the Near-Earth Asteroid Scout (NEAS) utilizing a low-cost CubeSat platform in response to the current needs for affordable missions with exploration science value. The mission is enabled by the use of an 85-sq m solar sail being developed by MSFC (figs. 1 and 2).
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Design, Testing and Performance
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 14-15; NASA/TM-2015-218204
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    Deep Space Habitat Concept Demonstrator (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This project will develop, integrate, test, and evaluate Habitation Systems that will be utilized as technology testbeds and will advance NASA's understanding of alternative deep space mission architectures, requirements, and operations concepts. Rapid prototyping and existing hardware will be utilized to develop full-scale habitat demonstrators. FY 2014 focused on the development of a large volume Space Launch System (SLS) class habitat (Skylab Gen 2) based on the SLS hydrogen tank components. Similar to the original Skylab, a tank section of the SLS rocket can be outfitted with a deep space habitat configuration and launched as a payload on an SLS rocket. This concept can be used to support extended stay at the Lunar Distant Retrograde Orbit to support the Asteroid Retrieval Mission and provide a habitat suitable for human missions to Mars.
    Keywords: Launch Vehicles and Launch Operations; General
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 12-13; NASA/TM-2015-218204
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    Lunar Flashlight (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: The Lunar Flashlight is a Jet Propulsion Laboratory project, with NASA Marshall Space Flight Center (MSFC) serving as the principal investigator and providing the solar sail propulsion system. The goal of Lunar Flashlight is to determine the presence and abundance of exposed lunar water ice within permanently shadowed regions (PSRs) at the lunar south pole, and to map its concentration at the 1-2 kilometer scale to support future exploration and use. After being ejected in cis-lunar space by the launch vehicle, Lunar Flashlight deploys solar panels and an 85-square-meter solar sail and maneuvers into a low-energy transfer to lunar orbit. The solar sail and attitude control system work to bring the satellite into an elliptical polar orbit, spiraling down over a period of 18 months to a perilune of 30-10 kilometers above the south pole for data collection. Lunar Flashlight uses its solar sail to shine reflected sunlight onto the lunar surface, measuring surface reflectance with a four-filter point spectrometer. The spectrometer measures water ice absorption features (1.5, 1.95 microns) and the continuum between them (1.1, 1.9 microns). The ratios of water ice bands to the continuum will provide a measure of the abundance of surface frost and its variability across PSRs. Water ice abundance will be correlated with other data from previous missions, such as the Lunar Reconnaissance Orbiter and Lunar Crater Observation and Sensing Satellite, to provide future human and robotic explorers with a map of potential resources. The mission is enabled by the use of an 85-square-meter solar sail being developed by MSFC.
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 16-17; NASA/TM-2015-218204
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    Nuclear Thermal Propulsion (2015)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: Development efforts in the United States for nuclear thermal propulsion (NTP) systems began with Project Rover (1955-1973) which completed 22 high-power rocket reactor tests. Results indicated that an NTP system with a high thrust-to-weight ratio and a specific impulse greater than 900 s would be feasible. John F. Kennedy, in his historic special address to Congress on the importance of Space on May 25, 1961, said, "First, I believe that this nation should commit itself to achieving the goal, before this decade is out, of landing a man on the Moon and returning him safely to the Earth..." This was accomplished. He also said, "Secondly ... accelerate development of the Rover nuclear rocket. This gives promise of someday providing a means for even more exciting and ambitious exploration of space... to the very end of the solar system itself." The current NTP project focuses on demonstrating the affordability and viability of a fully integrated NTP system with emphasis on fuel fabrication and testing and an affordable development and qualification strategy. The goal is to enable NTP to be considered a mainstream option for supporting human Mars and other missions beyond Earth orbit.
    Keywords: Spacecraft Propulsion and Power
    Type: George C. Marshall Space Flight Center Research and Technology Report 2014; 10-11; NASA/TM-2015-218204
    Format: application/pdf
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