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  • Inorganic Chemistry  (165)
  • Aircraft Propulsion and Power
  • Aircraft Stability and Control
  • 2005-2009  (45)
  • 1950-1954  (14)
  • 1930-1934  (70)
  • 1915-1919
  • 1910-1914
Collection
Keywords
Publisher
Years
Year
  • 1
    Electronic Resource
    Electronic Resource
    Wechselseitige elektromagnetische Masse und die Struktur des Atoms (1916)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 95 (1916), S. 1-19 
    Details
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Die Atomgewichte der ersten 27 Elemente, beginnend mit Helium, sind nicht Vielfache des Atomgewichts von Wasserstoff mit einer ganzen Zahl, wie es sein müßte, wenn PROUTS ursprüngliche Hypothese in ihrer numerischen Form richtig wäre. Dies kann ausgedrückt werden durch die Feststellung, daß die Atomgewichte, bezogen auf Wasserstoff, nicht ganze Zahlen sind. Wenn man jedoch diese Atomgewichte kritisch prüft, so findet man, daß sie von den entsprechenden ganzen Zahlen um einen fast konstanten Prozentsatz abweichen, daß die Abweichung negativ ist und im Mittel den Wert -0.77%, besitzt.
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19160950102
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  • 2
    Electronic Resource
    Electronic Resource
    Das Wasserstoff-Heliumsystem und die Struktur der komplexen Atome (1916)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 95 (1916), S. 20-38 
    Details
    ISSN: 0863-1786
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: 1. Der Grundgedanke dieser zweiten Mitteilung uber die Atomstruktur ist folgender: Das Gesetz, welches bei den Beziehungen von Atomgewicht und Valenz zwischen Gliedern einer jeden radioaktiven Reihe Anwendung findet, trifft auch für die leichteren Atome zu. Bei einer radioaktiven Reihe bedingt der Verlust eines Teilchens mit einer Masse von 4 eine Abnahme der Wertigkeit um 2 und verschiebt so das Element um 2 Gruppen des periodischen Systems nach links, während gleichzeitig die Atomzahl um 2 vermindert wird. Wenn dies auch für die leichteren Elemente, beginnend mit Helium, zutrifft, so müßte die Zunahme um das Gewicht eines Heliumatome für jeden Anwachs um 2 in der Atomzahl die Atomgewichte der Elemente liefern, die zu den Gruppen mit geraden Zahlen gehören. Die nach diesem Verfahren abgeleiteten Atomgewichte stimmen im ganzen mit den experimentell festgestellten Werten überein, woraus hervorgeht, daß die Theorie den Tatsachen entspricht.
    Additional Material: 4 Tab.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19160950103
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  • 3
    Electronic Resource
    Electronic Resource
    Konstitution des durch Nitrieren erhältlichen Nitro-2.6-dimethyl-benzimidazols (1911)
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 44 (1911), S. 2999-3005 
    Details
    ISSN: 0365-9496
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cber.191104403149
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  • 4
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    Brush Seal Arrangement for the RS-68 Turbopump Set (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The nature of the RS-68 turbopumps requires that the hydrogen seals separating the pump from the turbine must have extremely low levels of leakage and be contained in small packages. Conventional seal technologies are not able to reasonably satisfy such design requirements. A review of experimental measurements and analysis publications suggests that brush seals are well suited for the design requirements. Brush seals are shown to have less leakage than conventional labyrinth and damper seals and have no adverse effects on the rotordynamics of the machine. The bulk-flow analysis presented by Hendricks et al. is used as a guideline to create a spreadsheet that provides mass flow through the seal and heat generated by the rubbing contact of the bristles on the shaft. The analysis is anchored to published data for LN2 and LH2 leakage tests. Finally, the analysis is used to design seals for both applications. It is observed that the most important analysis parameter is the thickness of the bristle pack and its relationship to seal clearance, lay angle and pressure drop.
    Keywords: Aircraft Propulsion and Power
    Type: Seals/Secondary Fluid Flows Workshop 1997; Volume I; 165-196; NASA/CP-2006-214329/VOL1
    Format: application/pdf
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  • 5
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    A Spreadsheet for the Mixing of a Row of Jets with a Confined Crossflow (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An interactive computer code, written with a readily available software program, Microsoft Excel (Microsoft Corporation, Redmond, WA) is presented which displays 3 D oblique plots of a conserved scalar distribution downstream of jets mixing with a confined crossflow, for a single row, double rows, or opposed rows of jets with or without flow area convergence and/or a non-uniform crossflow scalar distribution. This project used a previously developed empirical model of jets mixing in a confined crossflow to create an Microsoft Excel spreadsheet that can output the profiles of a conserved scalar for jets injected into a confined crossflow given several input variables. The program uses multiple spreadsheets in a single Microsoft Excel notebook to carry out the modeling. The first sheet contains the main program, controls for the type of problem to be solved, and convergence criteria. The first sheet also provides for input of the specific geometry and flow conditions. The second sheet presents the results calculated with this routine to show the effects on the mixing of varying flow and geometric parameters. Comparisons are also made between results from the version of the empirical correlations implemented in the spreadsheet and the versions originally written in Applesoft BASIC (Apple Computer, Cupertino, CA) in the 1980's.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2005-213137 , E-14651
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Acoustic Characteristics of Various Treatment Panel Designs Specific to HSCT Mixer-Ejector Application (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The development process of liner design methodology is described in several reports. The results of the initial effort of concept development, screening, laboratory testing of various liner concepts, and preliminary correlation (generic data) are presented in a report Acoustic Characteristics of Various Treatment Panel Designs for HSCT Ejector Liner Acoustic Technology Development Program. The second phase of laboratory test results of more practical concepts and their data correlations are presented in this report (product specific). In particular, this report contains normal incidence impedance measurements of several liner types in both a static rig and in a high temperature flow duct rig. The flow duct rig allows for temperatures up to 400 F with a grazing flow up to Mach 0.8. Measurements of impedance, DC flow resistance, and in the flow rig cases, impact of the liner on boundary layer profiles are documented. In addition to liner rig tests, a limited number of tests were made on liners installed in a mixer-Ejector nozzle to confirm the performance of the liner prediction in an installed configuration.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-2006-214401 , E-15680
    Format: application/pdf
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  • 7
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    Acoustic Characteristics of Various Treatment Panel Designs for HSCT Ejector Liner Acoustic Technology Development Program (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The objectives of the initial effort (Phase I) of HSR Liner Technology Program, the selection of promising liner concepts, design and fabrication of these concepts for laboratory tests, testing these liners in the laboratory by using impedance tube and flow ducts, and developing empirical impedance/suppression correlation, are successfully completed. Acoustic and aerodynamic criteria for the liner design are established. Based on these criteria several liners are designed. The liner concepts designed and fabricated include Single-Degree-of-Freedom (SDOF), Two-Degree-of-Freedom (2DOF), and Bulk Absorber. Two types of SDOF treatment are fabricated, one with a perforated type face plate and the other with a wiremesh (woven) type faceplate. In addition, special configurations of these concepts are also included in the design. Several treatment panels are designed for parametric study. In these panels the facesheets of different porosity, hole diameter, and sheet thickness are utilized. Several deep panels (i.e., 1 in. deep) are designed and instrumented to measure DC flow resistance and insitu impedance in the presence of grazing flow. Basic components of these panels (i.e., facesheets, bulk materials, etc.) are also procured and tested. The results include DC flow resistance, normal impedance, and insertion loss.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/CR-2006-214399 , E-15678
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Explicit Finite Element Modeling of Multilayer Composite Fabric for Gas Turbine Engine Containment Systems, Phase II (2009)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A team consisting of Arizona State University, Honeywell Engines, Systems & Services, the National Aeronautics and Space Administration Glenn Research Center, and SRI International collaborated to develop computational models and verification testing for designing and evaluating turbine engine fan blade fabric containment structures. This research was conducted under the Federal Aviation Administration Airworthiness Assurance Center of Excellence and was sponsored by the Aircraft Catastrophic Failure Prevention Program. The research was directed toward improving the modeling of a turbine engine fabric containment structure for an engine blade-out containment demonstration test required for certification of aircraft engines. The research conducted in Phase II began a new level of capability to design and develop fan blade containment systems for turbine engines. Significant progress was made in three areas: (1) further development of the ballistic fabric model to increase confidence and robustness in the material models for the Kevlar(TradeName) and Zylon(TradeName) material models developed in Phase I, (2) the capability was improved for finite element modeling of multiple layers of fabric using multiple layers of shell elements, and (3) large-scale simulations were performed. This report concentrates on the material model development and simulations of the impact tests.
    Keywords: Aircraft Propulsion and Power
    Type: PB2010-103422 , DOT/FAA/AR-08/37,P3
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Attitude Control for an Aero-Vehicle Using Vector Thrusting and Variable Speed Control Moment Gyros (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Stabilization of passively unstable thrust-levitated vehicles can require significant control inputs. Although thrust vectoring is a straightforward choice for realizing these inputs, this may lead to difficulties discussed in the paper. This paper examines supplementing thrust vectoring with Variable-Speed Control Moment Gyroscopes (VSCMGs). The paper describes how to allocate VSCMGs and the vectored thrust mechanism for attitude stabilization in frequency domain and also shows trade-off between vectored thrust and VSCMGs. Using an H2 control synthesis methodology in LMI optimization, a feedback control law is designed for a thrust-levitated research vehicle and is simulated with the full nonlinear model. It is demonstrated that VSCMGs can reduce the use of vectored thrust variation for stabilizing the hovering platform in the presence of strong wind gusts.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2005-5972 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: application/pdf
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  • 10
    Electronic Resource
    Electronic Resource
    Über die Produkte die bei der Auflösung des Phosphorpentoxyds in Wasser entstehen (1910)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 69 (1910), S. 215-216 
    Details
    ISSN: 0863-1778
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19100690115
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