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  • AIRCRAFT  (316)
  • Inorganic Chemistry  (236)
  • 1970-1974  (552)
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  • 1
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests of supersonic rotors designed to reduce forward propagating pressure waves and the accompanying blade passing tones and multiple pure tones showed the wave propagation and noise reduction to have been obtained at the expense of increased noise radiation rearward. Outlet guide vanes served to muffle the noise propagating rearwards, but did not affect forward propagation at all.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-TN-D-7096 , E-6953
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
    Digitale Medien
    Digitale Medien
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 406 (1974), S. 228-234 
    ISSN: 0044-2313
    Schlagwort(e): Chemistry ; Inorganic Chemistry
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Chemie und Pharmazie
    Beschreibung / Inhaltsverzeichnis: Reactions of (CH3)3Si—NSN—Si(CH3)3 for Preparation of New Sulfur-Nitrogen CompoundsR3Si—NSN—SiR3 (1) [R = CH3] and chlorine react under formation of R3Si—NSN—Cl (3). From 1 and trifluoromethyl acetylchloride CF3CO(S3N3) is obtained, and 1 with sulfur dichloride yields S(NSN—SiR3)2 (5). This compound reacts with SCl2under formation of S4N4. A new method for the preparation of S( = NSiR3)3 (6) is given. Investigation of the chemical bonds of 5 by ESCA measurements was tried.
    Notizen: Die Reaktion des R3Si—NSN—SiR3 (1) [R = CH3] mit Chlor führt zum R3Si—NSN—Cl (3). Mit Trifluoracetylchlorid erhält man aus 1 CF3CO(S3N3) und mit Schwefeldichlorid S(NSNSiR3)2 (5), welches sich mit weiterem Schwefeldichlorid unter Ringschluß zu S4N4 umsetzt. Eine günstige Darstellungsmethode für S(=NSiR3)3 (6) wird mitgeteilt. Durch ESCA-Spektren werden die Bindungsverhältnisse in 5 zu ermitteln versucht.
    Zusätzliches Material: 1 Tab.
    Materialart: Digitale Medien
    Standort Signatur Erwartet Verfügbarkeit
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  • 3
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2006-03-27
    Beschreibung: A STOL ride-control development program has been initiated with the objective of generating ride-control technology through development and evaluation of an active control system specifically designed to provide ride smoothing on a STOL vehicle. Although much can be learned through analysis, there are deficiencies in technology for translating analysis results into operating hardware. The general approach being followed is to select an existing STOL vehicle for trial and then carry out a study to establish feasibility of a control system or systems to smooth the ride and generate system trade-off data.
    Schlagwort(e): AIRCRAFT
    Materialart: STOL Technol.; p 215-226
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
    Publikationsdatum: 2016-06-07
    Beschreibung: Results of a design and flight test program conducted to define the effect of rotating pushrod damping on stall-flutter induced control loads are presented. The CH-54B helicopter was chosen as the test aircraft because it exhibited stall induced control loads. Damping was introduced into the CH-54B control system by replacing the standard pushrod with spring-damper assemblies. Design features of the spring-damper are described and the results of a dynamic analysis are shown which define the pushrod stiffness and damping requirements. Flight test measurements taken at 47,000 lb gross weight with and without the damper are presented. The results indicate that the spring-damper pushrods reduced high frequency, stall-induced rotating control loads by almost 50%. Fixed system control loads were reduced by 40%. Handling qualities in stall were unchanged, as expected.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA. Ames Res. Center Rotorcraft Dyn.; p 223-232
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
    Publikationsdatum: 2019-06-27
    Beschreibung: Propulsion systems proposed for the next generation of long-range transport aircraft will utilize advanced technology to reduce the noise to levels that will be inoffensive to the community. Additional reductions can be realized by adopting steeper glide slopes during the landing approach. The aircraft dynamic characteristics and methods of obtaining rapid engine response during the go-around maneuver from an aborted landing approach are identified and discussed. The study concludes that the present levels of flight safety will not be compromised by the steeper approach.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-CR-121243 , PWA-4693
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
    Publikationsdatum: 2019-06-27
    Beschreibung: Investigations were conducted to evaluate the relative benefits attainable through the exploitation of advanced technologies and to identify future research and development efforts required to permit the application of selected technologies to transport aircraft entering commercial operation in 1985. Results show that technology advances, particularly in the areas of composite materials, supercritical aerodynamics, and active control systems, will permit the development of long-range, high-payload commercial transports operating at high-subsonic speeds with direct operating costs lower than those of current aircraft. These advanced transports also achieve lower noise levels and lower engine pollutant emissions than current transports. Research and development efforts, including analytical investigations, laboratory test programs, and flight test programs, are required in essentially all technology areas to achieve the potential technology benefits.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-CR-112089
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
    Publikationsdatum: 2019-06-27
    Beschreibung: Noise attenuation was measured for several types of cylindrical suppressors that use a duct lining composed of honeycomb cells covered with a perforated plate. The experimental technique used gave attenuation data that were repeatable and free of noise floors and other sources of error. The suppressor length, the effective acoustic diameter, suppressor shape and flow velocity were varied. The agreement among the attenuation data and two widely used analytical models was generally satisfactory. Changes were also made in the construction of the acoustic lining to measure their effect on attenuation. One of these produced a very broadband muffler.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-TM-X-2652 , E-7009
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 8
    Publikationsdatum: 2019-07-27
    Schlagwort(e): AIRCRAFT
    Materialart: AIAA PAPER 72-985 , American Institute of Aeronautics and Astronautics, Atmospheric Flight Mechanics Conference; Sept. 11-13, 1972; Palo Alto, CA
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 9
    Publikationsdatum: 2019-06-27
    Beschreibung: The potential benefits of flight path control to optimize performance and/or reduce the noise of a tilt-rotor aircraft operating in the takeoff and landing phases of flight are investigated. A theoretical performance-acoustic model is developed and then mathematically flown to yield representative takeoff and landing profiles. Minimum-time and minimum-fuel trajectories are compared to proposed noise-abatement profiles to assess the reductions in annoyance possible through flight path control. Significant reductions are feasible if a nearly vertical-takeoff flight profile is flown near the landing site; however, the time expended and fuel consumed increase.
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-CR-2034
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 10
    Publikationsdatum: 2019-06-27
    Beschreibung: Flight characteristics of jet-flap STOL transport aircraft during approach and landing
    Schlagwort(e): AIRCRAFT
    Materialart: NASA-TN-D-6225 , L-7582
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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