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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (5)
  • Mass Spectra  (2)
  • Complexes of Titanium(IV), Vanadium(IV), Manganese(IV), Tin(IV)  (1)
  • Crystal Structure  (1)
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  • 1
    Digitale Medien
    Digitale Medien
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 621 (1995), S. 671-674 
    ISSN: 0044-2313
    Schlagwort(e): N,N,N′,N′-Tetrakis(2-hydroxybenzyl)ethylenediamine ; Complexes of Titanium(IV), Vanadium(IV), Manganese(IV), Tin(IV) ; Mass Spectra ; Mössbauer Data ; Crystal Structure ; Chemistry ; Inorganic Chemistry
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Chemie und Pharmazie
    Beschreibung / Inhaltsverzeichnis: Complexes with N,N,N′,N′-Tetrakis(2-hydroxybenzyl)ethylenediamine (H4tben). Crystal Structure of Ti(tben)The complexes of N,N,N′,N′-tetrakis(2-hydroxybenzyl)-ethylenediamine with titanium(IV), vanadium(IV), manganese(IV), and tin(IV) were synthesized and characterized by mass spectrometry. The Mössbauer date were evaluated for the tin compound. The molecular structure of the titanium(IV) complex was determined by X-ray structural analysis, crystallographic data see “Inhaltsübersicht”.
    Notizen: Es wurden die Komplexe von N,N,N′,N′-Tetrakis(2-hydroxybenzyl)ethylendiamin mit Titan(IV), Vanadium(IV), Mangan(IV) und Zinn(IV) hergestellt und massenspektrometrisch charakterisiert. Für die Zinn-Verbindung wurden die Mössbauer-Daten ermittelt. Die Molekülstruktur des Titan(IV)-Komplexes wurde röntgenstrukturanalytisch bestimmt. N,N,N′,N′-Tetrakis(2-hydroxybenzyl)ethylendiaminato(4-)titan(IV): Raumgruppe P21/c (Nr. 14), Z = 4, 3949 Zahl der beobachteten Intensitäten, R = 0,0539, Gitterabmessung bei 20°C; a = 10,447(3) Å, b = 20,668(5) Å, c = 13,420(3) Å, b̃ = 101,93(5) Å
    Zusätzliches Material: 1 Ill.
    Materialart: Digitale Medien
    Standort Signatur Erwartet Verfügbarkeit
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  • 2
    ISSN: 0044-2313
    Schlagwort(e): Manganese(IV) Chelates, Salicylaldehyde benzoylhydrazone and salicylhydrazone ; Mass Spectra ; Crystal Structure, Acetylacetonato-salicylaldehydebenzoylhydrazonato(2-)-methanol-manganese(III) ; Chemistry ; Inorganic Chemistry
    Quelle: Wiley InterScience Backfile Collection 1832-2000
    Thema: Chemie und Pharmazie
    Beschreibung / Inhaltsverzeichnis: Manganese(IV) Complexes with Tridentate Diacidic Ligands. Crystal Structure of Acetyl-acetonato-salicylaldehydebenzoylhydrazonato(2-)-methanol-manganese(III)The manganese(IV) chelates of salicylaldehyde benzoylhydrazone and salicylaldehyde salicylhydrazone were synthesized by ligand exchange reactions using bis(acetylacetonato)manganese(II), tris(acetylacetonato)manganese(III) as well as manganese(III) acetate. The brown complexes show the expected molecular ions in the APCI mass spectra. As an intermediate compound acetyacetonato-salicylaldehydebenzoylhydrazonato(2-)-methanol-manganese(III) was isolated and characterized by X-ray structural analysis. Crystallographic data see “Inhaltsübersicht”.
    Notizen: Durch Ligandenaustauschreaktion von Bis(acetylacetonato)mangan(II) und Tris(acetylacetonato)mangan(III) bzw. Mangan(III)-acetat mit Salicylaldehydbenzoylhydrazon und -salicylhydrazon wurden die Mangan(IV)-Chelate dieser Liganden dargestellt. Die braunen Verbindungen zeigen im APCI-positiv Massenspektrum die erwarteten Molekülionen. Für das Zwischenprodukt Acetylacetonato-salicylaldehydbenzoylhydrazonato(2-)-methanol-mangan(III) wurde die Kristall- und Molekülstruktur bestimmt: Gitterabmessungen bei 293 K; a = 754,3(2) pm, b = 1 027,3(6) pm, c = 1 357,4(5) pm, α = 79,64(4)°, β = 76,51(3)°, γ = 70,45(4)°, Raumgruppe P1 (Nr. 2), Z = 2, 3297 unabhängige Reflexe, R = 3,84%.
    Zusätzliches Material: 4 Ill.
    Materialart: Digitale Medien
    Standort Signatur Erwartet Verfügbarkeit
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  • 3
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-06-28
    Beschreibung: The report discusses momentum management for a large space structure with the structure selected configuration being the Initial Orbital Configuration of the dual-keel Space Station. The external torques considered were gravity gradient and aerodynamic torques. The goal of the momentum management scheme developed is to remove the bias components of the external torques and center the cyclic components of the stored angular momentum. The scheme investigated is adaptive to uncertainties of the inertia tensor and requires only approximate knowledge of principal moments of inertia. Computational requirements are minimal and should present no implementation problem in a flight-type computer. The method proposed is shown to be effective in the presence of attitude control bandwidths as low as 0.01 radian/sec.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 87-2596
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 4
    facet.materialart.
    Unbekannt
    In:  Other Sources
    Publikationsdatum: 2019-06-28
    Beschreibung: This paper discusses momentum management for the CDG Planar Space Platform. The external torques on the Space Station are assumed to be gravity gradient and aerodynamic with both having bias and cyclic terms. The integrals of the cyclic torques are the cyclic momenti which will be stored in the momentum storage actuator. Various techniques to counteract the bias torques and center the cyclic momentum were investigated including gravity gradient desaturation by adjusting vehicle attitude, aerodynamic desaturation using solar panels and radiators and the deployment of flat plates at the end of long booms generating aerodynamic torques.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: AIAA PAPER 85-0031
    Format: text
    Standort Signatur Erwartet Verfügbarkeit
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  • 5
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: Momentum management is discussed for a Large Space Structure (LSS) with the structure selected configuration being the Initial Orbital Configuration (IOC) of the dual keel space station. The external forces considered were gravity gradient and aerodynamic torques. The goal of the momentum management scheme developed is to remove the bias components of the external torques and center the cyclic components of the stored angular momentum. The scheme investigated is adaptive to uncertainties of the inertia tensor and requires only approximate knowledge of principle moments of inertia. Computational requirements are minimal and should present no implementation problem in a flight type computer and the method proposed is shown to be effective in the presence of attitude control bandwidths as low as .01 radian/sec.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA-CR-179085 , NAS 1.26:179085
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 6
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: Momentum management for the CDG planar space platform is discussed. It is assumed that the external torques on the space station are gravity gradient and aerodynamic, both have bias and cyclic terms. The integrals of the cyclic torques are the cyclic momenti which will be stored in the momentum storage actuator. Techniques to counteract the bias torques and center the cyclic momentum and gravity gradient desaturation by adjusting vehicle attitude, aerodynamic desaturation using solar panels and radiators and the deployment of flat plates at the end of long booms generating aerodynamic torques are investigated.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA-CR-174065 , NAS 1.26:174065
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 7
    facet.materialart.
    Unbekannt
    In:  CASI
    Publikationsdatum: 2019-07-13
    Beschreibung: The report discusses momentum management for the CDG Planar Space Platform. The external torques on the Space Station are assumed to be gravity gradient and aerodynamic with both having bias and cyclic terms. The integrals of the cyclic torques are the cyclic momenti which will be stored in the momentum storage actuator. Various techniques to counteract the bias torques and center the cyclic momentum were investigated including gravity gradient desaturation by adjusting vehicle attitude, aerodynamic desaturation using solar panels and radiators and the deployment of flat plates at the end of long booms generating aerodynamic torques.
    Schlagwort(e): SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Materialart: NASA-CR-171256 , NAS 1.26:171256
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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