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  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (2)
  • bic Book Industry Communication::H Humanities::HP Philosophy::HPQ Ethics & moral philosophy
  • 1
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    Unknown
    De Gruyter
    Publication Date: 2024-04-08
    Description: Gibt es überzeugende Überforderungseinwände gegen anspruchsvolle moralische Auffassungen? In der vorliegenden Abhandlung werden Überforderungseinwände sorgfältig charakterisiert, systematisch eingeordnet und argumentativ verteidigt. Unter Berücksichtigung der wichtigsten Beiträge zum Thema wird gezeigt, dass gewisse Moraltheorien oder -prinzipien zurückgewiesen werden können, weil sie zu viel von einzelnen Personen verlangen. Wenn moralische Forderungen die Grenzen dessen übersteigen, was vernünftigerweise von Menschen erwartet werden kann, dann lassen sie sich als zu anspruchsvoll kritisieren. Im Hinblick darauf, was für eine erfolgreiche Verteidigung von Überforderungseinwänden erforderlich ist, werden intuitionen-, theorie- und erklärungsbasierte Strategien geprüft. Dabei wird die These vertreten, dass Überforderungseinwände verteidigt werden können, wenn sich eine grundlegende und eigenständige Erklärung dafür finden lässt, weshalb anspruchsvolle moralische Auffassungen überfordernd sein können. In Auseinandersetzung mit den Ansätzen von Bernard Williams, Douglas W. Portmore und Samuel Scheffler wird daher ein entsprechender Vorschlag ausgearbeitet, der weder zu schwach noch zu stark oder zu wenig gut begründet ist.
    Keywords: Ethik ; Überforderungseinwände ; bic Book Industry Communication::H Humanities::HP Philosophy::HPC History of Western philosophy ; bic Book Industry Communication::H Humanities::HP Philosophy::HPQ Ethics & moral philosophy ; thema EDItEUR::Q Philosophy and Religion::QD Philosophy::QDH Philosophical traditions and schools of thought ; thema EDItEUR::Q Philosophy and Religion::QD Philosophy::QDT Topics in philosophy::QDTQ Ethics and moral philosophy
    Language: German
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  • 2
    Publication Date: 2011-08-24
    Description: Telemetry data are presented for two communications hybrid satellites, Spacenet I and Spacenet II, collected to determine the long-term temperature trend and associated solar absorptance degradation of the optical solar reflectors (OSRs). A thermal model was used to calculate the thermal sensitivity of various OSR components to changes in the solar absorptance and to determine absolute values of solar absorptance. The separation of the data into sunlit and nonsunlit periods made it possible to confirm the hypothesis that degradation occurs under the catalytic activity of direct sunlight on the spacecraft contaminants. The differences found between the degradation rates for Spacenet-I and Spacenet-II satellites and between the present results and published reports on other satellites are considered to be related to variations in the volume of spacecraft contaminants.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 5; p. 741-745.
    Format: text
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  • 3
    Publication Date: 2019-07-13
    Description: This document presents the results of an extensive, low perigee, orbital aerodynamic heating study undertaken in support of the Atmosphere Explorer-C Temperature Alarm. Based upon in-flight orbital temperature data from the Temperature Alarm tungsten resistance wire thermometer, aerodynamic heating rates have been determined for eight selected orbits by means of a reduced thermal analytical model verified by both ground test and flight data. These heating rates are compared with the classical free molecular and first order collision regime values. It has been concluded that, for engineering purposes, the aerodynamic heating rate of atmospheric gases at perigee altitudes between 170 and 135 km on pure tungsten wire is 30 to 60% of the value set by the classical free molecular limit. Relative to the more usual orbital thermal input attributable to direct solar radiation, the aerodynamic heating rate at the lowest altitude attempted with the spacecraft despun (135 km) is the equivalent of about 1.2 solar constants incident on a tungsten wire with a solar absorptivity of 0.85.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Heat Transfer and Fluid Mechanics Institute, Meeting; Jun 21, 1976 - Jun 23, 1976; Davis, CA
    Format: text
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