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Künstlerische Einlassungen auf den öffentlichen Raum folgten lange Zeit dem Prinzip des subkulturellen Widerstands. Nur in dem strategischen, invasiven Akt der Intervention sah man noch die Möglichkeit einer weitgreifenden Kritik am kulturellen System. Begriffe wie Cultural Hacking, Guerilla Marketing, Adbusting, Konsumguerilla oder parasitäre Strategien prägten eine rebellische Auffassung der künstlerischen Einmischung. Gleichzeitig konnten diese Haltungen aufgrund ihres rebellischen Chics mühelos von dem, was sie kritisierten, aufgenommen und vereinnahmt werden. Künstlerisches Handeln verharrt jedoch nicht in der Pose des Widerständigen, sondern arbeitet kontinuierlich an der Problematisierung und Gestaltung der öffentlichen Wahrnehmung. Viele Interventionen der Gegenwartskunst weisen unterschiedliche Grade der Ästhetisierung, der Partizipation und der Kooperation in der Auseinandersetzung mit dem öffentlichen Raum auf. Das wache Agieren im urbanen Kontext, die Irritation von Erwartungshaltungen, Fake und Desillusionierungsarbeit verstehen sich als künstlerische Arbeit an der Sensibilisierung der Wahrnehmung.
Pandemische Momente
(2022)
The optical properties of the thin metalized polymer films that are projected for solar sails are assumed to be affected by the erosive effects of the space environment. Their degradation behavior in the real space environment, however, is to a considerable degree indefinite, because initial ground test results are controversial and relevant inspace tests have not been made so far. The standard optical solar sail models that are currently used for trajectory design do not take optical degradation into account, hence its potential effects on trajectory design have not been investigated so far. Nevertheless, optical degradation is important for high-fidelity solar sail mission design, because it decreases both the magnitude of the solar radiation pressure force acting on the sail and also the sail control authority. Therefore, we propose a simple parametric optical solar sail degradation model that describes the variation of the sail film’s optical coefficients with time, depending on the sail film’s environmental history, i.e., the radiation dose. The primary intention of our model is not to describe the exact behavior of specific film-coating combinations in the real space environment, but to provide a more general parametric framework for describing the general optical degradation behavior of solar sails. Using our model, the effects of different optical degradation behaviors on trajectory design are investigated for various exemplary missions.
An Interstellar – Heliopause mission using a combination of solar/radioisotope electric propulsion
(2011)
There is common agreement within the scientific community that in order to understand our local galactic environment it will be necessary to send a spacecraft into the region beyond the solar wind termination shock. Considering distances of 200 AU for a new mission, one needs a spacecraft travelling at a speed of close to 10 AU/yr in order to keep the mission duration in the range of less than 25 yrs, a transfer time postulated by ESA.Two propulsion options for the mission have been proposed and discussed so far: the solar sail propulsion and the ballistic/radioisotope electric propulsion. As a further alternative, we here investigate a combination of solar-electric propulsion and radioisotope-electric propulsion. The solar-electric propulsion stage consists of six 22 cm diameter “RIT-22”ion thrusters working with a high specific impulse of 7377 s corresponding to a positive grid voltage of 5 kV. Solar power of 53 kW BOM is provided by a light-weight solar array. The REP-stage consists of four space-proven 10 cm diameter “RIT-10” ion thrusters that will be operating one after the other for 9 yrs in total. Four advanced radioisotope generators provide 648 W at BOM. The scientific instrument package is oriented at earlier studies. For its mass and electric power requirement 35 kg and 35 W are assessed, respectively. Optimized trajectory calculations, treated in a separate contribution, are based on our “InTrance” method.The program yields a burn out of the REP stage in a distance of 79.6 AU for a usage of 154 kg of Xe propellant. With a C3 = 45,1 (km/s)2 a heliocentric probe velocity of 10 AU/yr is reached at this distance, provided a close Jupiter gravity assist adds a velocity increment of 2.7 AU/yr. A transfer time of 23.8 yrs results for this scenario requiring about 450 kg Xe for the SEP stage, jettisoned at 3 AU. We interpret the SEP/REP propulsion as a competing alternative to solar sail and ballistic/REP propulsion. Omiting a Jupiter fly-by even allows more launch flexibility, leaving the mission duration in the range of the ESA specification.