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Soziale Netzwerke sind aus dem Alltag nicht wegzudenken. Es vergeht keine Sekunde, in der nicht abertausende Status-Updates, Kommentare und Nachrichten rund um den Globus versendet werden. Die Stellung als Informations- und Kommunikationsmedium macht die Betreiber solcher Plattformen - zahlreichen Skandalen zum Trotz - zu den Internetgiganten unserer Zeit. Insoweit ist es nicht verwunderlich, dass die Datenschutz-Grundverordnung (DSGVO) auch und gerade mit dem Ziel angetreten ist, soziale Netzwerke zu regulieren.
Die datenschutzrechtliche Diskussion fokussierte sich vor allem auf die Betreiber von sozialen Netzwerken. Unter welchen Umständen welches Recht auf wen Anwendung findet, wer für welche Tätigkeiten verantwortlich ist, und unter welchen Bedingungen eine Verarbeitung rechtmäßig ist, wurde bislang nur pauschal beantwortet. Bei Web 2.0-Plattformen wirkt jedoch eine Vielzahl von Beteiligten zusammen, bei denen Art der Verarbeitung, verfolgte Zwecke und mögliche Rechtsgrundlagen divergieren. Dies macht eine sorgfältige Differenzierung notwendig. Das vorliegende Werk analysiert die Handlungen von Netzwerkbetreibern, Fansite-Betreibern und Nutzern in sozialen Netzwerken und zeigt gleichermaßen Voraussetzungen wie praxistaugliche Lösungen für eine datenschutzkonforme Datenverarbeitung in Hinblick auf alle Beteiligten unter der DSGVO auf.
Schwerpunkte sind die Anwendbarkeit der DSGVO, der Umfang der Verantwortlichkeit der einzelnen Akteure und die Rechtmäßigkeit der Verarbeitung. Daneben werden auch jene Besonderheiten der DSGVO, die spezifische Relevanz für soziale Netzwerke entfalten, ausführlich behandelt. Hierzu zählt etwa das Haushaltsprivileg, die Verarbeitung "sensibler" Daten, das Kopplungsverbot, das Recht auf Datenübertragbarkeit, Privacy by Default oder das vielzitierte "Recht auf Vergessenwerden".
Das „Recht auf Vergessenwerden“ unter Geltung der DSGVO: Rechtmäßigkeit der Anzeige sensibler Daten
(2019)
Das Kopplungsverbot verbietet, die Nutzung einer Dienstleistung von der Erteilung einer nicht für die Leistungserbringung erforderlichen Einwilligung abhängig zu machen. Personalisierte Werbung wird hierdurch erheblich erschwert. Anbieter können jedoch durch Bereitstellung eines alternativen, einwilligungsfreien Zugangs zu derselben Leistung ihren Dienst datenschutzkonform anbieten. Ein solcher Zugang muss nicht zwingend in Form eines fixen Entgelts gestaltet sein. Vielmehr ist es datenschutzrechtlich in gewissem Umfang zulässig, Preise unter Einbeziehung personenbezogener Daten dynamisch zu gestalten.
Rezension zu: Reimer – Verwaltungsdatenschutzrecht: Das neue Recht für die behördliche Praxis (2019)
(2019)
Kein Urteil zum Datenschutzrecht sorgte im vergangenen Jahr für mehr panische Reaktionen als die Entscheidung des EuGH in der Rechtssache “Wirtschaftsakademie Schleswig-Holstein”(C-210/16). Das Urteil warf in datenschutzrechtlicher Literatur und Öffentlichkeit zahlreiche Fragen auf: Ist jetzt jeder “gemeinsam” Verantwortlicher? Was sind die Kriterien? Der EuGH hat kürzlich in einem – dem allgemeinen Vernehmen nach aufsehenerregenden, de facto aber kaum überraschenden – Urteil für Klarheit gesorgt. Dabei hat das Gericht jedoch einige Fragen offengelassen und neue Fragen aufgeworfen. Ein Blick auf alte und neue Herausforderungen in Kooperationsszenarien.
Kurz vor der parlamentarischen Sommerpause hat der Bundestag am 28.6.2019 das 2. Datenschutz-Anpassungs- und Umsetzungsgesetz EU (2. DSAnpUG-EU) beschlossen, der Bundesrat hat diesem Gesetz am 20.9.2019 zugestimmt. Das Artikelgesetz, welches im sog. Omnibusverfahren zahlreiche Gesetze auf Bundesebene ändert, soll zur Vereinheitlichung und Anpassung des Bundesrechts an die seit Mai 2018 geltende Datenschutz-Grundverordnung (DSGVO) beitragen.
Asteroid mining has the potential to greatly reduce the cost of in-space manufacturing, production of propellant for space transportation and consumables for crewed spacecraft, compared to launching the required resources from Earth’s deep gravity well. This paper discusses the top-level mission architecture and trajectory design for these resource-return missions, comparing high-thrust trajectories with continuous low-thrust solar-sail trajectories. This work focuses on maximizing the economic Net Present Value, which takes the time-cost of finance into account and therefore balances the returned resource mass and mission duration. The different propulsion methods will then be compared in terms of maximum economic return, sets of attainable target asteroids, and mission flexibility. This paper provides one more step towards making commercial asteroid mining an economically viable reality by integrating trajectory design, propulsion technology and economic modelling.
In parallel to the evolution of the Planetary Defense Conference, the exploration of small solar system bodies has advanced from fast fly-bys on the sidelines of missions to the planets to the implementation of dedicated sample-return and in-situ analysis missions. Spacecraft of all sizes have landed, touch-and-go sampled, been gently beached, or impacted at hypervelocity on asteroid and comet surfaces. More have flown by close enough to image their surfaces in detail or sample their immediate environment, often as part of an extended or re-purposed mission. And finally, full-scale planetary defense experiment missions are in the making. Highly efficient low-thrust propulsion is increasingly applied beyond commercial use also in mainstream and flagship science missions, in combination with gravity assist propulsion. Another development in the same years is the growth of small spacecraft solutions, not in size but in numbers and individual capabilities. The on-going NASA OSIRIS-REx and JAXA HAYABUSA2 missions exemplify the trend as well as the upcoming NEA SCOUT mission or the landers MINERVA-II and MASCOT recently deployed on Ryugu. We outline likely as well as possible and efficient routes of continuation of all these developments towards a propellant-less and highly efficient class of spacecraft for small solar system body exploration: small spacecraft solar sails designed for carefree handling and equipped with carried landers and application modules, for all asteroid user communities –planetary science, planetary defence, and in-situ resource utilization. This projection builds on the experience gained in the development of deployable membrane structures leading up to the successful ground deployment test of a (20 m)² solar sail at DLR Cologne and in the 20 years since. It draws on the background of extensive trajectory optimization studies, the qualified technology of the DLR GOSSAMER-1 deployment demonstrator, and the MASCOT asteroid lander. These enable ‘now-term’ as well as near-term hardware solutions, and thus responsive fast-paced development. Mission types directly applicable to planetary defense include: single and Multiple NEA Rendezvous ((M)NR) for mitigation precursor, target monitoring and deflection follow-up tasks; sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation; and deployable membrane based methods to modify the asteroid’s properties or interact with it. The DLR-ESTEC GOSSAMER Roadmap initiated studies of missions uniquely feasible with solar sails such as Displaced L1 (DL1) space weather advance warning and monitoring and Solar Polar Orbiter (SPO) delivery which demonstrate the capability of near-term solar sails to achieve NEA rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. For those mission types using separable payloads, such as SPO, (M)NR and RKI, design concepts can be derived from the separable Boom Sail Deployment Units characteristic of DLR GOSSAMER solar sail technology, nanolanders like MASCOT, or microlanders like the JAXA-DLR Jupiter Trojan Asteroid Lander for the OKEANOS mission which can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. These are an ideal match for solar sails in micro-spacecraft format whose launch configurations are compatible with ESPA and ASAP secondary payload platforms.
20 years after the successful ground deployment test of a (20 m) 2 solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed `now-term' and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC Gossamer Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid's but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection.
The results of a statistical investigation of 42 fixed-wing, small to medium sized (20 kg−1000 kg) reconnaissance unmanned air vehicles (UAVs) are presented. Regression analyses are used to identify correlations of the most relevant geometry dimensions with the UAV’s maximum take-off mass. The findings allow an empirical based geometry-build up for a complete unmanned aircraft by referring to its take-off mass only. This provides a bridge between very early design stages (initial sizing) and the later determination of shapes and dimensions. The correlations might be integrated into a UAV sizing environment and allow designers to implement more sophisticated drag and weight estimation methods in this process. Additional information on correlation factors for a rough drag estimation methodology indicate how this technique can significantly enhance the accuracy of early design iterations.
A review of guidelines and best practices for subsonic aerodynamic simulations using RANS CFD
(2019)
Recent Unmanned Aerial Vehicle (UAV) design procedures rely on full aircraft steady-state Reynolds-Averaged-Navier-Stokes (RANS) analyses in early design stages. Small sensor turrets are included in such simulations, even though their aerodynamic properties show highly unsteady behavior. Very little is known about the effects of this approach on the simulation outcomes of small turrets. Therefore, the flow around a model turret at a Reynolds number of 47,400 is simulated with a steady-state RANS approach and compared to experimental data. Lift, drag, and surface pressure show good agreement with the experiment. The RANS model predicts the separation location too far downstream and shows a larger recirculation region aft of the body. Both characteristic arch and horseshoe vortex structures are visualized and qualitatively match the ones found by the experiment. The Reynolds number dependence of the drag coefficient follows the trend of a sphere within a distinct range. The outcomes indicate that a steady-state RANS model of a small sensor turret is able to give results that are useful for UAV engineering purposes but might not be suited for detailed insight into flow properties.