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How to get more customer satisfaction : Erfolg im Wettbewerb durch kundenzentrierte Prozesse (2006)
Christian Czarnecki ; Marcus Heuser ; Christian Krämer ; Christoph Stummer ; Felix Theisinger ; Michael Wettklo
Unternehmen sind in der Regel überzeugt, dass sie die Bedürfnisse ihrer Kunden in den Mittelpunkt stellen. Aber in der direkten Interaktion mit dem Kunden zeigen sie häufig Schwächen. Der folgende Beitrag illustriert, wie durch eine konsequente Ausrichtung der Wertschöpfungsprozesse auf die zentralen Kundenbedürfnisse ein Dreifacheffekt erzielt werden kann: Nachhaltig erhöhte Kundenzufriedenheit, gesteigerte Effizienz und eine Differenzierung im Wettbewerb.
SEP for a lander mission to the jovian moon europa (2006)
Horst W. Loeb ; Karl-Heinz Schartner ; Wolfgang Seboldt ; Bernd Dachwald ; Joern Streppel ; Hans Meusemann ; Peter Schülke
Under DLR-contract, Giessen University and DLR Cologne are studying solar-electric propulsion missions (SEP) to the outer regions of the solar system. The most challenging reference mission concerns the transport of a 1.35-tons chemical lander spacecraft into an 80-RJ circular orbit around Jupiter, which would enable to place a 375 kg lander with 50 kg of scientific instruments on the surface of the icy moon "Europa". Thorough analyses show that the best solution in terms of SEP launch mass times thrusting time would be a two-stage EP module and a triple-junction solar array with concentrators which would be deployed step by step. Mission performance optimizations suggest to propel the spacecraft in the first EP stage by 6 gridded ion thrusters, running at 4.0 kV of beam voltage, which would save launch mass, and in the second stage by 4 thrusters with 1.25 to 1.5 kV of positive high voltage saving thrusting time. In this way, the launch mass of the spacecraft would be kept within 5.3 tons. Without a launcher's C3 and interplanetary gravity assists, Jupiter might be reached within about 4 yrs. The spiraling-down into the parking orbit would need another 1.8 yrs. This "large mission" can be scaled down to a smaller one, e.g., by halving all masses, the solar array power, and the number of thrusters. Due to their reliability, long lifetime and easy control, RIT-22 engines have been chosen for mission analysis. Based on precise tests, the thruster performance has been modeled.
Solar sail Kinetic Energy Impactor (KEI) mission design tradeoffs for impacting and deflecting asteroid 99942 Apophis (2006)
Bernd Dachwald ; Ralph Kahle ; Bong Wie
Near-Earth asteroid 99942 Apophis provides a typical example for the evolution of asteroid orbits that lead to Earth-impacts after a close Earth-encounter that results in a resonant return. Apophis will have a close Earth-encounter in 2029 with potential very close subsequent Earth-encounters (or even an impact) in 2036 or later, depending on whether it passes through one of several so-called gravitational keyholes during its 2029-encounter. Several pre-2029-deflection scenarios to prevent Apophis from doing this have been investigated so far. Because the keyholes are less than 1 km in size, a pre-2029 kinetic impact is clearly the best option because it requires only a small change in Apophis' orbit to nudge it out of a keyhole. A single solar sail Kinetic Energy Impactor (KEI) spacecraft that impacts Apophis from a retrograde trajectory with a very high relative velocity (75-80 km/s) during one of its perihelion passages at about 0.75 AU would be a feasible option to do this. The spacecraft consists of a 160 m x 160 m, 168 kg solar sail assembly and a 150 kg impactor. Although conventional spacecraft can also achieve the required minimum deflection of 1 km for this approx. 320 m-sized object from a prograde trajectory, our solar sail KEI concept also allows the deflection of larger objects. In this paper, we also show that, even after Apophis has flown through one of the gravitational keyholes in 2029, solar sail Kinetic Energy Impactor (KEI) spacecraft are still a feasible option to prevent Apophis from impacting the Earth, but many KEIs would be required for consecutive impacts to increase the total Earth-miss distance to a safe value. In this paper, we elaborate potential pre- and post-2029 KEI impact scenarios for a launch in 2020, and investigate tradeoffs between different mission parameters.
Experimenteller Prototyp zur ontologiebasierten Suche in einem Multi-Agenten-System (2006)
Bernd Müller
Numerical analysis for a new non-conforming linear finite element on quadrilaterals (2006)
Matthias Grajewski ; Jaroslav Hron ; Stefan Turek
Nuclear Receptors which play a pivotal role in drug disposition and chemical toxicity (2006)
Lesley A. Stanley ; Brian C. Horsburgh ; Jillian Ross ; Nico Scheer ; C. Roland Wolf
Asymmetric localization of Numb:EGFP in dividing neuroepithelial cells during neurulation in Danio rerio (2006)
Alexander M. Reugels ; Barbara Boggetti ; Nico Scheer ; José A. Campos-Ortega
Integrating Semantic Web Services and Business Process Management: A Real Use Case (2006)
Christian Drumm ; Jens Lemcke ; Daniel Oberle
The Constitutional Court as Driver of Reforms in German Family Law (2006)
Nina Dethloff ; Kathrin Kroll-Ludwigs
Selbstverantwortung oder Vertrauenshaftung? – Anwendung von § 311 II Nr. 1 BGB (c.i.c.) auf Eheverträge und Angehörigenbürgschaften (2006)
Kathrin Kroll-Ludwigs
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