@book{ChwallekFelden2006,
  author    = {Chwallek, Constanze and Felden, Birgit},
  title     = {RatingCheck : Wertsch{\"o}pfungskette / Chwallek, Constanze ; Felden, Birgit},
  publisher = {Deutscher Sparkassen Verlag},
  address   = {Stuttgart},
  year      = {2006},
  language  = {en}
}
@inproceedings{Kurz2006,
  author    = {Kurz, Melanie},
  title     = {Recognition of shape in virtual visualizations},
  series = {Proceedings : November 15 - 17, 2006, Technische Universit{\"a}t Darmstadt, Darmstadt, Germany ; PACE, Partners for the advancement of collaborative engineering education},
  booktitle = {Proceedings : November 15 - 17, 2006, Technische Universit{\"a}t Darmstadt, Darmstadt, Germany ; PACE, Partners for the advancement of collaborative engineering education},
  publisher = {Techn. Univ.},
  address   = {Darmstadt},
  isbn      = {978-3-00-020161-5},
  pages     = {203 -- 209},
  year      = {2006},
  language  = {en}
}
@inproceedings{SakthivelWeppner2006,
  author    = {Sakthivel, Mariappan and Weppner, Werner},
  title     = {Response behaviour of a hydrogen sensor based on ionic conducting polymer-metal interfaces prepared by the chemical reduction method},
  url       = {http://nbn-resolving.de/urn:nbn:de:hbz:a96-opus-1399},
  year      = {2006},
  abstract  = {A solid-state amperometric hydrogen sensor based on a protonated Nafion membrane and catalytic active electrode operating at room temperature was fabricated and tested. Ionic conducting polymer-metal electrode interfaces were prepared chemically by using the impregnation-reduction method. The polymer membrane was impregnated with tetra-ammine platinum chloride hydrate and the metal ions were subsequently reduced by using either sodium tetrahydroborate or potassium tetrahydroborate. The hydrogen sensing characteristics with air as reference gas is reported. The sensors were capable of detecting hydrogen concentrations from 10 ppm to 10\% in nitrogen. The response time was in the range of 10-30 s and a stable linear current output was observed. The thin Pt films were characterized by XRD, Infrared Spectroscopy, Optical Microscopy, Atomic Force Microscopy, Scanning Electron Microscopy and EDAX.},
  subject      = {Biosensor},
  language  = {en}
}
@inproceedings{KraftRetkowitz2006,
  author    = {Kraft, Bodo and Retkowitz, Daniel},
  title     = {Rule-Dependencies for Visual Knowledge Specification in Conceptual Design},
  year      = {2006},
  abstract  = {In: Proc. of the 11th Intl. Conf. on Computing in Civil and Building Engineering (ICCCBE-XI) ed. Hugues Rivard, Montreal, Canada, Seite 1-12, ACSE (CD-ROM), 2006 Currently, the conceptual design phase is not adequately supported by any CAD tool. Neither the support while elaborating conceptual sketches, nor the automatic proof of correctness with respect to effective restrictions is currently provided by any commercial tool. To enable domain experts to store the common as well as their personal domain knowledge, we develop a visual language for knowledge formalization. In this paper, a major extension to the already existing concepts is introduced. The possibility to define rule dependencies extends the expressiveness of the knowledge definition language and contributes to the usability of our approach.},
  subject      = {CAD},
  language  = {en}
}
@article{KrebsbachSchillerBrunneretal.2006,
  author    = {Krebsbach, M. and Schiller, C. and Brunner, D. and G{\"u}nther, G. and Hegglin, M. I. and Mottaghy, Darius and Riese, M. and Spelten, N. and Wernli, H.},
  title     = {Seasonal cycles and variability of O_3 and H_2O in the UT/LMS during SPURT},
  series = {Atmospheric Chemistry and Physics},
  volume    = {6},
  journal   = {Atmospheric Chemistry and Physics},
  number    = {1},
  doi       = {10.5194/acp-6-109-2006},
  pages     = {109 -- 125},
  year      = {2006},
  language  = {en}
}
@inproceedings{ButenwegMistler2006,
  author    = {Butenweg, Christoph and Mistler, Michael},
  title     = {Seismic resistance of unreinforced masonry buildings},
  series = {Proceedings of the Eighth International Conference on Computational Structures Technology : [Las Palmas de Cran Canaria, 12-15 September 2006] / ed. by B. H. V. Topping ...},
  booktitle = {Proceedings of the Eighth International Conference on Computational Structures Technology : [Las Palmas de Cran Canaria, 12-15 September 2006] / ed. by B. H. V. Topping ...},
  publisher = {Civil-Comp Press},
  address   = {Stirling},
  organization    = {International Conference on Computational Structures Technology <8, 2006, Las Palmas>},
  isbn      = {1-905088-06-X},
  doi       = {10.4203/ccp.83.9},
  pages     = {Paper 9},
  year      = {2006},
  language  = {en}
}
@inproceedings{LoebSchartnerSeboldtetal.2006,
  author    = {Loeb, Horst W. and Schartner, Karl-Heinz and Seboldt, Wolfgang and Dachwald, Bernd and Streppel, Joern and Meusemann, Hans and Sch{\"u}lke, Peter},
  title     = {SEP for a lander mission to the jovian moon europa},
  series = {57th International Astronautical Congress},
  booktitle = {57th International Astronautical Congress},
  doi       = {10.2514/6.IAC-06-C4.4.04},
  pages     = {1 -- 12},
  year      = {2006},
  abstract  = {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.},
  language  = {en}
}
@incollection{PoghossianSchoening2006,
  author    = {Poghossian, Arshak and Sch{\"o}ning, Michael Josef},
  title     = {Silicon-based chemical and biological field-effect sensors},
  series = {Encyclopedia of Sensors. Vol. 9 S - Sk},
  booktitle = {Encyclopedia of Sensors. Vol. 9 S - Sk},
  publisher = {ASP, American Scientific Publ.},
  address   = {Stevenson Ranch, Calif.},
  isbn      = {1-58883-065-9},
  pages     = {463 -- 534},
  year      = {2006},
  language  = {en}
}
@inproceedings{BarekFischerNavratiletal.2006,
  author    = {Barek, Jiri and Fischer, Jan and Navratil, Tomas and Peckova, Karolina and Yosypchuk, Bogdan},
  title     = {Silver solid amalgam electrodes as sensors for chemical carcinogens},
  url       = {http://nbn-resolving.de/urn:nbn:de:hbz:a96-opus-1554},
  year      = {2006},
  abstract  = {The applicability of differential pulse voltammetry (DPV) and adsorptive stripping voltammetry (AdSV) at a non-toxic meniscus-modified silver solid amalgam electrode (m-AgSAE) for the determination of trace amounts of genotoxic substances was demonstrated on the determination of micromolar and submicromolar concentrations of 3-nitrofluoranthene using methanol - 0.01 mol L-1 NaOH (9:1) mixture as a base electrolyte and of Ostazine Orange using 0.01 mol L-1 NaOH as a base electrolyte.},
  subject      = {Biosensor},
  language  = {en}
}
@inproceedings{DachwaldKahleWie2006,
  author    = {Dachwald, Bernd and Kahle, Ralph and Wie, Bong},
  title     = {Solar sail Kinetic Energy Impactor (KEI) mission design tradeoffs for impacting and deflecting asteroid 99942 Apophis},
  series = {AIAA/AAS Astrodynamics Specialist Conference and Exhibit},
  booktitle = {AIAA/AAS Astrodynamics Specialist Conference and Exhibit},
  doi       = {10.2514/6.2006-6178},
  pages     = {1 -- 20},
  year      = {2006},
  abstract  = {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.},
  language  = {en}
}