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000229982 001__ 229982 000229982 005__ 20220802154323.0 000229982 0247_ $$2URN$$aurn:nbn:de:hbz:82-opus-34547 000229982 0247_ $$2HSB$$a999910310678 000229982 0247_ $$2OPUS$$a3454 000229982 0247_ $$2datacite_doi$$a10.18154/RWTH-CONV-144789 000229982 037__ $$aRWTH-CONV-144789 000229982 041__ $$aEnglish 000229982 082__ $$a600 000229982 1001_ $$0P:(DE-82)011685$$aSantel, Christoph$$b0$$eAuthor 000229982 245__ $$aAn investigation of glider winch launch accidents utilizing multipoint aerodynamics models in flight simulation$$cChristoph G. Santel$$honline 000229982 260__ $$aAachen$$bPublikationsserver der RWTH Aachen University$$c2010 000229982 300__ $$aXIV, 67 S. 000229982 3367_ $$0PUB:(DE-HGF)10$$2PUB:(DE-HGF)$$aDiploma Thesis$$bdiploma$$mdiploma 000229982 3367_ $$02$$2EndNote$$aThesis 000229982 3367_ $$2DataCite$$aOutput Types/Supervised Student Publication 000229982 3367_ $$2DRIVER$$amasterThesis 000229982 3367_ $$2ORCID$$aSUPERVISED_STUDENT_PUBLICATION 000229982 3367_ $$2BibTeX$$aMASTERSTHESIS 000229982 502__ $$aAachen, Techn. Hochsch., Diplomarbeit, 2010 000229982 500__ $$aVeröffentlicht auf dem Publikationsserver der RWTH Aachen University 000229982 520__ $$aThe presented thesis investigated the mechanisms leading to accidents during the winch launch of gliders. Initially, data from the accident database of the German Federal Bureau of Aircraft Accident Investigation was studied. Critical phases of the launch were identied along with the associated probabilities and risks of accidents. From this data requirements to an aerodynamics model suitable for accident reconstruction were formulated. An instationary multipoint aerodynamics approach, based on blade element theory, met these demands. A "prescribed wake" model was then coupled with this multipoint aerodynamics approach to determine the induced velocities at all surfaces. The developed models were then validated and checked for plausibility with flight test data from a Schweizer SGS 1-36 sailplane. For the purpose of describing the relations between pilot and aircraft behavior as well as launch safety, a flight envelope limiting airspeed and pitch attitude was proposed. It was shown that the aircraft's radius of gyration along its pitch axis influences the path taken through the flight envelope. As a consequence, motorglider conversions of existing sailplane designs operate closer to the upper pitch boundary of the flight envelope. With this knowledge a generic 18 m class motorglider model was then implemented in the developed aerodynamics model and exposed to a hypothetical accident scenario. Here it was shown that under the presented circumstances the risk of a pilot-provoked stall of the horizontal stabilizer exists. Depending on the severity of the stall, a catastrophic accident might result.$$leng 000229982 591__ $$aGermany 000229982 653_7 $$aTechnik 000229982 653_7 $$2ger$$aWindenstart 000229982 653_7 $$2ger$$aMehrpunkt 000229982 653_7 $$2ger$$aVortex-Lattice-Methode 000229982 653_7 $$2eng$$awinch lauch 000229982 653_7 $$2eng$$avortex-lattice 000229982 653_7 $$2eng$$amulti-point aerodynamics 000229982 650_7 $$2SWD$$aSegelflug 000229982 650_7 $$2SWD$$aAerodynamik 000229982 650_7 $$2SWD$$aWirbel<Physik>, Simulation 000229982 7001_ $$0P:(DE-82)011686$$aGäb, Andreas$$b1$$eThesis advisor 000229982 8564_ $$uhttps://publications.rwth-aachen.de/record/229982/files/3454.pdf$$yOpenAccess 000229982 909CO $$ooai:publications.rwth-aachen.de:229982$$pdnbdelivery$$pVDB$$pdriver$$purn$$popen_access$$popenaire 000229982 915__ $$0StatID:(DE-HGF)0510$$2StatID$$aOpenAccess 000229982 9201_ $$0I:(DE-82)415410_20140620$$k415410$$lLehrstuhl und Institut für Flugsystemdynamik$$x0 000229982 961__ $$c2014-12-04$$x2013-08-06$$z2012-02-20 000229982 970__ $$aopus00003454 000229982 980__ $$adiploma 000229982 980__ $$aVDB 000229982 980__ $$aUNRESTRICTED 000229982 980__ $$aConvertedRecord 000229982 980__ $$aFullTexts 000229982 980__ $$aI:(DE-82)415410_20140620 000229982 9801_ $$aFullTexts