Erzielung einer optimierten Tragfluegelverwoelbung durch den Einsatz formvariabler Klappenstrukturen

Available from TIB Hannover: RA 437(2000-30) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEDEGerman

Steigerung der aerodynamischen Effizienz von Hochauftriebsklappen -Vergleich adaptiver und passiver Massnahmen

SIGLEAvailable from TIB Hannover / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Der adaptive Spoiler - Entwicklung und Umsetzung einer adaptiven Profilaufdickung zur Reduktion des transsonischen Wellenwiderstandes

Within the project 'Adaptive Wing (ADIF)' a local contour bump to reduce the transonic wave drag is realized at the DLR. The local countor bump is designed for a spoiler of a typical fixed wing and is based on the tube spring concept. The spoiler is considered as a 3-layered structure, a load-carrying substructure, a layer made of tube springs and the flexible spoiler skin. Here, the tube springs substitute the inner core of existing spoilers and contributes significantly to the stiffness of the complete spoiler. The tube spring itself consist of two, symmetrical hollows made of CFRP. The cross-section of each segment represents an open profile with a circumference angle of 270 . Either pressurized or activated by embedded shape memory alloys, the structure generates a stroke perpendicular to the open end. Analytical as well as experimental investigations have verified the tube spring concept and have proven, that this concept meets the requirements of an adaptive spoiler. (orig.)SIGLEAvailable from TIB Hannover: RA 437(1999-35) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Innovative Faserverbundstrukturen in Verkehrstechnik und Luftfahrt Proceedings

SIGLEAvailable from TIB Hannover: RN 4948(1998,23) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman

Verfahrens- und Konstruktionstechnisch optimierte Multiaxialgelege fuer beanspruchungsgerechte rationelle Kunststoffverstaerkung - OPTIMAX Abschlussbericht

Multiaxial-layered C-fiber composites suitable for production of aeroplane component parts have been constructed and characterized. Compared with costly prepreg composites, the multi-layered composites exhibited lower compression and shear resistances. This effect could be attributed to lower matrix resin strength, lower fiber-matrix bonding strength and disoriented and ondulated fiber strands in the multi-layered composites. However, improved process conditions may overcome these disadvantages.SIGLEAvailable from TIB Hannover: F03B852 / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekBundesministerium fuer Bildung und Forschung, Berlin (Germany)DEGerman

Schwarzer Rumpf - Realisierung von CFK-Rumpfkomponenten unter Einbeziehung des Concurrent Engineering Schlussbericht

Available from TIB Hannover: F04B805 / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEBundesministerium fuer Bildung und Forschung (BMBF), Bonn (Germany)DEGerman

Adaptive Verbundstrukturen fuer den Leichtbau - strukturkonform integrierte piezoelektrische Fasern und Folien (ADAPTRONIK). T. 1: Kurzbericht. T. 2: Eingehende Berichte. Bd. 1-6 Schlussbericht

Published in 7 volumesAvailable from TIB Hannover: QN 488(1) - (7) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekSIGLEBundesministerium fuer Bildung und Forschung, Berlin (Germany)DEGerman

Untersuchung adaptiver Konzepte zur Reduktion von Hubschraubervibrationen, zur Minderung des Hubschrauberlaerms und zur Steigerung der aerodynamischen Effizienz

By applying adaptronics to helicopters, i.e. by use of self-adapting structural components, noise can be suppressed, vibration reduced and aerodynamic efficiency increased. This thesis investigates two concepts, the adaptive blade root and the adaptive blade tip, allowing direct adaptive shape control of the main rotor areas that are the main sources of helicopter noise and vibration. Both concepts are based on the introduction of a local twist into the rotor blades. Since non-stationary helicopter aerodynamics and their interaction with the elastic helicopter structure are the main sources for flight envelope boundaries as well as vibration and noise, the comprehension of aerodynamics is essential to effectively influence local airflow conditions and finally evaluate the investigated concepts. With respect to these relations the adaptive blade root and the adaptive blade tip are described and evaluated. The adaptive blade root represents a torsional actuator integrated in the rotor blade root that mainly introduces rigid body blade torsion. A torsional actuator integrated in the rotor blade tip is realized by the adaptive blade tip. This concept influences the blade twist distribution close to the blade tip and leads to higher aerodynamic efficiency due to this approach. (orig.)SIGLEAvailable from TIB Hannover: RN 437(98-12) / FIZ - Fachinformationszzentrum Karlsruhe / TIB - Technische InformationsbibliothekDEGerman