A. Bezuevsky, I. Kondakov, A. Shanygin, M. Zichenkov
DOI Number: N/A
Conference number: IFASD-2015-049
Development of lattice composite aircraft primary structures have been formed during recent years as a novel and promising direction of research aiming to create the next generation of lightweight composite airframes. The application of composites within the frames of lattice/frame layouts, based on unidirectional composite elements, shows high potential in weight saving up to 15% and more for such composite primary structures in comparison with conventional semi-monocoque metallic and composite analogues [1]. The lattice composite structures are substantially different by their topology, layouts and the functions of their main structure elements from conventional laminated composite airframes based on thin stiffened skin. According to that, the creation of lightweight lattice composite airframes requires a proper study of the main questions of strength, including the question of dynamic behavior of composite structures with lattice layouts. The experience shows that the conventional methods of strength analysis are as a rule not correct as applied to the novel lattice composite structures. Hence, these methods should be adapted for the new type of structures or the new special methods for these structures should be developed in order to provide confident solutions of the main tasks of structural dynamics. In the presented paper the main special features of some lattice airframes from the viewpoint of structural dynamics, including eigen frequencies, mode shapes and frequency response, have been formulated. These special features should be taken into account as basic requirements for the development of methods for modeling of dynamic behavior of lattice composite airframes.