![]() ![]() Ivchenko, A.V., Tulaev, A.I.: Honeycomb panel and filler design. Ivchenko, A.V.: Configuring honeycomb filler for an adaptable wing based on a network combination of joints with hidden topological surfaces. Ivchenko, A.V.: Mechatronic unit and adaptable wing main frame. Ivchenko, A.V., Ziatdinov, R.: Flexagon grid: a novel method of creating dynamic spatial forms based on the synthesis of tritetraflexagons. Ivchenko, A.V.: Flexagon grids and a method to create robotic spatial forms on their basis. Ivchenko, A.V.: Flexagon grids: dynamic forms of the future. Ivchenko, A.V.: Flexagon grids: Combinatorics of reversive tiling patterns based on the synthesis of tritetraflexagons. In: Proceedings of the 45th AIAA Conference on Structures, Structural Dynamics and Materials, AIAA Paper, p. 1888 (2004)īlondeau, J., Pines, D.: Pneumatic morphing aspect ratio wing. Perkins, D.A., Reed, J.L., Havens, E.: Morphing wing structures for loitering air vehicles. Stanewsky, E.: Adaptive wing and flow control technology. 49(6), 1666–1674 (2012)īarbarino, S., Pecora, R., Lecce, L., et al.: Airfoil structural morphing based on SMA actuator series: numerical and experimental results. Pecora, R., Amoroso, F., Lecce, L.: Effectiveness of wing twist morphing in roll control. Pecora, R., Barbarino, S., Concilio, A., et al.: Design and functional test of a morphing high-lift device for a regional aircraft. In: Proceeding of Royal Aeronautical Society Symposium on Multidisciplinary Design and Optimization, pp. Monner, H.P., Bein, T., Hanselka, H., et al.: Design aspect of the adaptive wing – the elastic trailing edge and the local spoiler bump. 176–177 (2018)īarbarino, S., Bilgeno, O., Ajaj, R.M., et al.: A review of morphing aircraft. Ivchenko, A.V., Sharonov, N.D.: The mechatronic unit and frame adaptable wing. The results of the research can be used for designing and manufacturing configurable aircraft wing structures. Also, stress risers were detected, which became the round parts of the segments. The dynamics of the damages indicates that the weakest element of the structure is the link in the place of bending. As a result of the research, computer models of a fragment of the mechatronic unit have been obtained, stresses and deformations under various loads have been determined, and recommendations for enhancing the efficiency of the structure under study have been developed. When modeling, displacements, stresses, and deformations were determined, which arisen in various operating modes with external loads. The basis of the model of an adaptable wing main frame structure proposed is a mechatronic unit, which is designed to ensure the preset angle between the elements in the adaptable wing structure a coordinated control of the model and a possibility to vary the airfoil geometry with due regard to the aerodynamic and technical requirements. The work represents the results of modeling and studying the interaction of the mechatronic unit segments in an aircraft wing when an external impact is applied. ![]()
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