Tendencies in development of computational mechanics for strength design of aircraft structures

Development of novel approaches, methods and algorithms for solution of the computational mechanics problems for providing structural design of aircraft is an actual problem. Its solution allows to significantly increase bulk and efficiency of numerical investigations and to guarantee a high confidence of numerical results for advanced load-bearing structures of different aircraft made of metallic and composite materials. It is supposed that the developing methods will be implemented in the specialized replicable industry solutions on the basis of available software alienated from the developer as import substitution software. It gives feasibility to take into account important aeroelasticity, strength and fatigue requirements already in the preliminary design stage. At the final certification stage of the aircraft development the robust computational methods will reduce the amount of necessary evidentiary tests in accordance with the modern concept of "certification by calculation".
In the paper the requirements are formulated for development of new technology which is directed on integrating the available software tools and implementation of new methods for analysis of strength, fatigue and aeroelastic characteristics. They include the simulation and analysis methods that are under development in Russian and foreign research companies and universities. Development of the specialized replicable industry solution in the framework of “soft import substitution” based on the program tools available in TsAGI and the CAE-Fidesys software package.
New approach to solution of the coupled problem of interaction of flexible structure with airflow is demonstrated. Substantial influence of airflow viscosity on aeroelastic characteristics of structure is shown on the example of numerical analysis of middle-range passenger airplane. The important tendency in development of design methods is application of multidisciplinary approach in investigations on synthesis and optimization of aircraft structural layouts. It has been illustrated on the example of wing design of advanced helicopter and on the problem of searching optimal shape of tip part of high-aspect ratio wing with taking into account strength, buckling and aeroelasticity constraints.