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.

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