Метод інтегрованого проєктування ферменної композитної хвостової балки фюзеляжу багатоцільового легкого вертольота

The object of the study is a truss composite tail beam of the fuselage a multipurpose light helicopter. The subject of this study is the integration of CAD/CAM/CAE/PLM methods in the design of a truss composite tail beam of the fuselage multipurpose light helicopter. This study aims to scientifically substantiate the integrated design method of a composite truss tail beam of the fuselage of a multi-purpose light helicopter. Task: to develop an integrated design method for a truss composite tail beam of the fuselage of a multipurpose light helicopter, and to formulate the topological optimization problem of a composite tail beam of the fuselage of a multipurpose light helicopter. This study proposes an integrated design method for a truss composite tail beam of the fuselage of a multipurpose light helicopter and presents its scientific justification. The proposed method for the integrated design of a truss composite tail beam of the fuselage of a light helicopter is based on the use of an integrated CAD/CAE/CAM/PLM information environment for designing and maintaining the life cycle of helicopters. This environment integrates various software tools that encompass the full cycle of helicopter development, production, operation, and maintenance. This approach significantly increases work efficiency, reduces costs, and ensures the high quality of the final product. The proposed method uses topological optimization and creates a parametric master geometry of the tail beam of the truss structure, a composite material is designed, and the strength and mass characteristics of the tail beam are studied using CAD/CAE methods. The purpose of the topological optimization of the tail truss beam is to minimize the tail beam mass when applying strength constraints. Further research should test the proposed method of integrated design of the truss composite tail beam of the fuselage of a multipurpose light helicopter. Scientific novelty and practical significance of the obtained results: for the first time, a method of integrated design of the truss composite tail beam of the fuselage of a multipurpose light helicopter is proposed based on the use of topological optimization and creation of parametric master geometry of the truss structure’s tail beam.