Transport Category Aircraft Fuselage Integrated Design

Regulatory and technical documentation, design features and methods of transport category aircraft fuselage design analysis was performed and identified the need to update design methods and calculate the characteristics of the fuselage using parametric models and integrated design with CAD/CAM/CAE/PLM systems. Within the framework of the proposed method, parametric models of master geometry, aerodynamic flow and mass-inertial characteristics of the fuselage were created, taking into account the design features of transport aircraft. The proposed method was used to study the influence of geometric parameters of fuselage nose and tail sections on aerodynamic and mass characteristics of the fuselage, showing the efficiency of work with parametric models. The use of the method for regional aircraft fuselage design allowed to determine the rational configuration of the nose section of the fuselage and increase the fuel efficiency of the aircraft by 6.4%, reduce the aerodynamic drag of the fuselage by 10%, increase the viewing angle from the cockpit by 10%. Fuselage nose, center and tail sections main parameters determination method is presented. Main theoretical characteristics for determination of optimal parameters of fuselage and its cargo cabin for the transport aircrafts are described. According to the method master-geometry of fuselage of transport aircraft was developed with high accuracy.