Multiparametric optimization of the rotor blade design of a helicopter with controlled geometry

In flight, a helicopter’s rotor blades create significant fluctuations and noise due to changes in the aerodynamic loads acting on them when their azimuth angle changes. Various methods are used to reduce the resulting vibrations and noise. For example, with the advent of active materials, the concept of a rotor with an active twisting was proposed. The actuators integrated into the main rotor blade skin initiate dynamic twisting and curvature of the blade, adapted at any time to flight conditions and significantly reducing vibrations and noise, as well as improving flight characteristics. This work aims at the multiparametric optimization of the blade design with controlled geometry. The problem of the multiparametric optimization of a composite structure based on thermo-piezoelectric analogy is formulated. The target function is selected. The optimization parameters of the blade design are determined and constraints for the selected parameters are formulated. A design method of the blade structure with controlled geometry has been developed, which includes three program blocks. The first block is a mathematical model. The second block is the construction of the matrix of planning experiments. The third block is to obtain a surface response and search for an extremum. The optimal parameters of the active (control) and power elements of the blade design with controlled geometry are determined. The obtained solution of the optimization problem was compared with the results of the direct numerical simulation. When conducting the direct numerical simulation, controlled deformations of the blade under study were calculated at different values of the control electric voltage, the problem was solved in a related formulation using the obtained geometric parameters. Thus, the results of this study can be applied in the design of structures with controlled geometry.