In the article are proposed the approaches for the definition of the rational parameters of the feathering hinge torsion shaft of the helicopter rotor hub taking into account of both the explicit limitations to these parameters and the limitations in the form of functional dependences. The results of parametrical researches with the use of M. Box’s complex method are resulted.
rotor hub, feathering hinge, torsion shaft, optimization methods
"Optymizatsiia parametriv torsiona osovoho sharnira vtulky nesuchoho hvynta vertolota" ,
Systems of Arms and Military Equipment,