Aero-elastictailoring Method Research Of The Advanced Geometry Composite Rotor Blade

Reducing the vibration of the helicopter has been a difficulty and hotspot in the research of thehelicopter technology, reducing the rotor exciting force by elasticity tailoring of the rotor bladestructure design is the most effective and least costly approach to that. The research of composite rotorblade structure elasticity tailoring analysis method has accomplished in this work. The regular law ofelastic tailoring has also been explored, which is of important theoretical meaning and practical value.The research of this paper aims at the design of composite rotor blade structure elasticitytailoring and analysis of the key technical problems, the main work includes the following aspects:(1) Based on the beam theory of medium deformation, take use of advanced geometry shapedescription, introducing6x6elastic coupling constitutive relation, take the bending-bending torsion-twisting-shearing elastic coupling of structure into consideration, obtaining complete blade strainenergy and kinetic energy, and then using the Hamilton principle, then suitable analysis model of fullycoupled nonlinear dynamic of composite rotor blade the elasticity tailoring obtained.(2) Based on15DOFs beam element, a fully coupled composite beam element model of19DOFs was developed. We also developed finite element calculation program of advanced geometricshape of composite material blade structure elasticity tailoring, and operated large numbers ofcalculation examples of the composite blade coupling stiffness, coupling mode and blade dynamicload, the comparison of the experiment and measured data of domestic and abroad show that thisapproach has good accuracy, which validate the validity of the method.(3) With an emphasis on box beam composite blade, research on the regular rule of elastictailoring was carried out. The regular rule of four sets of composite box beam blade design of elasticcoupling stiffness, modal characteristics, and the regular that aero-elastic response an dynamic loadvaries with the change of layer angle was obtainedwhich validate the validity of the design ofcomposite blade structure elasticity tailoring in helicopter rotor dynamic design.The design canprovide important reference for the design of helicopter vibration reduction.