Composite blade section property calculation method

The invention belongs to the field of helicopter design, and particularly relates to a composite blade section property calculation method. Blade section properties are the most basic original parameters for helicopter rotor dynamic calculation. Accuracy of the blade section properties is a premise for judging helicopter rotor dynamic properties and vital to rotor dynamic design. According to the composite blade section property calculation method, data files of sections of blades are built according to blade structures, wing profile theory contour data and material data, rigidity is calculated by a modulus weighting method according to anisotropic performances of composites, and mass is calculated by a finite element concept. Accurate basic data are provided for blade dynamic analysis and design, the blade section properties can be rapidly and accurately calculated, optimal design of the blades can be rapidly finished, and rotor system dynamic design technology is broken through. 本发明属于直升机设计领域，具体涉及种复合材料桨叶剖面特性