An experimental technique and method for flutter research of helicopterblade model are proposed.
提出了直升机模型桨叶颤振试验技术及试验方法。
2
An iterative computation method for nonlinear forced vibration equation on helicopterblade aerodynamic load is given.
介绍用迭代方法求解直升机桨叶气动载荷中的非线性强迫振动方程。
3
In the static strength analysis of helicopterblade, the traditional analysis method may lead to the uncertainty of the strength conclusion due to the inaccuracy of load calculation.