helicopter blade testing 直升机旋翼测试
composite helicopter blade 直升机旋翼桨叶
echo from helicopter blade 直升机旋翼回波
helicopter blade dynamic balance 直升机桨叶动平衡试验
helicopter rotor blade 直升机旋翼桨叶
helicopter ' s blade 直升机旋翼
helicopter s blade 直升机旋翼
four-blade rotor helicopter 四叶旋翼直升机
An experimental technique and method for flutter research of helicopter blade model are proposed.
提出了直升机模型桨叶颤振试验技术及试验方法。
An iterative computation method for nonlinear forced vibration equation on helicopter blade 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。
In the static strength analysis of helicopter blade, the traditional analysis method may lead to the uncertainty of the strength conclusion due to the inaccuracy of load calculation.
在直升机桨叶的静强度分析中，传统的分析方法可能会由于载荷计算的不准确，给强度结论带来不确定性。
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