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。
As a critical part of helicopter, rotor blade anti-fatigue design technique is one of the key to improving safety life and decreasing cost.
作为直升机的关键动部件,桨叶的抗疲劳设计技术是提高桨叶安全寿命,降低桨叶使用成本的关键。
This paper concentrates on the application research of consistency evaluation technique for the structural test and analysis used in composite material of helicopter.
本文主要进行了一致性评判技术在直升机复合材料结构试验与分析中的应用研究。
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