1) blade lift
桨叶升力
2) blade-lift coefficient
桨叶升力系数
3) rotor blade improvement
桨叶升级
4) helicopter blade
直升机桨叶
1.
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。
2.
In this paper,the strength limit and fatigue limit of leading edge of a helicopter blade are obtained by tests of standard specimen,and stress concentration factors by finite element analysis.
通过标准样件试验,获得直升机桨叶前缘包铁的静强度极限和疲劳极限,通过有限元分析,获得应力集中系数,再应用应力集中系数对试验中获得的静强度极限和疲劳极限进行修正。
3.
Calculation about the natural vibration frequencies of the helicopter blade in rotating plane;
利用有限元法推导了直升机桨叶的耦合振动频率方程，提出了有效的计算方法──直接迭代法，并计算了桨叶第１至第４阶固有频率。
5) blade thrust
桨叶推力
6) lifting airscrew
升力螺旋桨
补充资料：GS,GT型空心桨叶连续干燥机
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说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条