摘要
直升机桨毂整流罩模态频率及振型是整流罩结构设计的关键参数,当其固有频率与激振频率相接近时会发生共振,造成结构破坏或脱落,进而影响飞行安全。尾桨整流罩由于其安装位置的特殊性及振动环境的复杂性,需进行模态分析以保证其结构设计合理。基于有限元法对整流罩进行建模,开展了不同转速及不同安装边界约束的模态分析。研究结果表明:随着转速增大,整流罩受到的预应力增大,从而造成拉伸刚度、弯曲刚度和扭转刚度发生不同程度的变化;相比于转速变化,整流罩安装边界约束条件改变对频率影响更明显;该整流罩频率与各阶激振频率都具有一定间隔,说明其结构设计合理。
The frequency and vibration mode of the helicopter rotor hub fairing are the key parameters in the structural design of the fairing.When its natural frequency is close to the excitation frequency,resonance will occur,causing structural damage or detachment,and thus affecting flight safety.Due to the special installation location and complexity of the vibration environment,modal analysis is required to ensure the reasonable structural design of the tail rotor fairing.This article modeled the fairing based on the finite element method and conducted modal analysis with different rotational speeds and installation boundary constraints.The research results indicated that:1)As the rotational speed increased,the prestressing force on the fairing increased,resulted in varying degrees of variation in tensile stiffness,bending stiffness,and torsional stiffness.2)Compared to changes in rotational speed,changes in the installation boundary constraints of the fairing had a more significant impact on frequency.3)The frequency of the fairing had a certain interval from the excitation frequencies of each order,indicating that its structural design was reasonable.
作者
张英琦
郭杰
黄国科
ZHANG Yingqi;GUO Jie;HUANG Guoke(China Helicopter Research and Development Institute,Jingdezhen 333001,China)
出处
《直升机技术》
2024年第1期11-15,19,共6页
Helicopter Technique
关键词
直升机
桨毂整流罩
结构动力学
有限元计算
模态分析
helicopters
hub fairing
structural dynamics
finite element modeling
modal analysis
