Analysis of Dynamic Characteristics of Helicopter Hub Fairing based on Finite Element Method
The frequency and vibration mode of the helicopter rotor hub fairing are the key parame-ters in the structural design of the fairing.When its natural frequency is close to the excitation fre-quency,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 a-nalysis 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 de-grees 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.
helicoptershub fairingstructural dynamicsfinite element modelingmodal analysis
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