当前位置: X-MOL 学术Proc. Inst. Mech. Eng. Part G J. Aerosp. Eng. › 论文详情
Our official English website, www.x-mol.net, welcomes your feedback! (Note: you will need to create a separate account there.)
Structural dynamic response analysis due to the slit flow between the tailplane and the elevator
Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering ( IF 1.1 ) Pub Date : 2021-05-17 , DOI: 10.1177/09544100211016949
Ju Qiu 1 , Jiali Tang 2 , Chundu Sun 2 , Fengyu Dai 3
Affiliation  

Any aircraft in flight is subjected to dynamic loads. Following vibration-related accidents, a flow field and vibration analysis can be carried out to analyze the data and study the cause of the accident. When slit airflow enters the cavity between the tailplane structure and the elevator, a mixed vortex is formed. If the vortex-induced vibrational frequency of around 50 Hz happens to be close to the natural frequency of the structure at 46 Hz, it is likely to induce structural vibration (resonance). The resonance can cause excessive fatigue damage which can ultimately lead to structural failure and the loss of the component or the aircraft. Damping methods can be employed to control vibration within the structure by reducing the amplitude of that vibrational motion by 83%. This article details a recreation of one example of structural vibration within an airborne aircraft.



中文翻译:

尾翼与电梯之间的缝隙流动引起的结构动力响应分析

任何飞行中的飞机都会承受动态载荷。在发生与振动有关的事故后,可以进行流场和振动分析,以分析数据并研究事故原因。当狭缝气流进入尾翼结构和升降机之间的空腔时,形成了混合涡流。如果涡流诱发的约50 Hz的振动频率恰好接近结构的固有频率(46 Hz),则很可能引起结构振动(共振)。共振会导致过度的疲劳损坏,最终可能导致结构故障以及零部件或飞机的损失。通过将振动运动的幅度降低83%,可以采用阻尼方法来控制结构内的振动。

更新日期:2021-05-17
down
wechat
bug