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赵则利,许 锋. 舰载直升机“舰面共振”动力学分析[J]. 科学技术与工程, 2020, 20(16): 6650-6657.
zhaozeli,xufeng.Dynamic Analysis of “Ship Resonance” for Shipboard Helicopter[J].Science Technology and Engineering,2020,20(16):6650-6657.
舰载直升机“舰面共振”动力学分析
Dynamic Analysis of “Ship Resonance” for Shipboard Helicopter
投稿时间:2019-09-07  修订日期:2020-06-14
DOI:
中文关键词:  直升机  舰面共振  起落架  旋翼减摆器  自激振动
英文关键词:helicopter  ship resonance  landing gear  lead-lag  damper  self-excited vibration
基金项目:
     
作者单位
赵则利 南京航空航天大学
许 锋 南京航空航天大学
摘要点击次数: 67
全文下载次数: 37
中文摘要:
      目前,在舰载直升机与舰船动态交互的研究过程中,几乎没有分析舰船运动对直升机动力学稳定性的影响,在仅有的研究文献中更是没有考虑直升机起落架的非线性特性。为了解舰载直升机舰面开车状态的动力学特性,以某舰载直升机为研究对象,建立了全机多体动力学模型、起落架液压缓冲系统模型和旋翼减摆器液压模型,进行了全机“舰面共振”动力学仿真试验。研究了舰船横摇角、舰船运动周期、旋翼液压减摆器参数对直升机“舰面共振”稳定性的影响。结果表明:在“舰面共振”状态,旋翼液压减摆器节流孔参数对舰载直升机机身振动幅值有较大的影响,随着减摆器节流孔孔径的增大,机身振动幅值大幅增加,直升机不稳定转速区扩大;舰船运动周期对机身振动幅值和不稳定转速区几乎没有影响;在不稳定转速区之外,舰船横摇角对机身振动稳态响应幅值的影响较明显。进入不稳定转速区后,由于自激振动影响,机身大幅振动,舰船横摇角对机身振动幅值的影响不再明显。
英文摘要:
      The influence of ship motion on helicopter dynamic stability is rarely analyzed in the research process of dynamic interaction between shipboard helicopter and flight deck as yet. Nonlinear characteristic of helicopter landing gear is not considered in the only research literatures. Multi-body dynamic numerical model of shipboard helicopter was built to analyze the shipboard helicopter dynamic characteristic in this paper. Models with nonlinear characteristics of hydraulic shock absorber and tire were established to improve fidelity and hydraulic lead-lag dampers were also included. The transient response of airframe model which withstand different ship roll angles, period of ship roll motion and parameter of lead-lag damper was parametric investigated. It is concluded that the diameter of lead-lag damper orifice play a great role in shipboard helicopter fuselage vibration. The amplitude of airframe vibration increases significantly and the rotor instable speed range expand with the increasing diameter of orifice, whereas the period of ship motion has little effect on it. It is also concluded that the influence of ship roll angle on fuselage steady state response amplitude is obvious out of the instable speed range, and become indistinct due to self-excited vibration within its instable speed range.
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