To study the influence of this damper configuration to aeromechanical stability , some work has been done in this thesis . first , dynamic equation of the rotor - hub system was modeled with the generalized hamilton principle , which can be used to analyze the stability problem in different conditions like on - ground , hovering and flight . when fastening the fuselage , the model can also be used to analyze the stability problem of isolated rotor system 為了研究這種新型布置減擺器對直升機穩(wěn)定性的影響,本文所作研究工作如下:首先,本文利用廣義的hamilton原理建立了適用于不同狀態(tài)(地面、懸停和前飛)的旋翼/機體耦合系統(tǒng)的動力學(xué)模型,該模型中將機體固定可以用來分析孤立旋翼的穩(wěn)定性問題。