Mathematical model and formulations of a new tilt - rotor aircraft for aeroelastic stability analysis 新型傾轉旋翼機氣動彈性穩(wěn)定性分析模型
The multi - body analysis of the aeroelastic stability of the tiltrotor aircraft is presented 摘要通過多體動力學方法建立了傾轉旋翼機動力學分析模型。
Model experiment and damping identification for aeroelastic stability of helicopter rotor with elastomeric lag damper 帶粘彈減擺器旋翼系統(tǒng)氣彈穩(wěn)定性試驗與阻尼識別
Numerical simulations demonstrate that the multi body analytical model can analyze the aeroelastic stability of the tiltrotor aircraft in the helicopter mode 數值計算表明:建立的多體動力學模型能夠快速分析直升機模式下傾轉旋翼機復雜的旋翼機翼氣彈耦合動力學特性。
By numerical simulation , the servo system in this paper greatly reduces the aeroelastic stability . the structural flitter added to the system can reduce the coupling effect of servo system and structure mode and increase the flutter velocity 通過數值模擬發(fā)現(xiàn),伺服系統(tǒng)會降低原有氣動彈性系統(tǒng)的穩(wěn)定性,結構陷波器的引入可以減弱伺服系統(tǒng)和結構模態(tài)的耦合。