机动飞行时安装角对转子叶片振动的影响

提出旋转转子叶片在轴线发生平面偏转时的振动问题。在非线性曲杆理论的基础上，建立了在陀螺力作用下叶片振动的微分程及其求解方法，并进行了数值分析。结果表明，安装角在不同取值范围和不同转速范围对叶片振动的影响是完全不同的。对于无扭向叶片在低转速下，安装角对振动的影响是显著的；而在高转速下则是很微弱的。当安装角在某个较大的范围取值时，可有效地减弱该运动状态所导致的振动。

INFLUENCE OF INSTALLATION ANGLE ON VIBRATIONS DURING MANEUVRING FLIGHT

This paper deals with the problem about oscillations of rotating blades due to plane deflection of the axis.This kind of motions appears during aircraft performing maneuvers.According to nonlinear theory of curvilinear rods,a system of differential equations for blades vibrations under gyroscopic loads is set up,and its solution is found out.Then a numerical analysis shows that the influence of installation angle on oscillations of unpretwisted blade is closely related with its rotational speed:This influence is very obvious when its rotational speed is low,but becomes quite weak when its rotational speed becomes high;Meanwhile if the installation angle is chosen big enough,the blade vibrations in two planes due to this motion can be effectively reduced at any rotational speed of the rotor.At last,it must be pointed out that the above conclusion is only true for the unpretwisted blades,but for pretwisted ones their oscillation behavior will be extremely complicated.