带后缘襟翼的直升机桨叶动态扭转特性分析
首发时间:2009-02-10
摘要:通过桨叶后缘襟翼的高频振动可以主动地控制旋翼传给直升机机身的振动载荷。本文提出了带后缘襟翼的直升机桨叶动态扭转特性的分析方法。后缘襟翼的气动力计算采用修正的Greensberg准定常气动理论。桨叶的结构模型采用21节点的中等变形梁模型。采用Newmark数值积分法求解桨叶的非线性运动方程。数值结果表明:随着后缘襟翼偏转速率的增加,桨叶扭转角、挥舞位移和旋翼拉力的波动量也随之增大。桨叶扭转振动峰峰值的大小和襟翼的振动频率有关,当襟翼的振动频率在旋转桨叶扭转一阶固有频率附近时,峰峰值达到最大值;桨叶扭转与襟翼振动之间的相位差也和襟翼的振动频率有关,当无量纲角频率为4时,桨尖扭转振动落后襟翼振动近1/4个周期。
关键词: 直升机 复合材料桨叶 后缘襟翼 扭转变形 动态特性
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Dynamic torsion of helicopter blade with trailing-edge flap
Abstract:To reduce vibrations in helicopters can be using active trailing-edge flaps on the rotor blades. The dynamic model of the helicopter blade with the trailing-edge flap is developed based on the modified Greensberg quasi- static aerodynamic theory. A 21-DOF beam finite element, including transverse shear DOF and warping DOF, is developed for analysis. The governing differential equations of motion can be solved by Newmark method. Results show that the fluctuation value of torsion and flapping deflection and rotor thrust increase with the increasing of the flapping speed of the trailing-edge flap. The peak to peak value of the torsion is related with the frequency of the trailing-edge flap. When the frequency is near the first torsion of the rotating blade, the peak to peak value of the torsion is maximum. The phase angle between the torsion and trailing-edge flap is also related with the frequency of the flap. The phase angle is about the quarter of a rotating period when the non-dimensional angle frequency is 4.
Keywords: Helicopter Composite Blade Trailing-edge flap Torsion Dynamic characteristics
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