桨叶分段线性扭转对降低旋翼振动载荷的作用分析OACSTPCD
Rotor Vibratory Load Reduction by Piecewise Linear Blade Twist
研究了用桨叶分段线性扭转来降低旋翼振动载荷.使用基于弹性梁的旋翼模型用于预测旋翼振动载荷.采用4片桨叶旋翼作为基准旋翼,桨叶形状与UH-60直升机桨叶相似.桨叶被划分为内、中、外3段,讨论了各段扭转对载荷的影响.低速时桨叶每一段的扭转都能减少桨毂四阶垂向力.当以80 km/h前飞时,中段-24°/R的扭转可使其降低99.5%.桨叶内段的扭转不利于降低桨毂四阶滚转和俯仰力矩,另外两段的扭转则可以在大多数前飞速度时控制这2个振动力矩.使用参数扫描以尽…查看全部>>
Piecewise linear blade twist is studied as a method for reducing the rotor vibratory loads.A rotor model based on an elastic beam concept is used to predict the loads.A four-bladed rotor with a shape similar to the UH-60 rotor is used as a baseline for comparisons.The blade is divided into three segments,which are inner,middle and outer segments respectively.Effect of the twist at different segments on the loads is discussed.The twists at all the segments ca…查看全部>>
张宇杭;韩东
南京航空航天大学航空学院,直升机动力学全国重点实验室,南京 210016,中国南京航空航天大学航空学院,直升机动力学全国重点实验室,南京 210016,中国
直升机旋翼振动载荷分段桨叶扭转桨毂垂向力滚转力矩俯仰力矩
helicopter rotorsvibratory loadpiecewise blade twistvertical hub forcerolling momentpitching moment
《南京航空航天大学学报（英文版）》 2024 (3)
278-288,11
This work was supported by the Active Control Rotor Technology Project(No.FKFB20231108055),the National Natural Science Foundation of China(No.11972181),and the Postgraduate Research&Practice Innova-tion Program of Jiangsu Province(No.KYCX21_0228).
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