首页|桨叶分段线性扭转对降低旋翼振动载荷的作用分析

桨叶分段线性扭转对降低旋翼振动载荷的作用分析

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  • 国家科技期刊平台
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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.使用参数扫描以尽可能降低旋翼振动载荷.降低四阶垂向力方面,低速时桨叶所有段都需要扭转,而高速时未扭转的桨叶表现更好.降低四阶滚转和俯仰力矩方面,在低速时需要桨叶外段高度扭转,而在中高速时则需要桨叶中段的扭转.
Rotor Vibratory Load Reduction by Piecewise Linear Blade Twist
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 can reduce the 4/rev(revolution)vertical hub force at low speeds.The 4/rev force can be reduced by 99.5%with a-24°/R(R is the blade radius)twist at the middle segment at 80 km/h.The twist at the inner segment is not helpful for reducing the 4/rev rolling and pitching moments,while the twists at other segments can control both the moments at most speeds.A parameter sweep is conducted to minimize these loads.To reduce the 4/rev force,all the segments need to be twisted at low speeds,while untwisted blades perform better at high speeds.For controlling the 4/rev moments,the outer segment should be highly twisted at low speeds,while high twists at the middle segment are essential at medium to high speeds.

helicopter rotorsvibratory loadpiecewise blade twistvertical hub forcerolling momentpitching moment

张宇杭、韩东

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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

Active Control Rotor Technology ProjectNational Natural Science Foundation of ChinaPostgraduate Research&Practice Innovation Program of Jiangsu Province

FKFB2023110805511972181KYCX21_0228

2024

10.16356/j.1005-1120.2024.03.002

南京航空航天大学学报(英文版)
南京航空航天大学

南京航空航天大学学报(英文版)

CSTPCD
影响因子：0.279
ISSN：1005-1120
年,卷(期)：2024.41(3)
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