模态修型减振的旋翼桨毂谐波振动载荷计算  

Calculation research of rotor hub harmonic vibration loads by the modal shaping method

作　　者：李波陈 王红州[1] 刘焜[1] 文曦[2] 王晓庆[3] 

机构地区：[1]合肥工业大学230009合肥 [2]中国航天空气动力技术研究院100074北京 [3]中电集团第27研究所450000郑州

出　　处：《应用力学学报》2015年第2期323-327,359,共5页Chinese Journal of Applied Mechanics

基　　金：国家青年自然基金(11302065);大学生创新训练计划项目(201310359001);中央高校基本科研业务费专项资金

摘　　要：基于模态修型的方法推导了直升机旋翼桨叶根部剪力的计算公式,通过合成桨叶根部载荷推导了旋翼桨毂的谐波振动载荷公式。将本文建立的桨毂谐波载荷计算模型与商用软件CAMRAD计算出的结果进行对比,结果表明:本文所建立模型的旋翼计算频率与CAMRAD计算的频率相比,基阶频率计算误差在2%以内,前十阶频率误差都在8%以内;与已有文献试验测试的桨毂谐波振动载荷相比最大误差在25%以内。说明了本文建立的旋翼桨毂谐波振动载荷计算模型具有可行性和有效性。Based on the modal shaping method, harmonic vibration loads of helicopter rotor blade root are deduced, rotor hub harmonic vibration loads are calculated together with the blade root load vector superposition. Compared with the results by using CAMRAD commercial software, the error of the modal frequency of rotor model established in this paper is within 2%, and the first ten order frequencies errors are within 8%. Compared with the examples in existed references, the maximum error of the calculated rotor hub harmonic vibration loads is within 25%. The feasibility and effectiveness of the established model for the rotor hub harmonic vibration loads calculation is demonstrated.

关 键 词：谐波振动载荷 气弹动力学 模态修型 振动减振 铰接式旋翼 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] V214.33