摘要
建立了适用于变转速旋翼直升机的综合分析模型,该模型可用于综合分析直升机稳态飞行时的旋翼需用功率、全机配平操纵、旋翼桨毂振动水平与旋翼气动噪声。并且使用UH-60A"黑鹰"直升机的飞行试验数据及相关研究结果验证综合分析方法的准确性。在此基础上,分析旋翼转速变化对旋翼需用功率、全机配平操纵、旋翼桨毂振动水平与旋翼气动噪声的影响,从而为转速优化设计提供依据。结果表明,改变旋翼转速会导致上述4个特性同时发生明显变化,而在本文算例中适当地降低旋翼转速可最多降低19.2%的旋翼需用功率与6.7%的旋翼气动噪声,但是却会造成旋翼操纵受限和旋翼桨毂振动增加的不良后果。
A comprehensive analysis model suitable for the helicopter with variable rotor speed is established.The model is able to calculate the rotor required power,trim controls,rotor hub vibration level and rotor noise of a helicopter in steady flight.And the flight data of UH-60A helicopter and related research results are used to validate the accuracy of the model.In order to provide the basis for the optimization design of rotor speed,the study is carried out to analyze the influence of variable rotor speed on rotor required power,trim controls,rotor hub vibration level and rotor noise.The results indicate that the variation of rotor speed have great impacts on the four characteristics above.19.2%of rotor required power and 6.7%of rotor noise can be reduced by decreasing rotor speed properly,but at the cost of reducing the rotor control margin and increasing the rotor hub vibration.
作者
池骋
陈仁良
CHI Cheng;CHEN Renliang(National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics&Astronautics,Nanjing,210016,China)
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2018年第5期629-639,共11页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家自然科学基金(11672128)资助项目
江苏高校优势学科建设工程资助项目
关键词
直升机
变转速旋翼
综合分析
helicopter
variable speed rotor
comprehensive analysis
