| 前飞状态直升机总距操纵响应特性计算 |
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| 引用本文： | 李春华,陈平剑,林永峰.前飞状态直升机总距操纵响应特性计算[J].直升机技术,2009(4). |
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| 作者姓名： | 李春华 陈平剑 林永峰 |
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| 作者单位： | 中国直升机设计研究所,景德镇,333001 |
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| 摘 要： | 本文对直升机运动方程中关键的旋翼气动力预测采用非定常分析计算模型,建立了时间推进自由尾迹方法。通过计算的孤立旋翼的总距操纵突变时的气动力响应与试验值的对比,验证了自由尾迹方法用于瞬时气动响应计算的有效性,然后利用嵌入自由尾迹模型的直升机运动方程分析了在前飞条件下,对旋翼进行总距阶跃突增及余弦突增操纵时,直升机载荷因子和平飞速度的时间响应历程。
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| 关 键 词： | 直升机 操纵响应 自由尾迹 |
Calculation on Helicopter Control Response for Forward Flight Based on Free Wake Model |
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| Authors: | LI Chunhua LIN Yongfeng CHEN Pingjian |
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| Institution: | LI Chunhua; LIN Yongfeng; CHEN Pingjian(China Helicopter Research and Development Institute; Jingdezhen; 333001); |
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| Abstract: | By the development of time-marching free wake model,an unsteady aerodynamic method was adopted in helicopter 3-D motion equation.By the comparisons of calculated aerodynamic responses with experimental results for isolate rotor,the present method was validated.Then the helicopter aerodynamic responses with abrupt or cosine increase of rotor collective pitch were calculated,and the time history of load factor and flight speed was analyzed. |
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| Keywords: | helicopter control response free wake |
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