留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

直升机-吊挂耦合系统平衡特性和稳定性分析

曹龙 曹义华 李春华

曹龙, 曹义华, 李春华等 . 直升机-吊挂耦合系统平衡特性和稳定性分析[J]. 北京航空航天大学学报, 2014, 40(9): 1219-1224. doi: 10.13700/j.bh.1001-5965.2013.0561
引用本文: 曹龙, 曹义华, 李春华等 . 直升机-吊挂耦合系统平衡特性和稳定性分析[J]. 北京航空航天大学学报, 2014, 40(9): 1219-1224. doi: 10.13700/j.bh.1001-5965.2013.0561
Cao Long, Cao Yihua, Li Chunhuaet al. Equilibrium characteristics and stability analysis of helicopter-slung-load coupling system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(9): 1219-1224. doi: 10.13700/j.bh.1001-5965.2013.0561(in Chinese)
Citation: Cao Long, Cao Yihua, Li Chunhuaet al. Equilibrium characteristics and stability analysis of helicopter-slung-load coupling system[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(9): 1219-1224. doi: 10.13700/j.bh.1001-5965.2013.0561(in Chinese)

直升机-吊挂耦合系统平衡特性和稳定性分析

doi: 10.13700/j.bh.1001-5965.2013.0561
详细信息
    作者简介:

    曹龙(1988-),男,湖北大悟人,博士生,caolong.buaa@gmail.com.

  • 中图分类号: V211.3

Equilibrium characteristics and stability analysis of helicopter-slung-load coupling system

  • 摘要: 基于单质点吊挂假设,建立了直升机-吊挂耦合系统的非线性动力学模型。在该假设下,吊挂将引入额外的自由度和约束,使运动方程增加4阶,且为隐式的微分代数方程组。通过将惯性力中的广义加速度项与广义速度的二次项分离,可将运动方程转化为显式的微分方程组。针对无吊挂的直升机本体和直升机-吊挂耦合系统这两种模型,采用直接数值方法,计算了它们以不同速度做零侧滑定直平飞的配平状态,并结合飞行试验数据进行对比。进一步对两种模型进行了小扰动线化处理,分析其运动模态并进行对比。结果表明,单质点吊挂会给系统引入两个新的运动模态,使得吊挂两个自由度上的运动与直升机高度响应产生耦合,同时改变直升机本体各个模态的特性,会使部分模态响应品质变坏。

     

  • [1] Sampath P.Dynamics of a helicopter-slung load system[D].Maryland:University of Maryland,1980
    [2] Ronen T.Dynamics of a helicopter with a slung load [D].Stanford:Stanford University,1986
    [3] Heffley R K,Jewell W F,Lehman J M,et al.A compilation and analysis of helicopter handling qualities data,volume one:data compilation[R].NASA-CR-3144,1980
    [4] Fusato D,Guglieri G,Celi R.Flight dynamics of an articulated rotor helicopter with an external slung load [J].Journal of the American Helicopter Society,2001,46(1):3-13
    [5] Thanapalan K,Wong T M.Modeling of a helicopter with an under-slung load system[C]//Proceedings of the 29th Chinese Control Conference.Piscataway,NJ:IEEE,2010:1451-1456
    [6] Stucky R A.Mathematical modelling of helicopter slung-load system[R].DSTO-TR-1257,2002
    [7] Cicolani L S,Cone A,Theron J N.Flight test and simulation of a cargo container slung load in forward flight[J].Journal of the American Helicopter Society,2009,54(3):032006-1-18
    [8] 崔瑛.直升机吊挂飞行稳定性分析[D].南京:南京航空航天大学,2005 Cui Ying.Stability analysis of a helicopter with an external slung load[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2005(in Chinese)
    [9] 吴鹏,马成江,朱国民.直升机吊挂飞行动力学建模与分析[J].直升机技术,2010,165(4):33-36 Wu Peng,Ma Chengjiang,Zhu Guomin.Flight dynamics modeling and handling quality analysis of helicopter with slung-load[J].Helicopter Technique,2010,165(4):33-36(in Chinese)
    [10] 齐万涛,陈仁良.直升机吊挂飞行稳定性和操纵性分析[J].南京航空航天大学学报,2011,43(3):406-412 Qi Wantao,Chen Renliang.Stability and control characteristic analysis for flight of helicopter with slung-load[J].Journal of Nanjing University of Aeronautics and Astronautics,2011,43(3):406-412(in Chinese)
    [11] 崔利,曹义华,李国知.直升机吊挂飞行平衡、稳定性与操纵性研究[J].航空动力学报,2010,25(10):2307-2311 Cui Li,Cao Yihua,Li Guozhi.Studies on trims,stability,and controllability of helicopter with slung-load[J].Journal of Aerospace Power,2010,25(10):2307-2311(in Chinese)
    [12] 马超,曹义华,徐忠达.直升机吊挂流场数值模拟与尾鳍设计分析[J].北京航空航天大学学报,2012,38(5):654-658 Ma Chao,Cao Yihua,Xu Zhongda.Numerical simulation of helicopter slung-load flow field and fins design[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(5):654-658(in Chinese)
    [13] 曹龙,曹义华,马超,等.直升机吊挂构型计算及稳定性分析[J].北京航空航天大学学报,2012,38(6):711-714 Cao Long,Cao Yihua,Ma Chao,et al.Analysis on stability and structure computation of helicopter with slung-load[J].Journal of Beijing University of Aeronautics and Astronautics,2012,38(6):711-714(in Chinese)
    [14] Sturgeon W R.A mathematical model of the CH-53 helicopter[R].NASA TM-81238,1980
    [15] Ostroff A J,Downing D R,Rood W J.A technique using a nonlinear helicopter model for determining trims and derivatives[R].NASA TN-D-8159,1976
    [16] Ananthkrishnan N,Sinha N K.Level flight trim and stability analysis using extended bifurcation and continuation procedure[J].Journal of Guidance,Control,and Dynamics,2000,24(6):1225-1228

  • 加载中
计量
  • 文章访问数:  1180
  • HTML全文浏览量:  61
  • PDF下载量:  688
  • 被引次数: 0
出版历程
  • 收稿日期:  2013-10-10
  • 网络出版日期:  2014-09-20

目录

    /

    返回文章
    返回
    常见问答