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倾转四旋翼飞行器倾转过渡走廊分析方法

俞志明 陈仁良 孔卫红

俞志明, 陈仁良, 孔卫红等 . 倾转四旋翼飞行器倾转过渡走廊分析方法[J]. 北京航空航天大学学报, 2020, 46(11): 2106-2113. doi: 10.13700/j.bh.1001-5965.2019.0594
引用本文: 俞志明, 陈仁良, 孔卫红等 . 倾转四旋翼飞行器倾转过渡走廊分析方法[J]. 北京航空航天大学学报, 2020, 46(11): 2106-2113. doi: 10.13700/j.bh.1001-5965.2019.0594
YU Zhiming, CHEN Renliang, KONG Weihonget al. Analysis method for conversion corridor of quad tilt rotor aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(11): 2106-2113. doi: 10.13700/j.bh.1001-5965.2019.0594(in Chinese)
Citation: YU Zhiming, CHEN Renliang, KONG Weihonget al. Analysis method for conversion corridor of quad tilt rotor aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(11): 2106-2113. doi: 10.13700/j.bh.1001-5965.2019.0594(in Chinese)

倾转四旋翼飞行器倾转过渡走廊分析方法

doi: 10.13700/j.bh.1001-5965.2019.0594
基金项目: 

国家自然科学基金 11672128

详细信息
    作者简介:

    俞志明  男, 博士研究生。主要研究方向:旋翼飞行器飞行力学及直升机总体设计

    陈仁良  男, 博士, 教授, 博士生导师。主要研究方向:直升机空气动力学、直升机飞行力学与控制及直升机多学科优化设计

    孔卫红  女, 博士, 副教授。主要研究方向:直升机空气动力学及飞行力学

    通讯作者:

    陈仁良, E-mail: crlae@nuaa.edu.cn

  • 中图分类号: V212.4

Analysis method for conversion corridor of quad tilt rotor aircraft

Funds: 

National Natural Science Foundation of China 11672128

More Information
  • 摘要:

    针对倾转四旋翼(QTR)飞行器过渡飞行中的变速、变体特点,提出了一种确定倾转四旋翼飞行器倾转过渡走廊的方法,该方法从飞行力学角度用机翼升力特性限制低速和高速边界,以单旋翼可用功率限制高速边界。所提方法确定了无周期变距的倾转四旋翼飞行器样机倾转过渡走廊,并分析了其在倾转过渡飞行中不同机体迎角下各气动部件的气动力以及前后旋翼需用功率随飞行速度的变化规律。结果表明:倾转四旋翼飞行器在小机体迎角下倾转优于在大机体迎角下倾转;各气动部件提供的垂向力占比会随着机体迎角的改变而变化;机翼升力特性高速边界和单旋翼功率限制边界共同组成了倾转四旋翼飞行器倾转过渡走廊的高速边界;单旋翼可用功率限制边界比总可用功率限制边界更严格。

     

  • 图 1  作用在倾转四旋翼飞行器上的外力

    Figure 1.  Forces acting on quad tilt rotor aircraft

    图 2  倾转过渡走廊计算流程

    Figure 2.  Flowchart for computing conversion corridor

    图 3  旋翼模型验证

    Figure 3.  Rotor model verification

    图 4  等机体迎角倾转时短舱倾转角与前飞速度的关系

    Figure 4.  Relation between tilt angle of nacelle and forward speed at constant angle of attack of fuselage

    图 5  机体迎角为-6°时各气动部件垂向气动力随前飞速度的变化

    Figure 5.  Variation of vertical aerodynamic force of each pneumatic component with flight speed at -6°angle of attack of fuselage

    图 6  机体迎角为0°时各气动部件垂向气动力随前飞速度的变化

    Figure 6.  Variation of vertical aerodynamic force of each pneumatic component with flight speed at 0°angle of attack of fuselage

    图 7  机体迎角为10°时各气动部件垂向气动力随前飞速度的变化

    Figure 7.  Variation of vertical aerodynamic force of each pneumatic component with flight speed at 10°angle of attack of fuselage

    图 8  等短舱倾转角时前旋翼需用功率随前飞速度变化

    Figure 8.  Variation of required power of front rotor with flight speed at constant tilt angle of nacelle

    图 9  等短舱倾转角时后旋翼需用功率随前飞速度变化

    Figure 9.  Variation of required power of rear rotor with flight speed at constant tilt angle of nacelle

    图 10  算例飞行器的倾转过渡走廊

    Figure 10.  Conversion corridor of example aircraft

    表  1  算例倾转四旋翼飞行器主要参数

    Table  1.   Main parameters of example quad tilt rotor aircraft

    参数 数值
    设计总重/kg 60
    半径/m 0.58
    特征弦长/m 0.057
    桨叶片数 3
    旋翼实度 0.076
    短舱倾转角/(°) 0~90
    旋翼转速/(r·min-1) 2 400
    前/后机翼展长/m 1.6/2.2
    前/后机翼弦长/m 0.3/0.3
    前/后机翼安装角/(°) 6.5/3
    电机数量 4
    单个电机功率/kW 4.8
    机身特征长度/m 2.4
    机身特征面积/m2 0.12
    下载: 导出CSV
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出版历程
  • 收稿日期:  2019-11-20
  • 录用日期:  2019-12-27
  • 网络出版日期:  2020-11-20

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