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飞翼布局飞机舵面偏转速率设计

何倩琳 王立新

何倩琳, 王立新. 飞翼布局飞机舵面偏转速率设计[J]. 北京航空航天大学学报, 2015, 41(9): 1729-1735. doi: 10.13700/j.bh.1001-5965.2014.0631
引用本文: 何倩琳, 王立新. 飞翼布局飞机舵面偏转速率设计[J]. 北京航空航天大学学报, 2015, 41(9): 1729-1735. doi: 10.13700/j.bh.1001-5965.2014.0631
HE Qianlin, WANG Lixin. Design of actuator rate for flying wing aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1729-1735. doi: 10.13700/j.bh.1001-5965.2014.0631(in Chinese)
Citation: HE Qianlin, WANG Lixin. Design of actuator rate for flying wing aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(9): 1729-1735. doi: 10.13700/j.bh.1001-5965.2014.0631(in Chinese)

飞翼布局飞机舵面偏转速率设计

doi: 10.13700/j.bh.1001-5965.2014.0631
详细信息
    作者简介:

    何倩琳(1990—),女,浙江义乌人,硕士研究生,hql47730@gmail.com

    通讯作者:

    王立新(1965—),男,江西南丰人,教授,wlx_c818@163.com,主要研究方向为飞机设计、飞行动力学与飞行控制.

  • 中图分类号: V212.1

Design of actuator rate for flying wing aircraft

  • 摘要: 舵面偏转速率的大小是飞机飞行控制系统设计的重要约束之一.当偏转速率饱和时,在外界干扰或操纵下,飞机可能进入自激振荡(PIO)状态,导致飞行品质下降.建立了飞翼布局飞机舵面偏转速率限制值的设计方法,给出了某大展弦比飞翼布局飞机的三轴主操纵面偏转速率设计的算例,分析了偏转速率限制对飞机动态响应特性的影响及其与飞机本体气动导数、转动惯量、展弦比构成的组合参数间的关系.结果表明:对于大展弦比飞翼布局飞机而言,其横向主操纵面偏转速率限制值要求最高,纵向次之,航向最低.研究方法和结果可用于飞翼布局飞机的操纵舵面与飞行控制系统初步设计时参考.

     

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出版历程
  • 收稿日期:  2014-10-14
  • 刊出日期:  2015-09-20

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