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舰载机弹射起飞安全性的影响因素分析

董阿鹏 李书 朱文国 吴伟潇

董阿鹏, 李书, 朱文国, 等 . 舰载机弹射起飞安全性的影响因素分析[J]. 北京航空航天大学学报, 2018, 44(11): 2396-2404. doi: 10.13700/j.bh.1001-5965.2018.0151
引用本文: 董阿鹏, 李书, 朱文国, 等 . 舰载机弹射起飞安全性的影响因素分析[J]. 北京航空航天大学学报, 2018, 44(11): 2396-2404. doi: 10.13700/j.bh.1001-5965.2018.0151
DONG Apeng, LI Shu, ZHU Wenguo, et al. Influence factor analysis of catapult launch safety for carrier-based aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(11): 2396-2404. doi: 10.13700/j.bh.1001-5965.2018.0151(in Chinese)
Citation: DONG Apeng, LI Shu, ZHU Wenguo, et al. Influence factor analysis of catapult launch safety for carrier-based aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2018, 44(11): 2396-2404. doi: 10.13700/j.bh.1001-5965.2018.0151(in Chinese)

舰载机弹射起飞安全性的影响因素分析

doi: 10.13700/j.bh.1001-5965.2018.0151
基金项目: 

国家“863”计划 2012AA112201

详细信息
    作者简介:

    董阿鹏  男, 博士研究生。主要研究方向:多体动力学

    李书  男, 博士, 教授, 博士生导师。主要研究方向:飞行器结构设计

    朱文国  男, 博士研究生。主要研究方向:多体动力学

    吴伟潇  男, 硕士研究生。主要研究方向:飞行器结构设计

    通讯作者:

    李书, E-mail:lishu@buaa.edu.cn

  • 中图分类号: V221+.6;O313.7

Influence factor analysis of catapult launch safety for carrier-based aircraft

Funds: 

National High-tech Research and Development Program of China 2012AA112201

More Information
  • 摘要:

    为了全面考察舰载机(CBA)弹射起飞系统的安全性能,在绝对坐标系下,利用自然坐标法,建立了弹射起飞过程的多体耦合动力学模型,结合舰载机弹射仿真曲线,从舰载机加速度和飞行轨迹两方面研究了不同参数对弹射安全的影响规律。仿真结果表明:在弹射滑跑阶段,弹射力对水平加速度影响较大,在自由飞行阶段,发动机推力对水平加速度影响较大,而起飞重量在整个弹射过程对加速度均有明显影响;定力栓临界值的增大对加速度、飞行轨迹影响不大,但需要考虑其带来的结构振动和时延效应;较长的剩余甲板可以增加离舰升力,从而有效减小离舰下沉量;舰船纵摇可引起飞行轨迹大幅下沉,应避免舰船纵摇位移最大的时刻离舰起飞,其中舰船运动引起牵制杆的提前释放也应是控制弹射时间的考虑因素之一;弹射起飞安全性设计是一个多变量寻优过程,单一要素的优化难以得到满意结果,需综合分析各要素的影响。

     

  • 图 1  多体起飞弹射系统的拓扑结构

    Figure 1.  Topological structure of multi-body catapult launch system

    图 2  多体起飞弹射系统示意图

    Figure 2.  Schematic diagram of multi-body catapult launch system

    图 3  起飞重量对水平速度与飞行轨迹的影响

    Figure 3.  Effects of takeoff weight on horizontal velocity and flight trajectory

    图 4  弹射阀开启速率对水平速度与飞行轨迹的影响

    Figure 4.  Effects of opening rate of catapult valve on horizontal velocity and flight trajectory

    图 5  发动机推力对水平速度与飞行轨迹的影响

    Figure 5.  Effects of engine thrust on horizontal velocity and flight trajectory

    图 6  定力栓临界值对水平速度、前支柱气簧力与飞行轨迹的影响

    Figure 6.  Effects of critical value of fixed-load plug on horizontal velocity, nose-strut spring force and flight trajectory

    图 7  剩余甲板长度对铅垂升力与飞行轨迹的影响

    Figure 7.  Effects of deck edge distance on vertical lift and flight trajectory

    图 8  舰船运动对水平速度与飞行轨迹的影响

    Figure 8.  Effects of carrier motion on horizontal velocity and flight trajectory

    表  1  起落架缓冲器主要参数

    Table  1.   Main parameters of landing gear buffer module

    参数 前起 主起
    支柱倾角/(°) -4 5
    缓冲行程/cm 72 58
    全压-停机压缩比 3 2
    机轮胎压/MPa 2.6 1.8
    轮胎型号Ⅷ/mm 600×180-280 900×275-370
    注:停机行程比为0.56;活塞面积为0.02 m2;阻尼面积比为0.015;停机-全伸压缩比为3。
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-03-22
  • 录用日期:  2018-05-04
  • 刊出日期:  2018-11-20

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