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基于气动导数的类X-37B飞行器纵向稳定性分析

张庆 叶正寅

张庆, 叶正寅. 基于气动导数的类X-37B飞行器纵向稳定性分析[J]. 北京航空航天大学学报, 2020, 46(1): 77-85. doi: 10.13700/j.bh.1001-5965.2019.0188
引用本文: 张庆, 叶正寅. 基于气动导数的类X-37B飞行器纵向稳定性分析[J]. 北京航空航天大学学报, 2020, 46(1): 77-85. doi: 10.13700/j.bh.1001-5965.2019.0188
ZHANG Qing, YE Zhengyin. Longitudinal stability analysis for X-37B like trans-atmospheric orbital test vehicle based on aerodynamic derivatives[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(1): 77-85. doi: 10.13700/j.bh.1001-5965.2019.0188(in Chinese)
Citation: ZHANG Qing, YE Zhengyin. Longitudinal stability analysis for X-37B like trans-atmospheric orbital test vehicle based on aerodynamic derivatives[J]. Journal of Beijing University of Aeronautics and Astronautics, 2020, 46(1): 77-85. doi: 10.13700/j.bh.1001-5965.2019.0188(in Chinese)

基于气动导数的类X-37B飞行器纵向稳定性分析

doi: 10.13700/j.bh.1001-5965.2019.0188
基金项目: 

国家“863”计划 2014AA7060201

国家自然科学基金 11732013

陕西省自然科学基础研究计划 2019JM-290

详细信息
    作者简介:

    张庆  男, 博士, 讲师。主要研究方向:微型飞行器气动布局设计、超声速机翼优化设计

    叶正寅  男, 博士, 教授, 博士生导师。主要研究方向:飞行器气动弹性力学、非定常空气动力学

    通讯作者:

    叶正寅,E-mail:yezy@nwpu.edu.cn

  • 中图分类号: V212.12

Longitudinal stability analysis for X-37B like trans-atmospheric orbital test vehicle based on aerodynamic derivatives

Funds: 

National High-tech Research and Development Program of China 2014AA7060201

National Natural Science Foundation of China 11732013

Shaanxi Provincial Research Foundation for Basic Research on Natural Science, China 2019JM-290

More Information
  • 摘要:

    为了定量地研究跨大气层轨道飞行器在不同飞行条件下俯仰方向的动态特性,在Etkin气动力模型的基础上,详细研究了飞行马赫数、减缩频率、振动幅值、平均迎角等因素对此类飞行器纵向动态特性的影响规律。研究结果表明,平均迎角和飞行马赫数决定了流场的基本特性,所以对气动导数的影响很大;而减缩频率和振动幅值决定了非定常扰动的强弱,影响非定常气动力的大小,决定非定常迟滞效应的强弱。对类似X-37B的跨大气层轨道飞行器来说,平均迎角越大,机身后方背风区的涡流作用越强,纵向稳定性越强。在亚声速范围内,随着飞行马赫数增加,纵向稳定性增强,在超声速范围内,随着飞行马赫数增大,纵向稳定性减弱。振动幅值大小虽然影响了流场的形态,但对气动导数的数值大小没有明显影响。振动频率对动态特性的影响也不明显。希望研究结果可为中国未来类似飞行器的研究和发展提供相应的参考和技术储备。

     

  • 图 1  钝锥的几何外形和计算采用的混合网格

    Figure 1.  Blunted cone's geometric profile and hybrid mesh for computation

    图 2  俯仰阻尼随迎角的变化曲线

    Figure 2.  Variation curves of damping in pitching motion with angle of attack

    图 3  跨大气层轨道飞行器的几何外形和计算采用的混合网格

    Figure 3.  Tran-atmospheric orbiter's geometric profile and hybrid mesh for computation

    图 4  不同平均迎角时的俯仰力矩系数迟滞曲线

    Figure 4.  Hysteresis curves of pitching moment coefficient at various average angle of attack

    图 5  不同平均迎角时的俯仰组合气动导数变化曲线

    Figure 5.  Combined pitching aerodynamic derivative variation curves at various average angle of attack

    图 6  不同振动幅值时的俯仰力矩系数迟滞曲线

    Figure 6.  Hysteresis curves of pitching moment coefficient at various oscillation amplitude

    图 7  不同振动幅值时的俯仰组合气动导数变化曲线

    Figure 7.  Combined pitching aerodynamic derivative variation curves at various oscillation amplitude

    图 8  不同飞行马赫数时的俯仰力矩系数迟滞曲线

    Figure 8.  Hysteresis curves of pitching moment coefficient at various Mach number in flight

    图 9  不同飞行马赫数时的俯仰组合气动导数变化曲线

    Figure 9.  Combined pitching aerodynamic derivative variation curves at various Mach number in flight

    图 10  不同振动频率时俯仰力矩系数迟滞曲线

    Figure 10.  Hysteresis curves of pitching moment coefficient at various oscillation frequency

    图 11  不同振动频率时的俯仰组合气动导数变化曲线

    Figure 11.  Combined dynamic derivative variation curve at various oscillation frequency

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出版历程
  • 收稿日期:  2019-04-28
  • 录用日期:  2019-08-30
  • 刊出日期:  2020-01-20

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