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高超声速飞行器平稳滑翔弹道设计方法

胡锦川 陈万春

胡锦川, 陈万春. 高超声速飞行器平稳滑翔弹道设计方法[J]. 北京航空航天大学学报, 2015, 41(8): 1464-1475. doi: 10.13700/j.bh.1001-5965.2014.0023
引用本文: 胡锦川, 陈万春. 高超声速飞行器平稳滑翔弹道设计方法[J]. 北京航空航天大学学报, 2015, 41(8): 1464-1475. doi: 10.13700/j.bh.1001-5965.2014.0023
HU Jinchuan, CHEN Wanchun. Steady glide trajectory planning method for hypersonic reentry vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8): 1464-1475. doi: 10.13700/j.bh.1001-5965.2014.0023(in Chinese)
Citation: HU Jinchuan, CHEN Wanchun. Steady glide trajectory planning method for hypersonic reentry vehicle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(8): 1464-1475. doi: 10.13700/j.bh.1001-5965.2014.0023(in Chinese)

高超声速飞行器平稳滑翔弹道设计方法

doi: 10.13700/j.bh.1001-5965.2014.0023
详细信息
    作者简介:

    胡锦川(1986-),男,湖南岳阳人,博士研究生,yuhang_hu@126.com

    通讯作者:

    陈万春(1964-),男,北京人,教授,wanchun_chen@buaa.edu.cn,主要研究方向为飞行力学、制导与控制.

  • 中图分类号: V221+.3;TB553

Steady glide trajectory planning method for hypersonic reentry vehicle

  • 摘要: 针对已知攻角和倾侧角的高超声速飞行器平衡滑翔再入问题,提出了满足纵向加速度变化率最小的平稳滑翔弹道概念,并给出了平稳滑翔弹道设计方法.首先采用正则摄动的方法对高度动态微分方程进行求解,获得了精度较高的平稳滑翔高度、弹道倾角和纵向加速度解析解.然后对平稳滑翔弹道的动态特性进行了分析,结果表明该弹道具有自然稳定性和弱阻尼性.进一步给出了弹道振荡的自然频率和阻尼表达式,其中自然频率仅与速度相关,而阻尼则与速度和纵向升阻比相关.最后,通过比较高度偏差的比例反馈、微分反馈和比例+微分反馈3种方案,得出纯微分反馈是实现平稳滑翔的最佳方案,并给出了定阻尼微分反馈系数的表达式.仿真校验表明:该方案具有控制平滑、弹道振荡收敛速度快及鲁棒性好等特点.

     

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出版历程
  • 收稿日期:  2015-01-12
  • 刊出日期:  2015-08-20

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