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高速飞行器失控成因及操稳判据发展综述

张静 李华光 郑宏涛 唐鹏 蔡巧言 李贵成

张静, 李华光, 郑宏涛, 唐鹏, 蔡巧言, 李贵成. 高速飞行器失控成因及操稳判据发展综述[J]. 气体物理, 2021, 6(6): 1-12. doi: 10.19527/j.cnki.2096-1642.0914
引用本文: 张静, 李华光, 郑宏涛, 唐鹏, 蔡巧言, 李贵成. 高速飞行器失控成因及操稳判据发展综述[J]. 气体物理, 2021, 6(6): 1-12. doi: 10.19527/j.cnki.2096-1642.0914
ZHANG Jing, LI Hua-guang, ZHENG Hong-tao, TANG Peng, CAI Qiao-yan, LI Gui-cheng. Review on out of Control Inducement and Criteria of Operation and Stability of High Speed Vehicle[J]. PHYSICS OF GASES, 2021, 6(6): 1-12. doi: 10.19527/j.cnki.2096-1642.0914
Citation: ZHANG Jing, LI Hua-guang, ZHENG Hong-tao, TANG Peng, CAI Qiao-yan, LI Gui-cheng. Review on out of Control Inducement and Criteria of Operation and Stability of High Speed Vehicle[J]. PHYSICS OF GASES, 2021, 6(6): 1-12. doi: 10.19527/j.cnki.2096-1642.0914

高速飞行器失控成因及操稳判据发展综述

doi: 10.19527/j.cnki.2096-1642.0914
详细信息
    作者简介:

    张静(1982-)男, 博士, 研究员, 主要研究方向为高超飞行器总体、气动.E-mail: babyzj2001@126.com

  • 中图分类号: O354.4

Review on out of Control Inducement and Criteria of Operation and Stability of High Speed Vehicle

  • 摘要: 首先介绍了高速飞行器设计所面临的静稳定裕度、航向操纵性、三通道耦合、安全边界等问题,进一步梳理了高速飞行器的失控成因,包括飞行环境、飞行姿态、控制耦合、惯性耦合、动力学耦合等因素,在此基础上,回顾了一系列适用于飞行器设计的典型抗失控判据,如横航向稳定性参数、动态航向稳定性参数、横/航向操纵偏离参数、Weissman组合判据、横向稳定性特征参数等.这些参数或判据不仅可以在设计初期预测气动布局的好坏及其对操稳特性的影响,帮助工程师改进气动布局以使飞行器获得最佳的性能,还可用来预测飞行器在当前气动布局下所需要的控制资源以帮助飞行器合理应对耦合的影响,最后在设计完成后还可用这些判据分析飞行器飞行过程中的稳定性以及控制策略的合理性.

     

  • 图  1  改进后的Cnβ, dyn和LCDP组合操稳特性判据平面

    Figure  1.  Plot of depature and spin susceptibility criteria

    图  2  Kalviste α-β静稳定图

    Figure  2.  Kalviste α-β static stability plot

    图  3  Cnβ-Clβ, 和Cnδa判据平面

    Figure  3.  Bihrle applied research design guidelines for departure susceptibility and roll reversal

    图  4  偏离敏感等级随1/Tϕ1ξϕωnϕ变化趋势

    Figure  4.  Departure susceptibility rating versus lateral closed-loop divergence potential, 1/Tϕ1 or ξϕωnϕ

    图  5  Kalviste稳定参数对攻角和侧滑角的稳定域图

    Figure  5.  Kalviste stability parameters versus angle- of-attack and sideslip angle

    表  1  耦合特性引发飞行事故一览表

    Table  1.   List of flight accidents caused by the coupling characteristics

    times vehicles Ma accidents/events causes
    1953.12 Bell X-1A 2.44 The aircraft was temporatily out of control, with the ±8g normal overload appeared alternately, and the pilot fell into a semi-coma rolling inertia coupling
    1954.10 X-3 / The aircraft rolled quickly to the left, and the angle of attack and sideslip deviated by more than 20°, causing the plane to get out of control inertia coupling
    1954.10 F-100A / Inertial coupling induced the aircraft to get out of control, causing serious injuries to the pilot inertia coupling
    1955 YF-102 / Inertial coupling caused roll angle deviation of up to -30° and angle of attack deviation of -12° inertia coupling
    1956.9 Bell X-2 3.2 Rolling control induced the directional departure, further induced ±6g normal overload alternately, and finally the aircraft entered sub-sonic spin lateral-directional static coupling
    1959 X-15X-15A-2 6.7 The ventral fin caused roll instability and induced side slip oscillation. After the removal of the ventral fin, the rolling static stability and direction dynamic stability were improved lateral-directional dynamic coupling
    下载: 导出CSV

    表  2  判据的适用条件

    Table  2.   Application of the criteria

    parameters application conditions
    Cnβ>0,Clβ < 0 positive lateral/directional aerodynamic static stability, open-loop static stability criteria
    Cnβ, dyn>0,LCDP(AADP)>0 suitable for open-loop, symmetric, steady-state flight situations
    αβ>0, αβ>αδ another form of expression of Cnβ, dyn and LCDP
    Weissman criterion combined open and closed-loop lateral/directional departure/spin susceptibility criteria, suitable for open-loop, symmetric, steady-state flight situations
    1/Tθ3>0 predict the closed-loop divergence of the longitudinal, lateral and directional coupling
    Cnβ, cop>0,Cmα, cop <0, K>0 predict the open-loop divergence of asymmetric flight, suitable for large nonlinearity and large angle of attack
    Cnβ-Clβcriterion plane empirical static stability design charts applicable to large angle transient maneu-vering flight
    1/T1>-0.5 a closed-loop departure parameter in terms of preventing uncommanded motion via roll control inputs, applicable to augmented aircraft
    Cnβ, app>0 open-loop lateral/directional static departure susceptibility criterion that includes the static effect of the controls
    Kalviste dynamic stability parameters predict open-loop stability of an aircraft in steady maneuverinig flight
    LSDP reflects which is dominant in the lateral or deirectional stability
    kari-1/CP criteria plane helpful to select an effective lateral/directional control strategy according to the characteristc parameters of the criterion
    下载: 导出CSV
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  • 收稿日期:  2021-02-23
  • 修回日期:  2021-07-07

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