北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (4): 705-713.doi: 10.13700/j.bh.1001-5965.2018.0430

• 论文 • 上一篇    下一篇

结冰飞机非线性稳定域确定及安全操纵方法

周驰, 李颖晖, 郑无计, 武朋玮, 董泽洪   

  1. 空军工程大学 航空工程学院, 西安 710038
  • 收稿日期:2018-07-13 出版日期:2019-04-20 发布日期:2019-04-26
  • 通讯作者: 李颖晖 E-mail:liyinghui66@163.com
  • 作者简介:周驰,男,博士研究生。主要研究方向:先进控制理论及应用;李颖晖,女,博士,教授。主要研究方向:非线性控制理论;郑无计,男,博士研究生。主要研究方向:飞行安全与飞行控制;武朋玮,男,硕士研究生。主要研究方向:飞行安全与可达性分析;董泽洪,男,硕士研究生。主要研究方向:先进控制理论及应用。
  • 基金资助:
    国家"973"计划(2015CB755805)

Nonlinear stability region determination and safety manipulation strategies for icing aircraft

ZHOU Chi, LI Yinghui, ZHENG Wuji, WU Pengwei, DONG Zehong   

  1. Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China
  • Received:2018-07-13 Online:2019-04-20 Published:2019-04-26
  • Supported by:
    National Basic Research Program of China (2015CB755805)

摘要: 结冰会恶化飞机的动力学特性,造成飞行包线收缩,威胁飞行安全,研究结冰后飞机的非线性稳定域变化对于驾驶员操纵应对策略设计以及飞行安全的提高具有重要意义。以NASA的GTM为案例飞机,首先对飞机气动参数进行多项式拟合,同时结合结冰因子模型,建立了飞机在结冰条件下的纵向通道动力学模型;然后通过分岔分析方法对飞机在不同程度结冰条件和操纵指令下的飞行状态变化进行了研究,并将其用于指导驾驶员操纵,同时考虑到分岔分析方法的局限性,利用微分流形理论确定了飞行系统的非线性稳定域,并将其作为飞行安全边界;最后针对结冰情形,提出将分岔分析方法与微分流形理论相结合共同用于操纵指导,并进行了操纵时域验证。研究结果表明,结冰会使安全边界收缩,在小扰动的作用下都可能使飞行状态超出安全边界。随着结冰程度增加,飞机的稳定性质甚至会发生变化,此时飞行状态将很难维持在原有的安全边界以内,提出了通过指导驾驶员操纵指令变化使飞行状态到达新的安全边界。研究结果对于飞行安全操纵及边界保护都具有一定的指导意义。

关键词: 结冰飞机, 分岔分析, 微分流形理论, 稳定域, 飞行操纵

Abstract: Icing will destroy the dynamic performance of the aircraft and cause the safety envelope shrink, which seriously affects the flight safety. It is of great significance to study the changes of nonlinear stability region of the icing aircraft for reducing flight accidents. In this paper, the NASA's GTM is taken as the object aircraft. First, the dynamic model of longitudinal channel under icing condition is established based on polynomial fitting of the aerodynamic parameters and the icing factor model. Then,the change of flight state under different icing conditions and control commands is studied by bifurcation analysis method which used to guide flight manipulation. Considering the limitation of bifurcation analysis method, the nonlinear stability region of flight system is determined by differential manifold theory. And the nonlinear stability region is regarded as flight safety boundary. Finally, considering the icing condition,the bifurcation analysis method and differential manifold theory are combined to guide manipulation. Furthermore, the time domain validation of the manipulation is carried out. The results show that icing will shrink the safety boundary, and a slight disturbance may contribute to flight state outside the safety boundary. Moreover, with the increasing degree of icing, the stability of the aircraft will even change and the flight state will be difficult to maintain within the original safety boundary. At this moment, the flight state can be brought to the new safety boundary by changing the pilot's manipulation instruction. The research results are helpful for flight safety manipulation and boundary protection.

Key words: icing aircraft, bifurcation analysis, differential manifold theory, stability region, flight manipulation

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