北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (2): 333-341.doi: 10.13700/j.bh.1001-5965.2017.0109

• 论文 • 上一篇    下一篇

气动参数对闭环飞机短周期模态特性的影响

徐王强, 王立新   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2017-03-02 修回日期:2017-06-02 出版日期:2018-02-20 发布日期:2018-03-01
  • 通讯作者: 王立新,E-mail:wlx_c818@163.com E-mail:wlx_c818@163.com
  • 作者简介:徐王强,男,博士研究生。主要研究方向:飞机设计、飞行安全;王立新,男,教授,博士生导师。主要研究方向:飞机设计、飞行动力学与控制、飞行安全。

Influence of aerodynamic parameters on short-period mode characteristics of closed-loop aircraft

XU Wangqiang, WANG Lixin   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2017-03-02 Revised:2017-06-02 Online:2018-02-20 Published:2018-03-01

摘要: 现代高性能战斗机均采用放宽静稳定性的布局构型,需通过先进飞行控制的设计来保证其闭环飞机在全飞行包线内均具有优良的动态特性。受到舵面操纵特性的限制,飞行控制系统(FCS)的能力是有限的,即飞机本体的气动参数需满足一定的要求才能保证闭环系统的飞行品质。本文建立了研究本体气动参数对闭环飞机短周期模态特性影响规律的方法,采用等效参数准则,以基于模型参考动态逆控制律的某放宽静稳定飞机为算例,计算分析了不同本体气动参数取值大小对闭环飞机短周期模态特性的影响规律。结果表明,升降舵操纵效能是影响闭环飞机短周期模态特性的主要因素,本体气动参数需满足一定的适配关系才能保证闭环飞机具有优良的短周期飞行品质。研究方法和结果对于放宽静稳定性飞机的本体设计与飞行控制系统设计等都具有很好的参考价值。

关键词: 本体气动参数, 舵面效能, 短周期模态特性, 模型参考动态逆, 飞行品质

Abstract: Owing to the relaxed static stability technology applied to the modern high-performance fighter aircraft, the design of an advanced flight control system is required to confirm its closed-loop system for an excellent dynamic property within the flight envelope. The ability of flight control system (FCS) is limited as a result of the control effectiveness and deflection rate of the control surface. The designed aerodynamic parameters of aircraft must meet certain requirements to confirm good flying qualities in its closed-loop system. This paper presents a new method which describes the influence of various aerodynamic parameters on short-period mode characteristics of closed-loop aircraft. A relaxed static stability aircraft with model reference dynamic inversion control law is provided to investigate the influence rules of various aerodynamic parameters on short-period mode characteristics based on the equivalent parameter criterion. The results show that the elevator control effectiveness has a great influence on the short-period mode characteristics and the aerodynamic parameters need to match a certain match value set to keep excellent short-period mode flying qualities. The proposed method can provide reference for flight control system design with the optimized aerodynamic parameters for relaxed static stability aircraft.

Key words: aerodynamic parameters, control surface effectiveness, short-period mode characteristics, model reference dynamic inversion, flying qualities

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