航空学报 > 2013, Vol. 34 Issue (11): 2435-2442   doi: 10.7527/S1000-6893.2013.0161

小展弦比飞翼布局航向控制的组合舵面研究

张彬乾1, 马怡1, 褚胡冰1, 陈真利1, 陈迎春1,2   

  1. 1. 西北工业大学 航空学院, 陕西 西安 710072;
    2. 中国商用飞机有限责任公司 上海飞机设计研究所, 上海 201210
  • 收稿日期:2012-11-21 修回日期:2013-03-05 出版日期:2013-11-25 发布日期:2013-03-22
  • 通讯作者: 陈迎春,Tel.:021-54100171 E-mail:chenyingchun@comac.cc E-mail:chenyingchun@comac.cc
  • 作者简介:张彬乾 男,教授,博士生导师。主要研究方向:飞行器气动布局设计、流动控制。 Tel:029-88494846 E-mail:bqzhang@nwpu.edu.cn;马怡 女,硕士研究生。 主要研究方向:飞行器气动布局设计。 Tel:029-88494846 E-mail:mayinwpu@gmail.com;褚胡冰 男,博士研究生。主要研究方向:飞行器气动布局设计、流动控制。 Tel:029-88494846 E-mail:chuhubing@126.com;陈真利 男,博士,讲师。主要研究方向:飞行器气动布局设计、流动控制。 Tel:029-88494846 E-mail:zhenlichen@nwpu.edu.cn;陈迎春 男,博士,教授,常务副总师。主要研究方向:飞行器总体、气动设计。 Tel:021-54100171 E-mail:chenyingchun@comac.cc
  • 基金资助:

    国家级项目

Investigation on Combined Control Surfaces for the Yaw Control of Low Aspect Ratio Flying Wing Configuration

ZHANG Binqian1, MA Yi1, CHU Hubing1, CHEN Zhenli1, CHEN Yingchun1,2   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. Shanghai Aircraft Design and Research Institute, Commercial Aircraft Corporation of China Ltd., Shanghai 201210, China
  • Received:2012-11-21 Revised:2013-03-05 Online:2013-11-25 Published:2013-03-22
  • Supported by:

    National Level Project

摘要:

航向控制是飞翼布局设计急需解决的关键技术之一。采用数值模拟方法,研究了小展弦比飞翼布局嵌入式阻力舵(SSD)的航向操纵及其耦合特性,针对滚转力矩大等耦合气动问题,提出了一种由嵌入式阻力舵与升降副翼构成的航向操纵组合舵面。研究了组合舵面的航向操纵规律及其耦合特性,揭示了其流动机理。研究结果表明:组合舵面具有很强的航向操纵和解耦能力,通过阻力舵偏度与升降副翼偏度的优化匹配,可显著减小或消除耦合滚转,使升力与俯仰特性得到恢复,很好地解决了小展弦比飞翼布局航向操纵及其耦合问题,具有舵面少、效率高等特点,是无尾布局航向控制的有效手段,应用前景广阔。

关键词: 飞翼布局, 航向控制, 组合舵面, 嵌入式阻力舵, 数值模拟

Abstract:

Yaw control is one of the key issues in the design of a flying wing aircraft configuration. Based on numerical simulation, this paper studies the yaw control ability and coupling aerodynamic characteristics of spoiler-slot-deflector (SSD) used on a low aspect ratio flying wing configuration. To overcome the disadvantage of excessive coupling roll moment of the SSD, this paper proposes a yaw control surface by combining the SSD and elevon together. Then, it studies the rules of yaw control and the coupling characteristics of the combined control surface and reveals its physical mechanism. The research shows that the combined control surface has a strong ability for yaw control and decreases the coupling characteristics. By adjusting the deflection angles of the SSD and elevon, the coupling roll moment can be obviously decreased or eliminated, and the lift and the pitching moment can be recovered. The combined control surface can well solve the yaw control and coupling moment problems, and it has the advantage of fewer rudders concerned and high efficiency. Therefore, it is an efficient method for the yaw control of tailless aircraft with good prospect for application.

Key words: flying wing, yaw control, combined control surface, spoiler-slot-deflector, numerical simulation

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