北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (9): 2008-2016.doi: 10.13700/j.bh.1001-5965.2016.0142

• 论文 • 上一篇    

滚转机动载荷减缓风洞试验

秦航远, 吴志刚, 杨超, 戴玉婷, 马成骥   

  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:2016-02-27 出版日期:2016-09-20 发布日期:2016-05-23
  • 通讯作者: 吴志刚,Tel.:010-82333723,E-mail:wuzhigang@buaa.edu.cn E-mail:wuzhigang@buaa.edu.cn
  • 作者简介:秦航远,男,硕士研究生。主要研究方向:气动弹性力学。Tel.:010-82313376,E-mail:qinhangyuan@buaa.edu.cn;吴志刚,男,博士,副教授,硕士生导师。主要研究方向:气动弹性力学。Tel.:010-82333723,E-mail:wuzhigang@buaa.edu.cn
  • 基金资助:
    国家自然科学基金(11372023)

Wind tunnel test of rolling maneuver load alleviation

QIN Hangyuan, WU Zhigang, YANG Chao, DAI Yuting, MA Chengji   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2016-02-27 Online:2016-09-20 Published:2016-05-23

摘要: 机动载荷减缓能有效降低飞机结构重量并改善飞机的飞行性能,因此在飞机设计领域具有广阔的应用前景。针对滚转机动载荷减缓技术的实际应用,对多控制面联合偏转的机动载荷减缓控制方法进行了风洞试验验证。设计小展弦比正常式布局战斗机风洞试验模型、滚转及限位装置、试验模型测控系统、零度保持回路以及机动载荷减缓控制系统,采用两种不同控制面组合的多控制面联合偏转控制律开展试验并测试载荷减缓效果。结果表明,相比于基准控制,多控制面联合偏转的控制律能有效减缓飞机机动过程中的附加机动载荷。采用尾翼以及机翼后缘外侧(TEO)控制面联合偏转的控制律1的机翼弯矩和扭矩减缓率分别为30.1%和38.0%,尾翼弯矩和扭矩减缓率分别为 57.9%和12.5%;采用尾翼、TEO以及机翼后缘内侧(TEI)控制面联合偏转的控制律2的机翼弯矩和扭矩减缓率分别为33.0%和35.5%,尾翼弯矩和扭矩减缓率分别为 45.7%和54.8%。

关键词: 滚转机动, 载荷减缓, 多控制面偏转, 模型设计, 主动控制, 风洞试验

Abstract: It has been documented that maneuver load alleviation possesses a strong potency for reducing structure weight which would improve flight performance in the field of aircraft design. In view of this situation, a wind tunnel test was designed and conducted in this study to evaluate the control method of rolling maneuver load alleviation (RMLA) with multiple control surfaces. According to the demands for test, a series of models and procedures were designed, including the test aircraft model with a normal layout and a small aspect ratio, rolling and limiting device, measurement and control system based on test model, zero-degree keeping circuit, and RMLA control systems. The test was conducted using two control laws with different combinations of control surfaces to evaluate the effects on load alleviation. It was found that, compared with baseline control law, the additional maneuver load generated during the process of rolling maneuver was effectively alleviated using the method of simultaneously deflecting multiple control surfaces. The control law 1 with the simultaneous deflection of wing and trailing-edge outboard (TEO) control surface alleviated the bending and torsion moments of wing by 30.1% and 38.0%, respectively, and the bending and torsion moments of empennage by 57.9% and 12.5%, respectively. The control law 2 with the simultaneous deflection of wing, TEO, and trailing-edge inboard (TEI) control surfaces alleviated the bending and torsion moments of wing by 33.0% and 35.5%, respectively, and the bending and torsion moments of empennage by 45.7% and 54.8%, respectively.

Key words: rolling maneuver, load alleviation, simultaneously deflecting multiple control surfaces, model design, active control, wind tunnel test

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