北京航空航天大学学报 ›› 2014, Vol. 40 ›› Issue (8): 1127-1133.doi: 10.13700/j.bh.1001-5965.2013.0462

• 论文 • 上一篇    下一篇

新型折叠翼机构设计

包晓翔1, 张云飞2, 杨晓树2   

  1. 1. 中国航天空气动力技术研究院 第十一总体设计部, 北京 100074;
    2. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2013-08-12 出版日期:2014-08-20 发布日期:2014-08-27
  • 作者简介:包晓翔(1990-),男,河南信阳人,助理工程师,baoxiaoxiang@foxmail.com.

Design of a novel folding wing mechanism

Bao Xiaoxiang1, Zhang Yunfei2, Yang Xiaoshu2   

  1. 1. 11th General Design Department, China Academy of Aerospace Aerodynamics, Beijing 100074, China;
    2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2013-08-12 Online:2014-08-20 Published:2014-08-27

摘要: 为了进一步缩减折叠翼飞行器(如舰载机、无人机、飞行汽车等)的展向尺寸来节省储存、运输空间,设计一种新型的折叠翼机构方案.它由内翼、中翼和外翼3部分组成,采用连杆机构作为翼面折叠机构,能进行两次折叠.简化运动模型,建立运动微分方程,分析折叠翼机构在地面(无气动载荷)情况下的运动特性;利用多刚体动力学软件进行动力学仿真分析;通过在内翼和中翼间的铰链添加扭力弹簧,改善了折叠翼的驱动性能;开展折叠翼地面折叠/展开实验,实验结果与计算机仿真基本吻合.翼面折叠/展开运动平稳,大幅缩减了折叠翼飞行器地面展向占用空间.

Abstract: In order to reduce the spanwise size of some aircraft (such as shipboard aircraft, unmanned aerial vehicle, flying car and so on) for saving the storage and transportation space, a novel folding wing mechanism was designed. It consists of three components (an inboard wing, a middle wing and an outboard wing) and can fold twice. The folding mechanism was designed with link mechanism. Then, the kinematics differential equations were established with the simplified kinematics model (without aerodynamic load on ground) to analyze its motion characteristics. The simulation software of multi-body dynamics was used to analyze its dynamics. Torsion spring was used around the hinge between inboard wing and middle wing to improve performance of the drive system. Finally, experiment was done. The result corresponds with the computer simulation very well. The novel folding wing mechanism can reduce the spanwise size of the aircraft remarkably, and the fold/extension motion is smooth and steady.

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