航空学报 > 2016, Vol. 37 Issue (8): 2426-2435   doi: 10.7527/S1000-6893.2016.0155

一种提高风洞动态试验数据质量的模型姿态控制和测量技术

刘志涛1,2, 孙海生2   

  1. 1. 西北工业大学 航空学院, 西安 710072;
    2. 中国空气动力研究与发展中心, 绵阳 621000
  • 收稿日期:2016-02-17 修回日期:2016-05-23 出版日期:2016-08-15 发布日期:2016-06-07
  • 通讯作者: 刘志涛,Tel.:0816-2461906。E-mail:liuzhitao@cardc.cn E-mail:liuzhitao@cardc.cn
  • 作者简介:刘志涛,男,硕士,副研究员。主要研究方向:大攻角空气动力学。Tel.:0816-2461906。E-mail:liuzhitao@cardc.cn;孙海生,男,博士,研究员,博士生导师。主要研究方向:非定常空气动力学。Tel.:0816-2461001。E-mail:sunhaisheng@cardc.cn

A model attitude control and measurement technique for improving quality of wind tunnel dynamic test data

LIU Zhitao1,2, SUN Haisheng2   

  1. 1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
    2. China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-02-17 Revised:2016-05-23 Online:2016-08-15 Published:2016-06-07

摘要:

低速风洞动态试验装置通常采用“电机+减速器+偏心机构+线性传动机构”的方式,存在传递环节多、机械间隙大等问题,给模型运动的精确控制和模型姿态的精确测量带来较大困难。为满足大型客机等大飞机对低速风洞动态试验的要求,基于现有的静态试验通用支撑平台,采用“电子凸轮”技术,建立了一套迎角/侧滑角解耦、可进行飞机小振幅动导数和大振幅非定常气动特性研究的动态试验装置。利用该动态试验装置进行了某飞机大尺度动态试验模型动导数试验和大振幅振荡试验,获得了试验数据的重复性,并研究了动态试验数据和静态试验数据之间的相关性。试验结果表明:利用该装置获得的某飞机动态试验数据重复性较好、规律合理,能满足大型飞机动态试验要求。

关键词: 大型飞机, 动导数, 非定常气动力, 风洞试验, 支撑装置

Abstract:

Motors, reducers, eccentric mechanisms and linear linkage mechanisms combination is commonly adopted by dynamic test equipment in a low speed wind tunnel. The derived problems such as too many linkages and too large mechanical clearance will lead to difficulties in precise control of model motion and model attitude measurement accuracy. A dynamic test equipment employing programmed motor technique is developed to meet the requirements of large transport airplanes for low speed wind tunnel dynamic tests based on the available generic support platform for static tests which can be used for small amplitude dynamic derivatives and large amplitude unsteady aerodynamic characteristics study on a aircraft. The dynamic derivative and large amplitude oscillation tests on some large scaled aircraft model are carried out to acquire the data repeatability and investigate the correlation between dynamic data and static data. Test results indicate that the good repeatability and reasonable change law abstracted from the aircraft dynamic test data can fulfill the demands of large aircraft dynamic tests.

Key words: large aircraft, dynamic derivatives, unsteady aerodynamics, wind tunnel test, support rig

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