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
发布时间：2018-10-18 19:14
【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。
[Abstract]:The low speed wind tunnel dynamic test device usually adopts the "linear drive mechanism of the eccentric mechanism of the motor reducer", which has many transfer links and large mechanical clearance, etc. It is difficult to control the motion of the model and to measure the attitude of the model accurately. In order to meet the requirement of low speed wind tunnel dynamic test for large airliner and other large aircraft, a set of decoupling of angle of attack / side slip angle is established based on the existing universal support platform of static test and "electronic cam" technology. A dynamic test device that can be used to study the unsteady aerodynamic characteristics of aircraft with small amplitude dynamic derivative and large amplitude. The dynamic derivative test and large amplitude oscillation test of a large scale dynamic test model of an aircraft were carried out by using this dynamic test device. The repeatability of the test data was obtained, and the correlation between the dynamic test data and the static test data was studied. The experimental results show that the dynamic test data obtained by this device have good repeatability and reasonable regularity, and can meet the requirements of large aircraft dynamic test.
【作者单位】： 西北工业大学航空学院;中国空气动力研究与发展中心;
【分类号】：V211.7
本文编号：2280113
[Abstract]:The low speed wind tunnel dynamic test device usually adopts the "linear drive mechanism of the eccentric mechanism of the motor reducer", which has many transfer links and large mechanical clearance, etc. It is difficult to control the motion of the model and to measure the attitude of the model accurately. In order to meet the requirement of low speed wind tunnel dynamic test for large airliner and other large aircraft, a set of decoupling of angle of attack / side slip angle is established based on the existing universal support platform of static test and "electronic cam" technology. A dynamic test device that can be used to study the unsteady aerodynamic characteristics of aircraft with small amplitude dynamic derivative and large amplitude. The dynamic derivative test and large amplitude oscillation test of a large scale dynamic test model of an aircraft were carried out by using this dynamic test device. The repeatability of the test data was obtained, and the correlation between the dynamic test data and the static test data was studied. The experimental results show that the dynamic test data obtained by this device have good repeatability and reasonable regularity, and can meet the requirements of large aircraft dynamic test.
【作者单位】： 西北工业大学航空学院;中国空气动力研究与发展中心;
【分类号】：V211.7
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