低速风洞双自由度大幅振荡试验技术
发布时间：2019-03-17 20:31
【摘要】：为满足国内战斗机型号研制对大迎角过失速机动过程中非定常气动力问题研究的需求,中国航空工业空气动力研究院在FL-8风洞开发了一套基于电液伺服马达和电机耦合驱动的双自由度大幅振荡试验技术。简单介绍了该系统的基本组成和试验原理,给出了FL-8风洞动态标准模型双自由度大幅振荡试验的典型结果,分析表明:该系统运行性能稳定,试验数据可靠,重复性精度较高,可以有效应用于飞行器双自由度耦合运动气动特性研究。
[Abstract]:In order to meet the requirements of domestic fighter models for the study of unsteady aerodynamic problems in the process of high angle of attack stall maneuver, A set of two-degree-of-freedom large-amplitude oscillation test technology based on coupling drive of electro-hydraulic servo motor and motor has been developed in FL-8 wind tunnel by China Aeronautical Industry aerodynamics Research Institute. The basic composition and test principle of the system are briefly introduced. The typical results of the two-degree-of-freedom large-amplitude oscillation test of the dynamic standard model of FL-8 wind tunnel are given. The analysis shows that the operation performance of the system is stable and the test data are reliable. Because of its high repeatability, it can be used to study the aerodynamic characteristics of two-degree-of-freedom coupling motion of aircraft.
【作者单位】： 中国航空工业空气动力研究院;中国空气动力研究与发展中心;
【基金】：航空科学基金(20143203002)~~
【分类号】：V211.74
，
本文编号：2442673
[Abstract]:In order to meet the requirements of domestic fighter models for the study of unsteady aerodynamic problems in the process of high angle of attack stall maneuver, A set of two-degree-of-freedom large-amplitude oscillation test technology based on coupling drive of electro-hydraulic servo motor and motor has been developed in FL-8 wind tunnel by China Aeronautical Industry aerodynamics Research Institute. The basic composition and test principle of the system are briefly introduced. The typical results of the two-degree-of-freedom large-amplitude oscillation test of the dynamic standard model of FL-8 wind tunnel are given. The analysis shows that the operation performance of the system is stable and the test data are reliable. Because of its high repeatability, it can be used to study the aerodynamic characteristics of two-degree-of-freedom coupling motion of aircraft.
【作者单位】： 中国航空工业空气动力研究院;中国空气动力研究与发展中心;
【基金】：航空科学基金(20143203002)~~
【分类号】：V211.74
，
本文编号：2442673
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