论文部分内容阅读
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。
In order to meet the demand of researching unsteady aerodynamics in the process of stalling maneuvering at high angle of attack, China Aerospace Institute of Aeronautics and Astronautics developed a set of electro-hydraulic servomotor and motor coupled drive The two degrees of freedom large oscillation test technology. The basic composition and experimental principle of the system are briefly introduced. The typical results of the two-DOF large-amplitude oscillation test for the dynamic standard model of the FL-8 wind tunnel are given. The results show that the system has stable performance, reliable test data and better repeatability High, which can be effectively applied to aerodynamic characteristics research of two degrees-of-freedom coupled aerocraft.