带动力模型水平风洞自由飞试验

Free-flight test in horizontal wind tunnel with powered aircraft

为了在设计初期开展气动/飞行/控制一体化研究,缩短研制周期,降低研发成本,在FL-10风洞开口试验段建立了水平风洞自由飞试验系统。该系统根据尺寸、质量及转动惯量相似准则设计缩比验证机模型,建立飞行控制系统,在此基础上对系统建模仿真,设计闭环增稳控制律,实现配平迎角稳定飞行。试验结果显示:根据相似准则设计的飞行控制律结构及参数,仿真配平迎角为5°,配平升降舵舵偏为-4.5°,风洞试验迎角控制在(5±0.2)°范围内,由于供电、信号线缆会给试验模型一个正向俯仰力矩,升降舵舵偏控制在-3.2°左右,略小于仿真配平升降舵舵偏。

In order to carry out aerodynamic/flight/control integration research at the early stage of design,shorten the development cycle and reduce the development cost,a model free-flight test system was established in FL-10 open wind tunnel.The system was used to design the scale verification machine model according to the similarity criteria of size,mass and moment of inertia,invent the flight control system,on this basis,the system was modeled and simulated,and the closed-loop stability increasing control law was designed to realize the stable flight at the trim angle of attack.The test results showed that the structure and parameters of the flight control law were designed according to the similarity criterion,the simulated trim angle of attack was 5°,the trim elevator deviation was−4.5°,and the wind tunnel test angle of attack was controlled within(5±0.2)°.Because the power supply and signal cables gave the test model a positive pitch moment,the elevator deviation was controlled at about−3.2°,which was slightly less than the simulated trim elevator deviation.