低速风洞带动力模型自由飞试验

发布时间：2018-03-24 12:57

本文选题：风洞　切入点：飞行试验　出处：《航空学报》2017年10期

【摘要】：为在风洞中模拟飞行器六自由度飞行的物理过程,获取飞行器流动/运动/控制耦合特性,对低速风洞带动力模型自由飞试验技术进行了研究。基于相似准则,在大型低速风洞建立了试验系统,利用纵向静不稳定的动力学相似缩比模型飞机,经过飞行控制律闭环控制增稳后,开展稳态飞行、施加标准激励验证飞行、控制律参数调整验证飞行、大迎角飞行等自由飞试验,并将试验结果与原型机飞行仿真结果进行了对比研究。结果表明,基于相似准则建立的低速风洞带动力模型自由飞试验系统,能够有效模拟飞机闭环控制飞行过程,试验结果准确反映原型机的稳定与控制特性。低速风洞带动力模型自由飞试验验证了原型机的飞行控制律,预测了其大迎角失速/偏离特性,形成了飞行器气动/飞行力学/控制一体化风洞试验研究能力。
[Abstract]:In order to simulate the physical process of aircraft flight with six degrees of freedom in wind tunnel and obtain the coupled flow / motion / control characteristics of the vehicle, the free-flight test technique of the low-speed wind tunnel dynamic model is studied. A test system was set up in a large low-speed wind tunnel. By using the longitudinal static instability model aircraft with similar dynamic ratio, the steady flight was carried out after the closed-loop control of the flight control law was increased, and the standard excitation was applied to verify the flight. The control law parameters are adjusted to verify the flight and fly at a high angle of attack. The experimental results are compared with the flight simulation results of the prototype aircraft. The results show that, The free-flight test system of low-speed wind tunnel model based on similarity criterion can effectively simulate the closed-loop control flight process of aircraft. The test results accurately reflect the stability and control characteristics of the prototype, and the free-flight test of the strip power model in low speed wind tunnel verifies the flight control law of the prototype, and predicts the stall / deviation characteristics of the prototype at high angle of attack. The aerodynamics / flight mechanics / control integrated wind tunnel test and research capability is formed.
【作者单位】：清华大学自动化系;中国空气动力研究与发展中心;
【分类号】：V211.74

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