收稿日期: 2017-03-03
修回日期: 2017-04-15
网络出版日期: 2017-04-14
Low speed wind tunnel free-flight test of powered sub-scale aircraft
Received date: 2017-03-03
Revised date: 2017-04-15
Online published: 2017-04-14
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。
岑飞 , 聂博文 , 刘志涛 , 孙海生 , 李清 . 低速风洞带动力模型自由飞试验[J]. 航空学报, 2017 , 38(10) : 121214 -121214 . DOI: 10.7527/S1000-6893.2017.121214
To simulate the physical progress of the aircraft flying at six-degree-of-freedom in the wind tunnel and achieve the aerodynamics,kinematics and flight-control coupling characteristics of the aircraft,the low speed wind tunnel free-flight test technique for powered sub-scale aircraft is studied.Based on the similarity criterion,a test platform is established in a large-scale low speed wind tunnel.A dynamic sub-scale model which is unstable in longitudinal static stability is augmented according to flight control laws,and flies in the wind tunnel test section with 1g trim condition,doublet control inputs,adjusted control feed-back gains and high angle of attack.The correlation between the free-flight test results of the sub-scale model and the simulation results of the full-scale prototype aircraft is analyzed.The results show that the wind tunnel free-flight test platform developed based on the similarity criterion can effectively simulate the actual flight process of the aircraft augmented with flight control laws,and the stability and control characteristics of the sub-scale model representing the prototype aircraft,and is thus especially useful for verification of flight control laws and prediction of stall/departure characteristics.The established test platform has the capability of conducting integrated research on the coupling between aerodynamics,flight dynamics and flight control characteristics.
Key words： wind tunnel; flight test; flying quality; dynamic stability; flight control
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