低速风洞带动力模型自由飞试验

doi:10.7527/S1000-6893.2017.121214

Abstract

Abstract:

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

CLC Number:

V211.7

CEN Fei, NIE Bowen, LIU Zhitao, SUN Haisheng, LI Qing. Low speed wind tunnel free-flight test of powered sub-scale aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(10): 121214-121214.

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Low speed wind tunnel free-flight test of powered sub-scale aircraft

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