| Citation: | YANG Junbin, WU Zhigang, DAI Yuting, et al. Wind tunnel test of gust alleviation active control for flying wing configuration aircraft[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(1): 184-192. doi: 10.13700/j.bh.1001-5965.2016.0079(in Chinese)
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Flying wing configuration aircraft is advantageous on the characteristics of stealth and aerodynamics, but due to lack of conventional elevator and rudder, gust alleviation control method for the aircraft with conventional configuration is not suitable anymore. For the flying wing configuration aircraft with large aspect ratio, a wind tunnel model, support system with two degrees of freedom of plunging and pitching, and gust generator which is capable of generating continuous sine gust are designed. Three control schemes that can simultaneously reduce wing tip acceleration and wing root bending moment are designed using classical control law theory. Wind tunnel test of gust alleviation active control is conducted and the open and closed loop test data are analyzed. Test data show that the wing tip acceleration and the wing root bending moment due to gust of flying wing aircraft have a large peak at the frequency of pitch mode, while the peak at the frequency of first bending mode is relatively small; for different combinations of control surface, the effects of gust alleviation are different; for flying wing configuration aircraft, selecting the appropriate combination of control surfaces can effectively reduce the gust load and gust response.
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