| Citation: | YAO Junkai, HE Haibo, ZHOU Danjie, et al. Tests of flying wing aircraft roll control using plasma actuator[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(4): 701-708. doi: 10.13700/j.bh.1001-5965.2016.0309(in Chinese)
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Flying wing aircraft usually uses multiple aerodynamic control surfaces for flight control. The aerodynamic control surface has a complex structure and control efficiency decreases dramatically at large angles of attack due to flow separation. The plasma actuator is usually used in flow control due to the advantages of simple structure, light-weight design and fast time response. In this paper, tests were done using the plasma actuator to produce asymmetrical aerodynamic forces for flying wing aircraft roll control by suppressing the flow separation on unilateral wing. The optimal dispose position and discharge parameter of plasma actuator were obtained and aileron roll control effect was also investigated and compared with plasma actuator. The results indicate that the plasma actuator arranged at the leading edge of inner and middle wing can get the best roll control effect. The modulation frequency of plasma actuator has significant impact on aircraft roll control, while excitation voltage's impact is small. Compared to the aileron, the plasma actuator achieves better roll control effect at large angles of attack.
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