Volume 36 Issue 11
Nov.  2021
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Article Navigation >  Journal of Aerospace Power  > 2021  >  36(11): 2278-2291
ZHU Jiachen, SHI Zhiwei, GENG Xi, FU Junquan, SUN Quanbing, CHEN Yongliang. Scheme optimization of yaw control of flying-wing aircraft based on jet flow control[J]. Journal of Aerospace Power, 2021, 36(11): 2278-2291. doi: 10.13224/j.cnki.jasp.20200466
Citation: ZHU Jiachen, SHI Zhiwei, GENG Xi, FU Junquan, SUN Quanbing, CHEN Yongliang. Scheme optimization of yaw control of flying-wing aircraft based on jet flow control[J]. Journal of Aerospace Power, 2021, 36(11): 2278-2291. doi: 10.13224/j.cnki.jasp.20200466
shu

Scheme optimization of yaw control of flying-wing aircraft based on jet flow control

doi: 10.13224/j.cnki.jasp.20200466
  • 1.

    Department of Aerodynamics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • 2.

    Key Laboratory of Unsteady Aerodynamics and Flow Control，Ministry of Industry and Information Technology，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • Received Date: 2020-11-02
  • Publish Date: 2021-11-28
    Abstract
  • There are difficulties in yaw control of a flying-wing aircraft due to the cancellation of vertical tail.A variety of control schemes were designed based on the jet flow control technology to assist in and optimize the yaw control.The jet control actuator was designed and manufactured.Through the wind tunnel force measurement experiment and two-dimensional numerical simulation，the control effect and mechanism of each scheme were analyzed，and the optimal control scheme was selected.The results showed that under the same jet momentum coefficient，it was easier to obtain yaw moment by producing resistance than by applying thrust.After turning on the excitation，the more inverse components the jet contains in relation to the incoming flow，the more obvious the interaction with the incoming flow；the larger the separation zone formed，the better the control effect.The forward symmetric blowing was proved to be the optimal control scheme，which can produce about rudder effect equivalent to a split drag rudder deflection of 70°，and the coupling degree of moment was small.

     

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