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<p>Aircraft steering instability during the taxiing process sometimes occurs resulting from the unstable bifurcation phenomena of the nonlinear steering dynamic system, which may lead to severe accidents. In this study, the control parameter design of an aircraft nose wheel steering control system based on the control continuation method is proposed to reduce the number of unstable bifurcation points and enlarge the system stable region area in a certain parameter domain. Thus, the aircraft turning performance can be improved greatly. First, a nonlinear aircraft rollout dynamic model is constructed, and the aircraft ground steering bifurcation characteristics are obtained under the open-loop steering control system. Then, the bifurcation performances under three closed-loop nose wheel steering controllers based on the feedback control method are compared, and the control parameter of the quadratic nonlinear controller with a better bifurcation control effect is selected as a second bifurcation parameter to analyze the directional system stability via two-parameter bifurcation analysis. Further, the influence of a crosswind on the aircraft ground steering bifurcation performance is studied for various control parameter values. Then, the control effects of a traditional proportional-integral-derivative (PID) nose wheel steering control law and the designed feedback controller are compared and analyzed. Finally, a semi-physical experiment of the aircraft nose wheel steering system is carried out, and different control parameter values are selected for test verification, which can further verify the control effect of the designed nonlinear feedback controller. The results indicate that the feedback control method is unable to vary the system bifurcation types, but appropriate control parameter design can effectively shrink the system instability region and even eliminate the unstable Hopf bifurcation points under some specific working conditions, improving the aircraft ground turning stability remarkably from the perspective of the global parameter region.</p>

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Improving aircraft nose wheel steering stability based on control continuation method

  • 期刊论文

  • 发表日期：

    2025年2月17日

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  • Qiaozhi Yin,
  • Dexu Kong,
  • Jiawei Wang,
  • Hong Nie,
  • Xiaohui Wei

摘要

Aircraft steering instability during the taxiing process sometimes occurs resulting from the unstable bifurcation phenomena of the nonlinear steering dynamic system, which may lead to severe accidents. In this study, the control parameter design of an aircraft nose wheel steering control system based on the control continuation method is proposed to reduce the number of unstable bifurcation points and enlarge the system stable region area in a certain parameter domain. Thus, the aircraft turning performance can be improved greatly. First, a nonlinear aircraft rollout dynamic model is constructed, and the aircraft ground steering bifurcation characteristics are obtained under the open-loop steering control system. Then, the bifurcation performances under three closed-loop nose wheel steering controllers based on the feedback control method are compared, and the control parameter of the quadratic nonlinear controller with a better bifurcation control effect is selected as a second bifurcation parameter to analyze the directional system stability via two-parameter bifurcation analysis. Further, the influence of a crosswind on the aircraft ground steering bifurcation performance is studied for various control parameter values. Then, the control effects of a traditional proportional-integral-derivative (PID) nose wheel steering control law and the designed feedback controller are compared and analyzed. Finally, a semi-physical experiment of the aircraft nose wheel steering system is carried out, and different control parameter values are selected for test verification, which can further verify the control effect of the designed nonlinear feedback controller. The results indicate that the feedback control method is unable to vary the system bifurcation types, but appropriate control parameter design can effectively shrink the system instability region and even eliminate the unstable Hopf bifurcation points under some specific working conditions, improving the aircraft ground turning stability remarkably from the perspective of the global parameter region.