Volume 36 Issue 10
Oct.  2021
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ZHOU Pan, CHEN Renliang, YU Zhiming. Investigation of control strategy for quad-tilt-rotor aircraft in helicopter mode[J]. Journal of Aerospace Power, 2021, 36(10): 2036-2051. doi: 10.13224/j.cnki.jasp.20200384
Citation: ZHOU Pan, CHEN Renliang, YU Zhiming. Investigation of control strategy for quad-tilt-rotor aircraft in helicopter mode[J]. Journal of Aerospace Power, 2021, 36(10): 2036-2051. doi: 10.13224/j.cnki.jasp.20200384
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Investigation of control strategy for quad-tilt-rotor aircraft in helicopter mode

doi: 10.13224/j.cnki.jasp.20200384

  • National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • Received Date: 2020-09-13
  • Publish Date: 2021-10-28
    Abstract
  • Quad-tilt-rotor aircraft is a vehicle of particular configuration.For its strategy of the helicopter mode，a nonlinear flight dynamic model was established for a prototype，and some relevant test were carried out.Four control strategies were proposed，and a relatively reasonable control strategy was determined by comparing the trim values，control efficiency and cross coupling.The control redundant problem of quad-tilt-rotor aircraft in helicopter mode was solved under the strategy.At last，the influence of the center of gravity location on trim characteristics and control efficiency was analyzed.The results showed that the main control efficiency of longitudinal and lateral channel obtained by collective differential was much greater than by linkage of cyclic pitch.The main control efficiency of yaw channel obtained by cyclic pitch differential was greater than by collective differential.The cross coupling of yaw channel obtained by lateral cyclic pitch differential was less than longitudinal cyclic pitch differential.The values of trimming and cross coupling were the minimum at the normal position of center of gravity.

     

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