Volume 29 Issue 2
Feb.  2014
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WANG Qiang, CHEN Ming, XU Guan-feng. Control strategy for compound coaxial helicopter under conversion mode[J]. Journal of Aerospace Power, 2014, 29(2): 458-466. doi: 10.13224/j.cnki.jasp.2014.02.027
Citation: WANG Qiang, CHEN Ming, XU Guan-feng. Control strategy for compound coaxial helicopter under conversion mode[J]. Journal of Aerospace Power, 2014, 29(2): 458-466. doi: 10.13224/j.cnki.jasp.2014.02.027
shu

Control strategy for compound coaxial helicopter under conversion mode

doi: 10.13224/j.cnki.jasp.2014.02.027
  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2.

    Army Aviation Research Institute, the Headquarters of General Staff, the Chinese People's Liberation Army, Beijing 101121, China

  • Received Date: 2012-12-27
  • Publish Date: 2014-02-28
    Abstract
  • According to the characteristics of the compound coaxial helicopter,the general aerodynamic forces and moments of rotors,wing,fuselage,stabilator,vertical stabilizers (containing the rudder) and propeller were modeled and a trimming equation set was established accordingly.In view of the controlling redundancy problem,a control strategy was studied for the compound coaxial helicopter under conversion mode,using the linear transition method and minimal power optimization transition method.A sample compound coaxial helicopter was taken as an example to demonstrate the effectiveness of the method.Then the trimming values,the attitude angles and the power of these two methods were compared.The result shows that both the two methods can solve the controlling redundancy problem,while the trimming values and the attitude angles are reasonable and the linear transition method is better in the smooth change of the control values,the difficulty level of the controlling system and the flight quality.

     

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