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Volume 41 Issue 5
May  2015
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Journal of Beijing University of Aeronautics and Astronautics  > 2015  >  41(5): 835-840.
XU Ziyao, WANG Qi. Method for modeling and simulation of aircraft taxiing with unilateral and non-holonomic constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(5): 835-840. doi: 10.13700/j.bh.1001-5965.2014.0342(in Chinese)
Citation: XU Ziyao, WANG Qi. Method for modeling and simulation of aircraft taxiing with unilateral and non-holonomic constraints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2015, 41(5): 835-840. doi: 10.13700/j.bh.1001-5965.2014.0342(in Chinese)
shu

Method for modeling and simulation of aircraft taxiing with unilateral and non-holonomic constraints

doi: 10.13700/j.bh.1001-5965.2014.0342

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

  • Received Date: 11 Jun 2014
  • Rev Recd Date: 25 Jun 2014
  • Publish Date: 20 May 2015
    Abstract
  • The motion of the aircraft taxiing along the ground was related to wind load and asymmetric braking torque. The method for modeling and simulation of the aircraft was presented on the basis of the dynamics of the non-smooth multibody system with non-holonomic constraints in order to analyze the dynamic behavior of the aircraft taxiing along the ground. The aircraft was treated as the multibody system which consisted of a rigid fuselage, two wheels of main landing gears and a wheel of nose landing gear. Two wheels of main landing gears rolled on the ground without slip. The lateral slip of the wheel on the nose landing gear was taken into account when the aircraft taxied along the ground. The dynamic equations of the system were obtained by Routh's equations and the constraint-stabilized method to reduce constraint drift. The frictional model between the wheels and the ground was the model of Coulomb friction which was described by the set value of function to determine whether the wheel of the nose landing gear slipped in lateral direction or not. Finally, numerical examples were presented to analyze the dynamic behavior of the aircraft undertook the wind load and the asymmetric braking torque.

     

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