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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (12): 222027-222027.doi: 10.7527/S1000-6893.2018.22027

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles     Next Articles

Optimal design for landing gear stiffness and damping based on helicopter ground resonance requirements

WU Jing1, HU Guocai1, LIU Quan2, LIU Xiangyi1   

  1. 1. Aeronautical Foundation College, Naval Aviation University, Yantai 264001, China;
    2. Troops 91206, Naval Aviation University, Qingdao 266108, China
  • Received:2018-01-18 Revised:2018-04-19 Online:2018-12-15 Published:2018-09-17

Abstract: To meet the requirement of helicopter ground resonance stability, an optimal design method for landing gear stiffness and damping is proposed. First, a modal damping ratio function in the instable area for the fuselage without damping was constructed. The requirements of fuselage natural frequency and damping for meeting ground resonance stability were given by combining the calculation method of the instable area critical rotate speed with the calculation method of damping ratio at the resonance rotate speed of the fuselage mode. Then, based on the freedom motion model for the fuselage on the landing gear, the relation between landing gear stiffness and damping with fuselage mode frequency and damping was established, and the requirements of landing gear stiffness and damping for meeting ground resonance stability were given. Finally, based on the stability requirements, an optimal design method of landing gear stiffness and damping is proposed to reduce the required damping of landing gear and increase the minimum damping ratio of fuselage mode within the range determined by the buffering property requirements. This method was validated by optimizing the landing gear stiffness and damping of a type of helicopter at 4 states with different weights and gravity centers.

Key words: helicopter, ground resonance, landing gear, stiffness, damping, optimal design

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