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Nonlinear response analysis of variable speed rotor system under maneuvering flight

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Abstract

Maneuverability is one of the important tactical and technical indexes of fighter aircraft. In this paper, the finite element method is used to establish a dynamic model of the rotor system that can consider arbitrary maneuvering flight form and rotor speed variation during the flight, and the vibration characteristic of the dynamic model is investigated in detail. In addition, the nonlinear forces caused by bearings and oil film are also considered. The Newmark-β method combined with Newton-Raphson method is adopted to solve the dynamic equations. The influences of speed variation, rolling, pitching, and yawing maneuver loads on the vibration responses of the rotor system are also evaluated.

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Abbreviations

T t :

Translational kinetic energy

T r :

Rotational kinetic energy

v B :

Velocity of the aircraft

\({{\bf{\bar \omega }}_B}\) :

Angular velocity of the aircraft

ω :

Rotor speed

φ 0 :

Initial angle of disk unbalance

Ẋ B, Ẏ B, Ż B :

Aircraft velocity along coordinate axis

ω x, ω y, ω z :

Angular velocity around coordinate axis.

J d :

Diameter moment of inertia of the disk

J p :

Polar moment of inertia of the disk

C B :

Additional damping matrix

K B :

Additional stiffness matrix

F B :

Maneuvering load

m sl, m sr :

Concentrated mass SFD

k blx, k bly :

Stiffness of the elastic support on the left

k brx, k bry :

Stiffness of the elastic support on the right

M :

Mass matrix of the rotor system

C :

Damping matrix of the rotor system

G :

Gyroscopic matrix of the rotor system

K :

Stiffness matrix of the rotor system

F e :

Unbalanced force

F b :

Nonlinear bearing force

F s :

Nonlinear oil film force

ω 1, ω 2 :

First and second natural angular frequency

ξ 1, ξ 2 :

First and second modal damping ratios

Δt :

Time of deceleration

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Acknowledgments

The research work is supported by the National Science and Technology Major Project (2017-I-0006-0007), the National Natural Science Foundation of China (52005100), the National Science Foundation for Distinguished Young Scholars (52125209), the Key R&D Plan of Jiangsu Province (BE2022158), the Jiangsu Association for Science and Technology Young Talents Lifting Project (TJ-2022-043), the Zhishan Youth Scholar Program of SEU (2242021R41169) and the Fundamental Research Funds for the Central Universities.

Author information

Authors and Affiliations

  1. School of Mechanical Engineering, Southeast University, Nanjing, 211189, China

    Xueyang Miao, Junzeng He, Dahai Zhang & Qingguo Fei

  2. Jiangsu Engineering Research Center of Aerospace Machinery, Nanjing, 211189, China

    Xueyang Miao, Junzeng He, Dahai Zhang, Dong Jiang & Qingguo Fei

  3. School of Mechanical and Electronic Engineering, Nanjing Forestry University, Nanjing, 210037, China

    Dong Jiang

  4. China Aviation Power Plant Research Institute, Zhuzhou, 412002, China

    Jian Li & Xing Ai

Authors
  1. Xueyang Miao
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  2. Junzeng He
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  3. Dahai Zhang
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  4. Dong Jiang
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  5. Jian Li
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  6. Xing Ai
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  7. Qingguo Fei
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Corresponding authors

Correspondence to Dahai Zhang or Qingguo Fei.

Additional information

Zhang Dahai is an Associate Professor of the School of Mechanical Engineering, Southeast University, Nanjing, China. He received his Ph.D. in School of Mechanical Engineering from Southeast University. His research interests include aeroengine rotor system dynamics, and mechanical behavior of lightweight porous materials and their composite structures.

Fei Qingguo is a Full Professor of the School of Mechanical Engineering, Southeast University, Nanjing, China. He received his Ph.D. in Nanjing University of Aeronautics and Astronautics. His research interests include Aerospace mechanical dynamics.

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Miao, X., He, J., Zhang, D. et al. Nonlinear response analysis of variable speed rotor system under maneuvering flight. J Mech Sci Technol 37, 4957–4971 (2023). https://doi.org/10.1007/s12206-023-0903-x

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  • DOI: https://doi.org/10.1007/s12206-023-0903-x

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