Nonlinear vibration phenomenon of an aircraft rub-impact rotor system due to hovering flight

Hou, Lei; Chen, Yushu; Cao, Qingjie

doi:10.1016/j.cnsns.2013.06.023

Cited by 66 publications

(29 citation statements)

References 28 publications

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“…The occurrence of sub-harmonic resonance was also shown to be possible in a hovering rotor system due to the effect of the maneuver load [9]. In this resonance situation, the rub-impact between the rotor and the stator may also be induced [10]. In [11] and [12], the maneuvering flight model with a constant angular speed or a constant acceleration in a vertical plane was proposed to study the nonlinear dynamics of an aircraft rotor system, the results of which showed that the climbing angle, acceleration, and other flight parameters make significant influence on the parameter range for bifurcation, quasi-periodic response and chaotic response as well as system stability.…”

Section: Introductionmentioning

confidence: 93%

Nonlinear response and bifurcation analysis of a Duffing type rotor model under sine maneuver load

Hou

Chen

et al. 2016

International Journal of Non-Linear Mechanics

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Section: Introductionmentioning

confidence: 93%

Nonlinear response and bifurcation analysis of a Duffing type rotor model under sine maneuver load

Hou

Chen

et al. 2016

International Journal of Non-Linear Mechanics

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“…Based upon these, the studies were extended to geared rotor system under sinusoidal moving bases [22]. Hou et al [16] focused on the nonlinear vibration phenomenon caused by aircraft hovering flight in a rub-impact rotor system supported by two general supports with cubic stiffness. Moreover, several researchers also concerned about the active vibration control of base excited rotor-bearing system utilizing the electromagnetic actuators [17][18][19].…”

Section: Introductionmentioning

confidence: 99%

“…The moving base not only causes external force excitations but also gyroscopic and stiffness excitations to the rotor-bearing system. Over the past ten years, a number of studies [5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22] have been carried out on the dynamic characteristics of base excited rotor systems, which differ distinctly from that of the fixed supported rotor systems.…”

Section: Introductionmentioning

confidence: 99%

Parametric instability of flexible rotor-bearing system under time-periodic base angular motions

Han

Chu

2015

Applied Mathematical Modelling

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a b s t r a c tParametric instability of flexible rotor-bearing system under time-periodic base angular motions is analyzed in this paper. The accurate finite element model for the flexible rotor-bearing system under time-varying base angular motions is derived based upon the energy theorem and Lagrange's principle. Three base angular motions, including the rolling, pitching and yawing motions, are assumed to be sinusoidal perturbations superimposed upon constant terms. Considering the time-varying base movements, the second order differential equations of the system will have time-periodic gyroscopic and stiffness coefficients. The discrete state transition matrix (DSTM) method is introduced for numerically acquiring the instability regions. Based upon these, instability computations for a rotor-bearing system with one base motion alone and two base motions together are conducted, respectively. The effects of rotating speed, amplitudes of base motion and phases between two base motions on both the primary and combination instability regions are discussed in detail.

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“…The motivation of this paper is to detect the effect of maneuver load on the dynamic response of an aircraft rotor-ball bearing system, since the dynamical effect of maneuvering flight to the rotor system of the aircraft engine becomes an interesting topic in recent years [30][31][32]. The turning flight model proposed herein enables us to investigate the nonlinear behaviors of the system under maneuver load.…”

Section: Introductionmentioning

confidence: 99%

Turning maneuver caused response in an aircraft rotor-ball bearing system

et al. 2014

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This paper focuses on the nonlinear response caused by aircraft turning flight in a rotor-ball bearing system with internal clearances and Hertzian contact forces. The equations of motion are formulated by using Lagrange equation, where the aircraft turning flight is modeled as a maneuver load. Numerical analyses are carried out to detect the response of the system under maneuver load. The sub-harmonic resonance and irregular motions subjected to the maneuver load are obtained and presented by bifurcation diagrams, amplitude spectrum diagrams, Poincare maps and phase portraits. Two typical patterns that the maneuver load inducing response are found: one is the alternating of period 2 motion and period 1 motion for ω = 1,350 rad/s; the other is the alternating of quasi-periodic motion and period 2 motion for ω = 1,470 rad/s. Moreover, mass eccentricity shows a significant effect on the sub-harmonic resonance of the rotor-ball bearing system under turning flight, which is different from that without considering maneuvering flight condition (Bai and Zhang in Int J Nonlinear Mech 50:1-10, 2013). The results obtained in this paper will contribute an understanding of the nonlinear dynamic behaviors of aircraft rotor systems in maneuvering flight.

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Nonlinear vibration phenomenon of an aircraft rub-impact rotor system due to hovering flight

Cited by 66 publications

References 28 publications

Nonlinear response and bifurcation analysis of a Duffing type rotor model under sine maneuver load

Nonlinear response and bifurcation analysis of a Duffing type rotor model under sine maneuver load

Parametric instability of flexible rotor-bearing system under time-periodic base angular motions

Turning maneuver caused response in an aircraft rotor-ball bearing system

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