Active Vibration Control of Flexible Rotors on Maneuvering Vehicles

This research work deals with tip vibration control of a Two-Link Flexible manipulator using hybrid control technique. This technique involves the implementation of unconstrained viscoelastic damping layer on the links in conjunction with active damping using piezoelectric sensors and actuators. Mathematical modelling of the complete system is done using the finite element approach in the inertial frame. Viscoelastic damping is modelled using Kelvin-Voigt elements for which a damping matrix is derived. Active damping is modelled as time-dependent uniformly distributed load applied by the piezoelectric actuator on the flexible link working under feedback control. The angular and linear velocities of the tips of flexible links are used for direct feedback. The unconstrained viscoelastic damping layer effectively reduces the vibrations of the system. The effectiveness of the active control depends upon the relative position of sensors and actuators on the links. The novelty of the work lies in control of torsional and flexural vibrations through the application of passive and active damping methods to the non-inertial frames represented by the manipulator links.

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“…The effects of passive and active vibration controls are also studied with respect to the inertial frame of Ref. [46].…”

Section: Mathematical Modellingmentioning

confidence: 99%

Hybrid vibration control of a Two-Link Flexible manipulator

Mishra

Singh

2019

SN Appl. Sci.

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“…As the simple rotor model was used, so their study could only give a qualitative insight into the systems's unstable behavior. Das et al [18,19] utilized the electromagnetic actuators to control the unstable responses of unbalanced flexible-shaft systems parametrically excited due to base motion. Only the pitching base motion was considered, while the other two base motions (rolling and yawing) were ignored in their studies.…”

Section: Introductionmentioning

confidence: 99%

“…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%

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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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“…Das et al. 26 predicted transient response of a flexible rotor mounted on a moving vehicle under a turning or pitching motion and utilized an electromagnetic actuator to actively control transverse vibration. Similarly, Soni et al.…”

Section: Introductionmentioning

confidence: 99%

Effect of flight/structural parameters and operating conditions on dynamic behavior of a squeeze-film damped rotor system during diving–climbing maneuver

Chen

Gan

Ren

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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During aircraft maneuvering flights, engine's rotor-bearing systems are subjected to parametric excitations and additional inertial forces, which may cause severe vibration and abnormal operation. Based on Lagrange's principle combined with finite element modeling, the differential equations of motion for a squeeze film damped rotor-bearing system mounted on an aircraft in maneuvering flight are derived. Using Newmark–Hilber–Hughes–Taylor integration method, dynamic characteristics of the nonlinear rotor system under maneuvering flight are investigated. The factors are considered, involving mass unbalance, oil–film force, gravity, parametric excitations and additional inertial forces, and instantaneous static eccentricity of journal induced by maneuvering loads. The effects of forward velocity, radius of curvature, rotating speed, mass unbalance, oil–film clearance, and elastic support stiffness on transient responses of rotor system are discussed during diving–climbing maneuver. The results indicate that when the aircraft performs a diving–climbing maneuver in the vertical plane, the journal deviates from the center of oil–film outer ring, and the excursion direction of whirl orbit is determined by centrifugal acceleration and additional gyroscopic moment. The journal whirls asynchronously around the instantaneous static eccentricity and its magnitude is related to the maneuvering loads and the supporting stiffness. Increasing forward velocity or decreasing pitching radius, the rotor vibration will enter earlier into or withdraw later from the relatively large eccentricity. Rotating near critical speeds or excessive mass unbalances should be prevented during maneuvering flights. For large maneuver, the oil–film radial clearance needs to be enlarged properly to avoid hard contact between journal and outer ring. In addition, the stiffness of elastic support needs to be appropriately determined for damping performance. Overall, it provides a flexible approach with good expandability to predict dynamic characteristics of on-board squeeze-film damped rotor system during maneuvering flights in the design process.

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Active Vibration Control of Flexible Rotors on Maneuvering Vehicles

Cited by 25 publications

References 21 publications

Hybrid vibration control of a Two-Link Flexible manipulator

Hybrid vibration control of a Two-Link Flexible manipulator

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

Effect of flight/structural parameters and operating conditions on dynamic behavior of a squeeze-film damped rotor system during diving–climbing maneuver

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