Multiobjective Design Optimization of Ironless Permanent Magnet Linear Synchronous Motors for Improved Thrust and Reduced Thrust Ripple

Li, Li Yi; Tang, Yong Bin; Liu, Jia Xi

doi:10.4028/www.scientific.net/amm.416-417.395

Cited by 4 publications

(3 citation statements)

References 7 publications

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“…Where F MRD is the total damping force of MR damper, c is the viscous damping coefficient, k is the stiffness coefficient, a is the scale factor of the hysteresis loop, z hysteretic operator, in which b is the slope of the hysteresis loop, d is the width coefficient of hysteresis loop, f 0 is the offset damping force. Multi-population genetic algorithm (MGA) (Li et al, 2013) was used to identify the parameters of hyperbolic tangential model. This algorithm can effectively restrain the phenomena of premature convergence, poor local search ability, and late population assimilation of the standard genetic algorithm.…”

Section: Dynamic Model Of Mr Dampermentioning

confidence: 99%

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Design and control of helicopter main reducer semi-active vibration isolation system based on MR damper

Wang

Zhou

Cao

et al. 2023

Journal of Intelligent Material Systems and Structures

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In order to effectively reduce the vibration of the helicopter rotor transmitted from the main reducer to the fuselage, a semi-active vibration isolation system (SAVIS) with a magnetorheological (MR) damper was proposed and effective control strategies were designed. Firstly, the structural scheme and working principle of helicopter main reducer SAVIS were proposed. Secondly, the mechanical properties of the MR damper were tested, and the dynamic model of the MR damper was established based on the hyperbolic tangent model. In addition, the model errors of MR damper were analyzed and quantified. Thirdly, according to the design requirements and parameters of a helicopter, the structural parameters of SAVIS were designed. Then, the virtual prototype of helicopter main reducer SAVIS was established by using 3D drawing software and ADAMS software, and the vibration characteristics of three directions were analyzed. Finally, two controllers of equivalent skyhook and continuous skyhook were designed. The numerical analysis results indicate that compared with passive vibration isolation and equivalent skyhook controller, the continuous skyhook controller has the best vibration isolation performance and disturbance resistance, which can effectively reduce the vibration transmitted from helicopter rotor to fuselage.

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Section: Dynamic Model Of Mr Dampermentioning

confidence: 99%

“…Multi-population genetic algorithm (MGA) (Li et al, 2013) was used to identify the parameters of hyperbolic tangential model. This algorithm can effectively restrain the phenomena of premature convergence, poor local search ability, and late population assimilation of the standard genetic algorithm.…”

Section: Dynamic Modeling Of Mr Dampermentioning

confidence: 99%

Design and control of helicopter main reducer semi-active vibration isolation system based on MR damper

Wang

Zhou

Cao

et al. 2023

Journal of Intelligent Material Systems and Structures

View full text Add to dashboard Cite

show abstract

“…Byungkwan et al [8] proposed an adaptive particle swarm optimization algorithm for reluctance motor optimization, which converged faster than the standard particle swarm optimization algorithm and had an improved ability to search for a better solution set. Li et al [9] used a multiple swarm genetic algorithm with a strong search capability for the multi-objective optimization of the thrust density, thrust fluctuation, and loss using the dimensions of the permanent magnets and toroidal windings of a coreless permanent magnet linear synchronous motor as variables. It was verified that the optimal design results obtained by MPGA were in good agreement with the design objectives under different weight coefficients.…”

Section: Introductionmentioning

confidence: 99%

Interval Uncertainty Optimization Method for Electromagnetic Orbital Launcher

Jin,

Liu,

Song

et al. 2023

Applied Sciences

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The performance optimization and reliability of electromagnetic orbital launchers need to take into account the uncertainties that exist in the manufacturing and service processes. Considering that it is difficult to identify the problem of the parameter probability distribution in advance for electromagnetic orbital launchers, this paper uses the interval number to describe the uncertain variables and realizes the conversion of uncertainty optimization into deterministic optimization problems based on interval sequential relations; moreover, it establishes interval uncertainty optimization methods. The converted deterministic optimization problem is solved by combining a high-precision proxy model with an optimization algorithm to search for the optimal solution set. Finally, reliability estimation is achieved by taking the armature of the electromagnetic orbital launcher as the optimization object. The computational example proves that the method is able to deal with the optimization problem of the parameter interval of an electromagnetic orbital launcher containing uncertain parameters and has good engineering applicability.

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The Frequency Characteristics Simulation of Traveling Wave Thermo-Acoustic Engine

Ma¹,

Xia²,

Tie³

2013

TELKOMNIKA

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Multiobjective Design Optimization of Ironless Permanent Magnet Linear Synchronous Motors for Improved Thrust and Reduced Thrust Ripple

Cited by 4 publications

References 7 publications

Design and control of helicopter main reducer semi-active vibration isolation system based on MR damper

Design and control of helicopter main reducer semi-active vibration isolation system based on MR damper

Interval Uncertainty Optimization Method for Electromagnetic Orbital Launcher

The Frequency Characteristics Simulation of Traveling Wave Thermo-Acoustic Engine

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