Optimization selection approach for distribution of actuators in active vibration control of helicopter

Qiyou, Cheng; Jing-hui, Deng; Ai-min, Ling; Ke, Lei

doi:10.1109/chicc.2015.7260140

Cited by 4 publications

(2 citation statements)

References 5 publications

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“…However, with the increasing requirements for helicopter flight height, flight time and flight environment, higher requirements are put forward for the vibration reduction level of the body [10]. Because the linear force actuator can only output single direction power, it can not meet the increasing demand of vibration elimination.…”

Section: Introductionmentioning

confidence: 99%

Research on Control Strategy of Two Dimensional Output Force Vibration Damping Electric Actuator

et al. 2021

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Section: Introductionmentioning

confidence: 99%

Research on Control Strategy of Two Dimensional Output Force Vibration Damping Electric Actuator

et al. 2021

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“…Therefore, the noise and vibration levels of fixed wing aircraft used by general have been included in the national military standard assessment range [1][2]. At the same time, in order to improve the vibration environment of airborne equipment, improve its safety and reliability, and improve the working state of pilots, vibration reduction has become a research hotspot of major non fixed wing aircraft manufacturers and research institutions in the world [3][4].…”

Section: Introductionmentioning

confidence: 99%

Design of Eccentric Mass-Type Vibration-Damping Electric Actuator Control System for Non-Fixed-Wing Aircraft

et al. 2020

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A Cross-Coupled Control Strategy of Phase Difference for Electric Vibration Damping Actuator

Hao

Cao

et al. 2020

IEEE Access

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The active vibration damping actuator uses dual-motors to drive two sets of eccentric wheels to achieve active vibration reduction, but the backlash nonlinearity and eccentric load will cause the load speed and load position to be out of synchronization, which will influence the system vibration reduction effect. The traditional parallel control strategy controls the dual motors separately without the consideration of internal coupling effect, leading to a poor synchronization performance. In order to solve these problems, a load position difference cross-coupled control strategy based on multiple-input and multiple-output (MIMO) is proposed in this paper. The minimum singular value of return difference matrix is used to analyze the stability margin of active vibration damping actuator system under the traditional parallel control strategy and the cross-coupled control strategy, and the analysis procedure has considered the influences of load disturbance and backlash nonlinearity. At the same time, the sensitivity comparison of the two strategies is conducted, and the results indicate that the system under cross-coupled control strategy has stronger relative stability and robustness. On this basis, a method for designing synchronization controller parameters is given. The stability region of parameters satisfying the requirement of stability margin is determined with the help of minimum singular value of return difference matrix. Then, the optimal value is found in the obtained parameter stability region according to the dynamic and steady-state performance. Finally, an experimental platform is set up to verify the effectiveness of cross-coupled control strategy and the rationality of parameter tuning. INDEX TERMS the electric vibration damping actuator, synchronization, cross-coupled control, stability margin, the minimum singular value, optimal tuning

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Optimization selection approach for distribution of actuators in active vibration control of helicopter

Cited by 4 publications

References 5 publications

Research on Control Strategy of Two Dimensional Output Force Vibration Damping Electric Actuator

Research on Control Strategy of Two Dimensional Output Force Vibration Damping Electric Actuator

Design of Eccentric Mass-Type Vibration-Damping Electric Actuator Control System for Non-Fixed-Wing Aircraft

A Cross-Coupled Control Strategy of Phase Difference for Electric Vibration Damping Actuator

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