ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Vibration damping electric actuator system based on parallel independent control strategy
Received date: 2023-09-13
Revised date: 2023-10-06
Accepted date: 2023-11-08
Online published: 2023-11-22
Supported by
National Natural Science Foundation of China(52077100);Aeronautical Science Foundation of China(201958052001)
The traditional vibration damping electric actuator adopts cross-coupling control strategy to realize the servo control of output force. However， there are coupling control items in this control strategy， which affect the rapidity and accuracy of the system response and reduces the vibration reduction efficiency of the actuator. At the same time， the impulse voltage on the Direct Current （DC） bus side cannot meet the requirements of the national military standard， which directly threatens the flight safety of the helicopter. This paper proposes a servo control system for vibration damping electric actuator using the parallel independent control strategy. Firstly， the given output force of the system is decoupled to realize the parallel and independent operation of multi-motors. Secondly， the dominant pole method and maximum sensitivity method are used to design the dynamic and steady-state characteristics and robustness of the system from the perspectives of time domain and frequency domain， respectively. Finally， an experimental platform is set up to compare the control strategies. The unitary experimental data show that the response accuracy of the system is increased by 3.6% and the response time is reduced by 40% when the direction is changed； the response accuracy is increased by 1.5% and the response time is reduced by 31% when the phase is changed； the voltage impact value on the DC bus side is reduced by 8 V. The experimental data verify the effectiveness and advantages of the parallel independent control strategy.
Zhenyang HAO , Fengting ZHANG , Jian YANG , Xin CAO . Vibration damping electric actuator system based on parallel independent control strategy[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2024 , 45(13) : 329573 -329573 . DOI: 10.7527/S1000-6893.2023.29573
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