Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor

Li, Kewei; Su, Taoyong; Ma, Jinchao; Zhang, Zhaozhong

doi:10.3390/machines11020237

Open AccessArticle

Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor

by

Kewei Li

^1,2,3,

Taoyong Su

^2,3,*

,

Jinchao Ma

⁴ and

Zhaozhong Zhang

²

¹

National Key Laboratory of Rotorcraft Aeromechanics, College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

²

School of General Aviation, Nanchang Hangkong University, Nanchang 330063, China

³

Rotor Aerodynamics Key Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China

⁴

School of Mechanical Technology, Wuxi Institute of Technology, Wuxi 214121, China

^*

Author to whom correspondence should be addressed.

Machines 2023, 11(2), 237; https://doi.org/10.3390/machines11020237

Submission received: 1 January 2023 / Revised: 31 January 2023 / Accepted: 31 January 2023 / Published: 6 February 2023

(This article belongs to the Special Issue Dynamic Stability Analysis of Aerospace Structures)

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Abstract

An electrically controlled rotor (ECR), also known as a swashplateless rotor, is an active rotor system that reduces the vibration load of the rotor through active control while achieving primary control by using a trailing edge flap system instead of a swashplate. In this study, the control effect of a 2Ω higher-order harmonic input on the vibration load of an ECR is investigated. First, an analytical aeroelastic model of the ECR is established based on Hamilton’s principle and an unsteady aerodynamic model with a flapped airfoil. On this basis, the use of higher-order harmonic flap control to reduce the vibration load of the ECR is investigated. The effect of the 2Ω higher-order harmonic flap control on the 2Ω vibration load of the example ECR is analyzed by sweeping the amplitude and phase of the higher-order harmonic flap control. The effect of higher-order harmonic flap control on the primary control of the ECR is also analyzed. The results show that the 2Ω higher-order flap deflection has the most significant control effect on the 2Ω vertical vibration load of the hub, that there is coupling between the higher-order flap deflection and the primary control of the ECR, and that the higher-order flap deflection disrupts the original equilibrium of the ECR.

Keywords: helicopter; electrically controlled rotor; aeroelasticity; vibration control; trailing edge flaps

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MDPI and ACS Style

Li, K.; Su, T.; Ma, J.; Zhang, Z. Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor. Machines 2023, 11, 237. https://doi.org/10.3390/machines11020237

AMA Style

Li K, Su T, Ma J, Zhang Z. Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor. Machines. 2023; 11(2):237. https://doi.org/10.3390/machines11020237

Chicago/Turabian Style

Li, Kewei, Taoyong Su, Jinchao Ma, and Zhaozhong Zhang. 2023. "Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor" Machines 11, no. 2: 237. https://doi.org/10.3390/machines11020237

APA Style

Li, K., Su, T., Ma, J., & Zhang, Z. (2023). Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor. Machines, 11(2), 237. https://doi.org/10.3390/machines11020237

Note that from the first issue of 2016, this journal uses article numbers instead of page numbers. See further details here.

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Open-Loop Simulation of Active Vibration Control of Electrically Controlled Rotor

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