A directly coil-actuated cyclic pitch control based rotor: Design, modeling, and analysis

Qi Wu; Dewei Tang; Qiquan Quan; Kaijie Zhu; Yuanxu Wu; Zongquan Deng

doi:10.1016/j.ast.2023.108423

A directly coil-actuated cyclic pitch control based rotor: Design, modeling, and analysis

Qi Wu
, Dewei Tang
, Qiquan Quan^*
, Kaijie Zhu
, Yuanxu Wu
, Zongquan Deng

^*Corresponding author for this work

School of Mechatronics Engineering

Harbin Institute of Technology

Research output: Contribution to journal › Article › peer-review

6 Scopus citations

Abstract

This work introduces a directly coil-actuated cyclic pitch control method for the swashplate-less aircraft. This method drives the rotor to rotate periodically around the pitch axis through a magnetic field. The sensitive parameters that affect pitch motion are analyzed and optimized by simulation. Next, the aerodynamic model of the rotor is established by idealizing the blade as a centrally hinged rigid body with a spring restraint, and then the kinematic model of the rotor system is obtained. A state feedback attitude control method is proposed based on the kinematic model. The feasibility of the directly coil-actuated cyclic pitch control method is verified by comparing the results of mechanical experiments and numerical calculations. Moreover, the attitude response of the rotor system is evaluated through attitude experiments.

Original language	English
Article number	108423
Journal	Aerospace Science and Technology
Volume	140
DOIs	https://doi.org/10.1016/j.ast.2023.108423
State	Published - Sep 2023

Keywords

Attitude response
Magnetic field
Mechanical experiments
Rotorcraft
Swashplate-less

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10.1016/j.ast.2023.108423

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title = "A directly coil-actuated cyclic pitch control based rotor: Design, modeling, and analysis",

abstract = "This work introduces a directly coil-actuated cyclic pitch control method for the swashplate-less aircraft. This method drives the rotor to rotate periodically around the pitch axis through a magnetic field. The sensitive parameters that affect pitch motion are analyzed and optimized by simulation. Next, the aerodynamic model of the rotor is established by idealizing the blade as a centrally hinged rigid body with a spring restraint, and then the kinematic model of the rotor system is obtained. A state feedback attitude control method is proposed based on the kinematic model. The feasibility of the directly coil-actuated cyclic pitch control method is verified by comparing the results of mechanical experiments and numerical calculations. Moreover, the attitude response of the rotor system is evaluated through attitude experiments.",

keywords = "Attitude response, Magnetic field, Mechanical experiments, Rotorcraft, Swashplate-less",

author = "Qi Wu and Dewei Tang and Qiquan Quan and Kaijie Zhu and Yuanxu Wu and Zongquan Deng",

note = "Publisher Copyright: {\textcopyright} 2023 Elsevier Masson SAS",

year = "2023",

month = sep,

doi = "10.1016/j.ast.2023.108423",

language = "英语",

volume = "140",

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TY - JOUR

T1 - A directly coil-actuated cyclic pitch control based rotor

T2 - Design, modeling, and analysis

AU - Wu, Qi

AU - Tang, Dewei

AU - Quan, Qiquan

AU - Zhu, Kaijie

AU - Wu, Yuanxu

AU - Deng, Zongquan

PY - 2023/9

Y1 - 2023/9

N2 - This work introduces a directly coil-actuated cyclic pitch control method for the swashplate-less aircraft. This method drives the rotor to rotate periodically around the pitch axis through a magnetic field. The sensitive parameters that affect pitch motion are analyzed and optimized by simulation. Next, the aerodynamic model of the rotor is established by idealizing the blade as a centrally hinged rigid body with a spring restraint, and then the kinematic model of the rotor system is obtained. A state feedback attitude control method is proposed based on the kinematic model. The feasibility of the directly coil-actuated cyclic pitch control method is verified by comparing the results of mechanical experiments and numerical calculations. Moreover, the attitude response of the rotor system is evaluated through attitude experiments.

AB - This work introduces a directly coil-actuated cyclic pitch control method for the swashplate-less aircraft. This method drives the rotor to rotate periodically around the pitch axis through a magnetic field. The sensitive parameters that affect pitch motion are analyzed and optimized by simulation. Next, the aerodynamic model of the rotor is established by idealizing the blade as a centrally hinged rigid body with a spring restraint, and then the kinematic model of the rotor system is obtained. A state feedback attitude control method is proposed based on the kinematic model. The feasibility of the directly coil-actuated cyclic pitch control method is verified by comparing the results of mechanical experiments and numerical calculations. Moreover, the attitude response of the rotor system is evaluated through attitude experiments.

KW - Attitude response

KW - Magnetic field

KW - Mechanical experiments

KW - Rotorcraft

KW - Swashplate-less

UR - https://www.scopus.com/pages/publications/85161346533

U2 - 10.1016/j.ast.2023.108423

DO - 10.1016/j.ast.2023.108423

M3 - 文章

AN - SCOPUS:85161346533

SN - 1270-9638

VL - 140

JO - Aerospace Science and Technology

JF - Aerospace Science and Technology

M1 - 108423

ER -

A directly coil-actuated cyclic pitch control based rotor: Design, modeling, and analysis

Abstract

Keywords

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